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FLARE(Flyby Anomaly Research Endeavor)
bull Project Managerndash Amritpreet Kang
bull Systems Engineerndash Graeme Ramsey
bull Chief Engineerndash Jeffrey Alfaro
bull Associate Engineersndash Kyle Chaffinndash Anthony Huet
= 3099 x
point mass orbital mechanics 2D flyby visual
Presentation Overview
bull Backgroundbull Mission Statementsbull Requirementsbull Constraintsbull CONOPSbull Baselinebull Trade Studiesbull Design Selectionbull Commentary
Speaker Amritpreet Kang
Graphic courtesy of NASA
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 1
Executive Summarybull Team FLARE of the University of Texas at Austin has been tasked with confirming the flyby anomaly
notably experienced first by Galileo in 1990 followed by NEAR Cassini Messenger and Rosetta
bull The anomaly takes the form of an unaccounted for change in energyvelocity which takes place around periapse of a hyperbolic planetary flyby during which their is a change in declination The velocity anomalies vary by as much as 135 mms from precisely modeled values
bull A phenomenological formula which relates the velocity discrepancy to a change in declination excess velocity and a constant scaling factor serves to guide a flyby trajectory corollary to the anomaly
bull Many causes have been conjectured accounted for or otherwise proved innocent (from atmospheric drag to modifications to inertia) A thorough investigation of the navigation software and mathematical models used for navigation by JPL uncovered two potential culprits (high order gravity terms and anisotropy of the speed of light)
bull Team FLARErsquos proposed design is an affordable CubeSat mission whose goal is to gather more data points on the anomaly to corroborate its existence
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 2
Executive Summary
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 2
The primary benefit from this mission is filling in the gap of closest approach left by most heritage missions and in the process prove whether the anomaly truly exists Furthermore the data gained from FLARE would allow further evaluation of the two most probable explanations of the anomaly
This endeavor will lead to more accurate trajectory propagation methods by further characterizing this anomalous perturbation By those standards objects like Earth rendezvousing asteroids will be predictable to a higher degree
Anomaly Background
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 3
Parameter GLL-I GLL-II NEAR Cassini Rosetta MGer Juno
Date 1281990 1281992 1231998 8181999 342005 822005
H (km) 960 303 539 1175 1956 2347
φ (deg) 252 -338 33 -235 202 4695
λ (deg) 2965 3544 472 2314 2468 1075
Vf (kms) 1374 1408 12739 19026 10517 10389
V_inf (kms) 8949 8877 6851 1601 3863 4056 991
DA (deg) 477 511 669 197 993 947
i (deg) 1429 1387 108 254 1449 1331
αi (deg) 26676 21935 26117 33431 34612 29261
δi (deg) -1252 -3426 -2076 -1292 -281 3144 -142
αo (deg) 21997 17435 18349 35254 24651 22717
δo (deg) -3415 -487 -7196 -499 -3429 -3192 394
MSC (kg) 2497 2497 730 4612 2895 1086
ΔV_inf (mms) 392 -46 1346 -2 18 002 0
σV_inf (mms) 03 1 001 1 003 001 2
Theoretical ΔV_inf (mms) 412 -467 1328 -107 207 006 604
= 3099 x
Heritage Mission Data Acquisition Overview
Heritage missions navigation precision details [24-26 26]
bull Instruments used on heritage missions to obtain velocity databull With these instruments NEAR measured the highest change in hyperbolic excess
velocity whereas Juno measured no apparent changebull Uniquely Juno incorporated 50x50 and 100x100 gravitational modeling leading to
mismatch between expected and apparent anomaly in fact no apparent anomaly [36]
bull Explanations of the flyby anomaly focus on modeling errorsbull Higher order gravity termsbull Anisotropy of the speed of light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 4
Speaker Kyle Chaffin
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
JUNO Doppler postfit residuals reconstruction (left) and deleted data (right) [36]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Dominate Anomaly Sources (JUNO) High Order Gravity
Speaker Kyle Chaffin and Graeme Ramsey
Simulated Doppler residuals from 7 mms anomaly with (left) and without (right) spin signature [36]
Speaker Kyle Chaffin and Graeme Ramsey
Position (top) and Velocity (bottom) perturbations incurred by modeling with higher order gravity models than 10X10 [36]
The order of this perturbation is comparable to that of the anomaly
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Presentation Overview
bull Backgroundbull Mission Statementsbull Requirementsbull Constraintsbull CONOPSbull Baselinebull Trade Studiesbull Design Selectionbull Commentary
