11/26/08 Wed Team #4

Design of Unmanned Aircraft System(UAS)

032748 선 진 성 032776 유 태 석 032789 이 선 민 032791 이 세 동 032794 이 영 신 032821 정 우 진

Contents

Contents

1. Scenario

2. Overview

3. Requirement

4. Parametrics

5. Conclusion

1. Scenario

Korea Sejong Unv.Dr. Kyung-Tae Lee

Emergency Phone Call

USA CIA USA FAA

USA 엔지니어들이 이라크에 납치당했네 도와주게 ..

Dr. Lee

사정이 딱하니 우리 학생들이 도와드리죠

우리가 원하는 건 중고도급 정찰 및 다목적 UAV 일세 요구조건을 보여주시오

Scenario

저공 비행

가벼운 기체

뒤쳐지지 않는 성능

Requirement

Scenario

USA FAA – KOR SEJONG UNIV JOINT

Scenario

Sejong Unv.Best of Best Team

SystemSystem

WeightWeight Configuration

Configuration Sub-SysSub-Sys ElectronicElectronic Performan

cePerforman

ce

너희가 최고다 !

Scenario

▷ Start [MQ-1 Predator Development]

Aerospace Research Institute : Choong moo gwan

2 . Overview

MQ-1 Predator

Overview

Specification

Overview

1 . Synthetic Aperture Radar (SAR) Antenna 2 . Inertial Navigation System/GPS 3 . Ku-Band Satellite Communications Antenna 4 . Video Cassette Recorder 5 . GPS Antennas (Left and Right) 6 . APX-100 Identification Friend or Foe Transponder 7 . Ku-Band Satellite Communications Sensor Processor Modem Assembly 8 . C-Band Upper Omnidirectional Antenna Bracket 9 . Forward Fuel Cell Assembly 10 . Aft Fuel Cell Assembly 11 . Accessory Bay 12 . Engine Cooling Fan 13 . Oil Cooler/Radiator 14 . 914F Engine 15 . Tail Servo (Left and Right) 19 . Aft Equipment Bay Tray 20 . Secondary Control Module 21 . Synthetic Aperture Radar Processor/AGM-114 El ectronics Assembly 22 . Primary Control Module 23 . Front Bay Avionics Tray 24 . ARC-210 Receiver/Transmitter 25 . light Sensor Unit 26 . Video Encoder 27 . De-ice Controller 28 . Electro-Optical/Infrared Sensor/AN/AAS-52(V)1 Electronics Assembly 29 . Front Bay Payload Tray 30 . Ice Detector 31 . SAR)Receiver/Transmitter 32 . Nose Camera Assembly

Overview

[ 주요 특징 ] 1 . 밤낮 상관없이 고정밀 촬영 가능 2 . Hellfire missile 을 위한 레이저 표시 제공

AN/AAS-52

Multi-Spectral Targeting System

Overview

[ 주요 특징 ]

1. small volume , light weight 2. supports all-weather

3. low power

TESARTactical Endurance Synthetic Aperture Radar

Overview

TESAR SYSTEM

Overview

AGM-114 Hellfire missile

[ 주요 특징 ]

1 . 대전차 미사일 ( 대함용도 있음 )

2 . 주로 헬기에서 사용

Overview

Communication

Pre-conceptual design

3. Requirement

Requirement Ex ) Preconcept

저공비행

1 . 대부분의 지대공 missile → 3~6km → 최소 7km 이상은 되어야 하겠다 ex) 미스트랄 - 3km 스팅어 - 3.5km

2 . 일단 대류권이 좋겠다

가벼운 기체1 . 최신 복합체를 쓸 수는 없고 최대한 크기를 작게 해야겠다 . → 동시대의 UAV 비교 .

뒤쳐지지 않는 성능

1 . 최소 24 시간

2 . supports all-weather → (using TESAR 용 )

3 . 공격 능력까지 추가되면 어떨까 ?

Oh! Parametrics.. God dammit!

4 . Parametrics

Range

propulsion Weight

performance

Parametric 의 순서

Configuration

4 . Parametrics

Range

4 . Parametrics

From requirement

Range

Range 400nm=740km

Altitude 7km = 23ft

Static pressure ratio( )

0.3966

Temperature ratio( ) 0.9044

Density ratio( ) 0.4386

Pa 839.2929lb/ft^2

Block time_loiter 22hr

Block speed_loiter 33km/h

1962 U.S. Atmosphere

0.00

0.10

0.20

0.30

0.40

0.50

0.60

0.70

0.80

0.90

1.00

0 50 100

Altitude (Kft)A

mbi

ent/S

ea