Speaker Amritpreet Kang
Graphic courtesy of NASA
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 1
Executive Summarybull Team FLARE of the University of Texas at Austin has been tasked with confirming the flyby anomaly
notably experienced first by Galileo in 1990 followed by NEAR Cassini Messenger and Rosetta
bull The anomaly takes the form of an unaccounted for change in energyvelocity which takes place around periapse of a hyperbolic planetary flyby during which their is a change in declination The velocity anomalies vary by as much as 135 mms from precisely modeled values
bull A phenomenological formula which relates the velocity discrepancy to a change in declination excess velocity and a constant scaling factor serves to guide a flyby trajectory corollary to the anomaly
bull Many causes have been conjectured accounted for or otherwise proved innocent (from atmospheric drag to modifications to inertia) A thorough investigation of the navigation software and mathematical models used for navigation by JPL uncovered two potential culprits (high order gravity terms and anisotropy of the speed of light)
bull Team FLARErsquos proposed design is an affordable CubeSat mission whose goal is to gather more data points on the anomaly to corroborate its existence
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 2
Executive Summary
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 2
The primary benefit from this mission is filling in the gap of closest approach left by most heritage missions and in the process prove whether the anomaly truly exists Furthermore the data gained from FLARE would allow further evaluation of the two most probable explanations of the anomaly
This endeavor will lead to more accurate trajectory propagation methods by further characterizing this anomalous perturbation By those standards objects like Earth rendezvousing asteroids will be predictable to a higher degree
Anomaly Background
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 3
Parameter GLL-I GLL-II NEAR Cassini Rosetta MGer Juno
Date 1281990 1281992 1231998 8181999 342005 822005
H (km) 960 303 539 1175 1956 2347
φ (deg) 252 -338 33 -235 202 4695
λ (deg) 2965 3544 472 2314 2468 1075
Vf (kms) 1374 1408 12739 19026 10517 10389
V_inf (kms) 8949 8877 6851 1601 3863 4056 991
DA (deg) 477 511 669 197 993 947
i (deg) 1429 1387 108 254 1449 1331
αi (deg) 26676 21935 26117 33431 34612 29261
δi (deg) -1252 -3426 -2076 -1292 -281 3144 -142
αo (deg) 21997 17435 18349 35254 24651 22717
δo (deg) -3415 -487 -7196 -499 -3429 -3192 394
MSC (kg) 2497 2497 730 4612 2895 1086
ΔV_inf (mms) 392 -46 1346 -2 18 002 0
σV_inf (mms) 03 1 001 1 003 001 2
Theoretical ΔV_inf (mms) 412 -467 1328 -107 207 006 604
= 3099 x
Heritage Mission Data Acquisition Overview
Heritage missions navigation precision details [24-26 26]
bull Instruments used on heritage missions to obtain velocity databull With these instruments NEAR measured the highest change in hyperbolic excess
velocity whereas Juno measured no apparent changebull Uniquely Juno incorporated 50x50 and 100x100 gravitational modeling leading to
mismatch between expected and apparent anomaly in fact no apparent anomaly [36]
bull Explanations of the flyby anomaly focus on modeling errorsbull Higher order gravity termsbull Anisotropy of the speed of light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 4
Speaker Kyle Chaffin
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
JUNO Doppler postfit residuals reconstruction (left) and deleted data (right) [36]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Dominate Anomaly Sources (JUNO) High Order Gravity
Speaker Kyle Chaffin and Graeme Ramsey
Simulated Doppler residuals from 7 mms anomaly with (left) and without (right) spin signature [36]
Speaker Kyle Chaffin and Graeme Ramsey
Position (top) and Velocity (bottom) perturbations incurred by modeling with higher order gravity models than 10X10 [36]
The order of this perturbation is comparable to that of the anomaly
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Executive Summarybull Team FLARE of the University of Texas at Austin has been tasked with confirming the flyby anomaly
notably experienced first by Galileo in 1990 followed by NEAR Cassini Messenger and Rosetta
bull The anomaly takes the form of an unaccounted for change in energyvelocity which takes place around periapse of a hyperbolic planetary flyby during which their is a change in declination The velocity anomalies vary by as much as 135 mms from precisely modeled values
bull A phenomenological formula which relates the velocity discrepancy to a change in declination excess velocity and a constant scaling factor serves to guide a flyby trajectory corollary to the anomaly
bull Many causes have been conjectured accounted for or otherwise proved innocent (from atmospheric drag to modifications to inertia) A thorough investigation of the navigation software and mathematical models used for navigation by JPL uncovered two potential culprits (high order gravity terms and anisotropy of the speed of light)
bull Team FLARErsquos proposed design is an affordable CubeSat mission whose goal is to gather more data points on the anomaly to corroborate its existence
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 2
Executive Summary
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 2
The primary benefit from this mission is filling in the gap of closest approach left by most heritage missions and in the process prove whether the anomaly truly exists Furthermore the data gained from FLARE would allow further evaluation of the two most probable explanations of the anomaly
This endeavor will lead to more accurate trajectory propagation methods by further characterizing this anomalous perturbation By those standards objects like Earth rendezvousing asteroids will be predictable to a higher degree
Anomaly Background
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 3
Parameter GLL-I GLL-II NEAR Cassini Rosetta MGer Juno
Date 1281990 1281992 1231998 8181999 342005 822005
H (km) 960 303 539 1175 1956 2347
φ (deg) 252 -338 33 -235 202 4695
λ (deg) 2965 3544 472 2314 2468 1075
Vf (kms) 1374 1408 12739 19026 10517 10389
V_inf (kms) 8949 8877 6851 1601 3863 4056 991
DA (deg) 477 511 669 197 993 947
i (deg) 1429 1387 108 254 1449 1331
αi (deg) 26676 21935 26117 33431 34612 29261
δi (deg) -1252 -3426 -2076 -1292 -281 3144 -142
αo (deg) 21997 17435 18349 35254 24651 22717
δo (deg) -3415 -487 -7196 -499 -3429 -3192 394
MSC (kg) 2497 2497 730 4612 2895 1086
ΔV_inf (mms) 392 -46 1346 -2 18 002 0
σV_inf (mms) 03 1 001 1 003 001 2
Theoretical ΔV_inf (mms) 412 -467 1328 -107 207 006 604
= 3099 x
Heritage Mission Data Acquisition Overview
Heritage missions navigation precision details [24-26 26]
bull Instruments used on heritage missions to obtain velocity databull With these instruments NEAR measured the highest change in hyperbolic excess
velocity whereas Juno measured no apparent changebull Uniquely Juno incorporated 50x50 and 100x100 gravitational modeling leading to
mismatch between expected and apparent anomaly in fact no apparent anomaly [36]
bull Explanations of the flyby anomaly focus on modeling errorsbull Higher order gravity termsbull Anisotropy of the speed of light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 4
Speaker Kyle Chaffin
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
JUNO Doppler postfit residuals reconstruction (left) and deleted data (right) [36]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Dominate Anomaly Sources (JUNO) High Order Gravity
Speaker Kyle Chaffin and Graeme Ramsey
Simulated Doppler residuals from 7 mms anomaly with (left) and without (right) spin signature [36]
Speaker Kyle Chaffin and Graeme Ramsey
Position (top) and Velocity (bottom) perturbations incurred by modeling with higher order gravity models than 10X10 [36]
The order of this perturbation is comparable to that of the anomaly
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Executive Summary
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 2
The primary benefit from this mission is filling in the gap of closest approach left by most heritage missions and in the process prove whether the anomaly truly exists Furthermore the data gained from FLARE would allow further evaluation of the two most probable explanations of the anomaly
This endeavor will lead to more accurate trajectory propagation methods by further characterizing this anomalous perturbation By those standards objects like Earth rendezvousing asteroids will be predictable to a higher degree
Anomaly Background
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 3
Parameter GLL-I GLL-II NEAR Cassini Rosetta MGer Juno
Date 1281990 1281992 1231998 8181999 342005 822005
H (km) 960 303 539 1175 1956 2347
φ (deg) 252 -338 33 -235 202 4695
λ (deg) 2965 3544 472 2314 2468 1075
Vf (kms) 1374 1408 12739 19026 10517 10389
V_inf (kms) 8949 8877 6851 1601 3863 4056 991
DA (deg) 477 511 669 197 993 947
i (deg) 1429 1387 108 254 1449 1331
αi (deg) 26676 21935 26117 33431 34612 29261
δi (deg) -1252 -3426 -2076 -1292 -281 3144 -142
αo (deg) 21997 17435 18349 35254 24651 22717
δo (deg) -3415 -487 -7196 -499 -3429 -3192 394
MSC (kg) 2497 2497 730 4612 2895 1086
ΔV_inf (mms) 392 -46 1346 -2 18 002 0
σV_inf (mms) 03 1 001 1 003 001 2
Theoretical ΔV_inf (mms) 412 -467 1328 -107 207 006 604
= 3099 x
Heritage Mission Data Acquisition Overview
Heritage missions navigation precision details [24-26 26]
bull Instruments used on heritage missions to obtain velocity databull With these instruments NEAR measured the highest change in hyperbolic excess
velocity whereas Juno measured no apparent changebull Uniquely Juno incorporated 50x50 and 100x100 gravitational modeling leading to
mismatch between expected and apparent anomaly in fact no apparent anomaly [36]
bull Explanations of the flyby anomaly focus on modeling errorsbull Higher order gravity termsbull Anisotropy of the speed of light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 4
Speaker Kyle Chaffin
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
JUNO Doppler postfit residuals reconstruction (left) and deleted data (right) [36]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Dominate Anomaly Sources (JUNO) High Order Gravity
Speaker Kyle Chaffin and Graeme Ramsey
Simulated Doppler residuals from 7 mms anomaly with (left) and without (right) spin signature [36]
Speaker Kyle Chaffin and Graeme Ramsey
Position (top) and Velocity (bottom) perturbations incurred by modeling with higher order gravity models than 10X10 [36]
The order of this perturbation is comparable to that of the anomaly
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Anomaly Background
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 3
Parameter GLL-I GLL-II NEAR Cassini Rosetta MGer Juno
Date 1281990 1281992 1231998 8181999 342005 822005
H (km) 960 303 539 1175 1956 2347
φ (deg) 252 -338 33 -235 202 4695
λ (deg) 2965 3544 472 2314 2468 1075
Vf (kms) 1374 1408 12739 19026 10517 10389
V_inf (kms) 8949 8877 6851 1601 3863 4056 991
DA (deg) 477 511 669 197 993 947
i (deg) 1429 1387 108 254 1449 1331
αi (deg) 26676 21935 26117 33431 34612 29261
δi (deg) -1252 -3426 -2076 -1292 -281 3144 -142
αo (deg) 21997 17435 18349 35254 24651 22717
δo (deg) -3415 -487 -7196 -499 -3429 -3192 394
MSC (kg) 2497 2497 730 4612 2895 1086
ΔV_inf (mms) 392 -46 1346 -2 18 002 0
σV_inf (mms) 03 1 001 1 003 001 2
Theoretical ΔV_inf (mms) 412 -467 1328 -107 207 006 604
= 3099 x
Heritage Mission Data Acquisition Overview
Heritage missions navigation precision details [24-26 26]
bull Instruments used on heritage missions to obtain velocity databull With these instruments NEAR measured the highest change in hyperbolic excess
velocity whereas Juno measured no apparent changebull Uniquely Juno incorporated 50x50 and 100x100 gravitational modeling leading to
mismatch between expected and apparent anomaly in fact no apparent anomaly [36]
bull Explanations of the flyby anomaly focus on modeling errorsbull Higher order gravity termsbull Anisotropy of the speed of light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 4
Speaker Kyle Chaffin
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
JUNO Doppler postfit residuals reconstruction (left) and deleted data (right) [36]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Dominate Anomaly Sources (JUNO) High Order Gravity
Speaker Kyle Chaffin and Graeme Ramsey
Simulated Doppler residuals from 7 mms anomaly with (left) and without (right) spin signature [36]
Speaker Kyle Chaffin and Graeme Ramsey
Position (top) and Velocity (bottom) perturbations incurred by modeling with higher order gravity models than 10X10 [36]
The order of this perturbation is comparable to that of the anomaly
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Heritage Mission Data Acquisition Overview
Heritage missions navigation precision details [24-26 26]
bull Instruments used on heritage missions to obtain velocity databull With these instruments NEAR measured the highest change in hyperbolic excess
velocity whereas Juno measured no apparent changebull Uniquely Juno incorporated 50x50 and 100x100 gravitational modeling leading to
mismatch between expected and apparent anomaly in fact no apparent anomaly [36]
bull Explanations of the flyby anomaly focus on modeling errorsbull Higher order gravity termsbull Anisotropy of the speed of light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 4
Speaker Kyle Chaffin
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
JUNO Doppler postfit residuals reconstruction (left) and deleted data (right) [36]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Dominate Anomaly Sources (JUNO) High Order Gravity
Speaker Kyle Chaffin and Graeme Ramsey
Simulated Doppler residuals from 7 mms anomaly with (left) and without (right) spin signature [36]
Speaker Kyle Chaffin and Graeme Ramsey
Position (top) and Velocity (bottom) perturbations incurred by modeling with higher order gravity models than 10X10 [36]
The order of this perturbation is comparable to that of the anomaly
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
JUNO Doppler postfit residuals reconstruction (left) and deleted data (right) [36]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Dominate Anomaly Sources (JUNO) High Order Gravity
Speaker Kyle Chaffin and Graeme Ramsey
Simulated Doppler residuals from 7 mms anomaly with (left) and without (right) spin signature [36]
Speaker Kyle Chaffin and Graeme Ramsey
Position (top) and Velocity (bottom) perturbations incurred by modeling with higher order gravity models than 10X10 [36]
The order of this perturbation is comparable to that of the anomaly
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Speaker Kyle Chaffin and Graeme Ramsey
JUNO Doppler postfit residuals reconstruction (left) and deleted data (right) [36]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Dominate Anomaly Sources (JUNO) High Order Gravity
Speaker Kyle Chaffin and Graeme Ramsey
Simulated Doppler residuals from 7 mms anomaly with (left) and without (right) spin signature [36]
Speaker Kyle Chaffin and Graeme Ramsey
Position (top) and Velocity (bottom) perturbations incurred by modeling with higher order gravity models than 10X10 [36]
The order of this perturbation is comparable to that of the anomaly
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 5
Dominate Anomaly Sources (JUNO) High Order Gravity
Speaker Kyle Chaffin and Graeme Ramsey
Simulated Doppler residuals from 7 mms anomaly with (left) and without (right) spin signature [36]
Speaker Kyle Chaffin and Graeme Ramsey
Position (top) and Velocity (bottom) perturbations incurred by modeling with higher order gravity models than 10X10 [36]
The order of this perturbation is comparable to that of the anomaly
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Kyle Chaffin and Graeme Ramsey
Position (top) and Velocity (bottom) perturbations incurred by modeling with higher order gravity models than 10X10 [36]
The order of this perturbation is comparable to that of the anomaly
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Phenomenological Formulae and Perturbation Magnitudes
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 6
Speaker Kyle Chaffin and Graeme Ramsey
= 3099 x
bull Primary formula [1]bull Developed by JPL (Anderson et al
2008)bull Effective range 500 to 2000 kmbull Error same as secondary formula
Magnitude of pertinent accelerations courtesy of a Portuguese mission proposal [39]
bull Secondary formula [44]bull Developed by Stephen Adler
Institute for Advanced Studybull Similar range see error table
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Mission Drivers
Need Statement
Evaluate whether the hyperbolic flyby anomaly is a consistent repeatable phenomenon or an otherwise unaccounted for data artifact
GoalsCollect a quantity of at least 4 data points during hyperbolic flybys showing
repeatability of the anomaly and characterizing its effects
ObjectivesCollect position velocity and acceleration data over the course of at least 4
hyperbolic flybys from two spacecraft comparable to the data from the NEAR spacecraft Earth flyby
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 7
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 8
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 9
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Requirements Traceability
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 10
Items after [extra] are requirements that werenrsquot explicitly listed
Traceability Matrix Relationship X=direct O=indirectPrimary Mission
Primary V_inf accuracy 4 data pnts V accuracy Tandem sats Budget Mission Assurance TrajectoryRequirement [A] [B] [C] [D] [extra]
System GNSS A O X XDoppler DSN B X O
Doppler error C X X X XSat Size D O X
Predicted anomaly E O X XAltitude of periapse F X O X X
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Graeme Ramsey
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Constraintsbull Projected satellite lifetime 3 years
ndash Radiation toll and propulsion capacity
ndash 250-300 ms DV corrections capable with 4u worth of hydrazine propulsion
bull (optional) cold gas attitude thrusters desaturation maneuvers for reaction wheals
ndash Medium to High TRL and rad hardened subsystem components only
bull Mission budget $5mil before launch associated costs
bull Secondary payload considerationsndash Satellites must be compatible with a Planetary Systems CSD
ndash Satellite mass 12 kg CSD constraint Max satellite volume 6u
bull Launch window and parking orbitexit trajectory characteristicsndash High eccentricity and inclination Molniya type parking orbit (considering baseline trajectory) [Primary ConOps]
ndash GTO parking orbit option More ride sharing possibilities [Secondary ConOps]
bull Flyby characteristics must coincide with phenomenological formula
bull SHERPA must be compatible with the launch vehicle
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 11
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Graeme Ramsey
CSD payload specifications courtesy of Planetary Systems Corporation [27]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Capsulized Satellite Dispenser (CSD) Constraints
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 12
CSD specifications courtesy of Planetary Systems Corporation [4]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Graeme Ramsey
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
SHERPA Capabilities
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 13
SHERPA configuration (left) and capabilities (right) courtesy of Spaceflight Inc [325]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
ConOps Intro Post-LaunchPre-Flyby Maneuver
SHERPA mounted on a primary payload of a Falcon 9 [25]
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA Rideshare potential [3]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
ConOps Intro Post-LaunchPre-Flyby Maneuver
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 14
Speaker Graeme Ramsey
SHERPA deployment from Falcon 9 payload section [3]
SHERPA 6U CubeSat Deployment via a CDS [4]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
ConOps A Repeat tandem flybys of Earth
Speaker Amritpreet Kang
12
3
4
5
1 Launch as a secondary payload highly inclined
2 SHERPA second stage provides hyperbolic excess velocity for FLARE CubeSats
3 Orbital correction maneuver relayed via DSN Inbound excess velocity via radio Doppler
4 Flyby GPS data from spacecraft to ground stations Ground station measured Doppler shift Possible SLR position monitoring
5 Outbound excess velocity via radio Doppler Orbital correction maneuver relayed via DSN
6 Repeat flyby or disposal based on system lifetime
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 15
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
7 System disposal
12
34
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 16
56
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
CubeSat PBS orange = primary to mission yellow = data source red = in contention
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Baseline Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
INSPIRE cubesat provided for subsystem design heritage (left) and Iris X-Band transponder system (right) courtesy of JPL [33]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Comms DesignAlternative
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
JPL designed X band transponder [34]
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
INSPRE configuration using an X-Band LMRST Comms system [45]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 19
X-Band LMRST Comms Link Budget [34]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) board assembly and fully assembled CubeSat [43]
Antcom L1 GPS patch Antenna PN 15G15A Link Budget Example in LEO
This report from the University of Michigan was intended to assist future CubeSat missions in regards to GPS and link budget [43]
GPS Comms Link Budget and Design
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 20
Radio Aurora eXplorer (RAX) mission GPS Comms Link Budget for reference [43]
GPS Comms Link Budget and Design
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 21
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 22
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Baseline TrajectoryCONOPS A
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 23
DisposalDate 05152018ΔV (ms) Remaininga (km) 11612E+08e 01230i (deg) 68567RAAN (deg) 81239w (deg) -52467
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Baseline TrajectoryCONOPS B
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 24
FlybyΔV (ms) 000V_inf (kms) 200a (km) -994E+04e 10827H (km) 1833DA (deg) 846Vp (kms) 9648δi (deg) 564δo (deg) -282ΔV_inf (mms) -1017
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
DeltaV Budget
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 25
Timeline EventConOps A ndash SHERPA
ConOps A ndash FLARE
ConOps B ndash SHERPA
ConOps B ndash FLARE
Departure 1407 07163
MCM1 0050 0010
MCM2 0100 0020 0010
Flyby1
MCM3 0020 19754
MCM4 0020 0010 0030
Flyby2
Disposal 06430 0040 0020
TOTAL 2200 0100 2722 0050
MARGIN 0400 0050 -0122 0025
AVAILABLE 2600 0150 2600 0075
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 26
bull Slew Ratendash DSN 70m dish 025 degs
34m dish 04 degs
ndash Estrack 34m DSA1 04 degs34m
DSA2 10 degsndash TDRSS 10 degsndash Worst Case 035 degs
bull Visibilityndash DSN Full visibility at gt 30000 km low
visibility for Earth orbits (few stations)ndash Estrack High visibility for Earth orbits due to
cooperating networksndash TDRSS Full visibility (lt 12000 km)
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Tracking Trade Studies
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 27
bull Slew Ratendash Worst Case 035 degs
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Trade Study Separationbull Considerations
ndash Trackability sets inner boundsbull Assume single receiver slew rate to track then reset for second pass
bull FLARE perigee pass length ~2597s for 180 degrees
bull Slew time to return to track 2nd satellite 450s
ndash Minimum separation of 3047s = 11651km at Vinf
ndash Similitude sets outer boundsbull Orbit does not depend on planetary synodic periods
bull Important parameter is direction of inclination of equator to the ecliptic rate of change 099 degday
bull For small angle change results in increased MCM to achieve heliocentric transit
ndash Increased separation increases deltaV for MCM amp separation maneuver
ndash Select separation near minimum w safety margin ~6000s = 22942km
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 28
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Trade Study Satellite Laser Ranging [4647]bull SLR Satellite Laser Ranging measures the travel time of light pulses from
a ground station to a spacecraft and backbull Spacecraft must have special reflector attached bull Altitudes from 300-22000+km
bull SLR Current accuracy on the order of millimetersbull 1-2mm normal point precision
bull Ground Stations available in USA Hawairsquoi Peru Australia South Africa and Tahiti allowing global coverage
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 29
[46]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Trade Study Propulsion Subsystembull Hydrazine Propulsion
ndash Lots of heritage with spacecraftndash Simpler implementationndash Relatively high thrust
bull Electric Propulsionndash Candidate solution for Primary ConOpsndash Highest ISP low thrust but sufficient time for burnndash Low TRL
bull Cold Gas Propulsionndash Candidate solution for Secondary ConOpsndash Lowest ISP moderate thrustndash Simple
Speaker Anthony Huet
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 30
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
30 Total CubeSat Mass 10567 g
Level 2
Master Equipment List (MEL)
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 31
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
bull The volume analysis of the actual components used is displayed in the following graph
Volume Analysisbull 385 U assuming 96x96mm base using maximum volume components
Speaker Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 32
Type Product Size (mm) Height (mm)Height Contingency
(10)Total Height
(mm)
RWampC BCT XACT10 100x100x50 mm (05U) 50 5 55Sensors None (BCT XACT) None 0 0 0
Radio ISIS VHFUHF Full Duplex Transceiver9 96x90x15 mm 15 15 165
GPS SGR-05U - Space GPS Receiver14 70x46x12 mm 12 12 132
Computer ISIS On Board Computer9 96x90x124 mm 12 12 132
EPS FleXible EPS 6 x 12W BCR12 153 mm Height (1 U base area) 153 15 168
Power CubeSat Power Distribution Module12 91x905x25 mm 25 25 275
Batteries CubeSat Standalone Battery12 95885x9017x22215 mm 222 22 244
Solar Panels 6U CubeSat SIDE Solar Panel12 No size inside cubesat 0 0 0
Propulsion MPS-120XWtrade CubeSat High-Impulse Adaptable13 200x100x1135 mm 1135 1135 12485
Sub-Total Height (mm)33524
Margin Height Margin5029
Total Height (mm) Volume (U) 38553 386
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Power Equipment List (PEL) Nominal Power Usage
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Anthony Huet or Kyle Chaffin
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 33
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Power Equipment List (PEL) Desaturation Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 34
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 24673 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
14 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
15 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
16 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 370095 W30 Total Desaturation Power Usage 28374 W
Level 2
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Power Equipment List (PEL) Flyby Power Usage
Speaker Anthony Huet or Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 35
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 25223 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 45 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
20 Margin (15 of 10 378345 W30 Total Flyby Power Usage 290065 W
Level 2
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Iris Comms Link Budget
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Down Link Rates for the INSPIRE CubeSat [33]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 36
Iris Down Link Rates courtesy of JPL [34]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Cost Analysis Components of One 6U CubeSat
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 37
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Total Cubesat Cost $492798
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Cost Analysis Two 6U CubeSats and Operations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 38
WBS Element Input CER ($K FY 15) Cost Driver(s) Input Range
11 Spacecraft amp Payload $98560 K Component Cost Analysis
12 IAampT $98560 K $13700 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
30 Program Level $98560 K $22570 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
40 LOOS $98560 K $6012 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)
50 GSE $98560 K $6505 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 15)Total Cost $147346542
12 Spacecraft Integration Assembly and Test
50 Aerospace Ground Equipment
40 Flight Support
30 Program Level
11 Spacecraft amp Payload
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Riskbull Largest risk from component failure
ndash Radiation hardened componentsndash Redundant systems
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 39
Speaker Anthony Huet
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Mandatory Considerations External Issuesbull Economics Environmental and Sustainability
ndash Low total cost but likely low science return
ndash Environmental effects consistent with primary payloadbull Disposal options do not increase orbital debris issues
bull Does not add to primary mission environmental impact
bull Ethical Social and HealthSafetyndash Ethically and socially pertinent to improving propagation of near-Earth bodies
ndash Hydrazine is a health risk High TRL mitigates
bull Manufacturability Political and Global Impactndash Developed using standard high TRL bus and components Easily manufactured
ndash Flyby altitudes well over LEO small collision probability during flybys
ndash Requiresfacilitates intl cooperation of ground stationslaunch facilities
Speaker Jeffrey Alfaro
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 40
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Critical Issues
bull Reevaluate design choice based on an empirical trade study
bull Radiation exposure during heliocentric trajectories
bull Attitude capabilities for ldquoquiet flybyrdquo scenario
bull Thermal requirements
bull Tracking ability during flyby
bull Comms Link Budgetbull JPL anomaly explanations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 41
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
httpkisscaltecheduworkshopssmallsat2012bpresentationslightseypdf [accessed 02162015]
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Image References
bull lthttpsthelistlovefileswordpresscom20140326jpggt
bull lthttpdarkroombaltimoresuncomwp-contentuploads201205AFP_Getty-TOPSHOTS-US-SPACE-INDUSTRY-FALCON-9jpggt
bull lthttpspaceflightservicescomwp-contentuploads201308SHERPA_w_panels_v002pnggt
bull lthttpwwwnasagovsitesdefaultfilesthumbnailsimagedellingr_artist_conceptjpggt
bull lthttpispacecomimagesi000025089i02orion-service-module-engine-burnjpg1358369866gt
bull lthttp
wwwesaintvaresastorageimagesesa_multimediaimages200307binary_system_earth-moon10225612-2-eng-GBBinary_system_Earth-Moon
jpg
gt
bull lthttpiytimgcomviFjCKwkJfg6Ymaxresdefaultjpggt
bull lthttpsicubesatfileswordpresscom201406icubesat-org_2014_b-1-4-kupda_sauder_20140617pdfgt
bull httpinspirehepnetrecord833373plots
bull lt httpescgsfcnasagovassetsimagesTLRS-4205-09jpggt
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
accuracy is achievable [15]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Speaker Graeme Ramsey
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 18
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection xx
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Speaker Amritpreet Kang
Background | Mission Statements | Requirements | Constraints | ConOps | Baseline | Trade Studies | Design Selection 17
Range (AU)
DataRate(bps)
L101AU
Moon0026AU
X-band 1w patch antenna
Ka-band 1w deployable dish
S-band 1w deployable dish
Figure courtesy of NASA JPL [19]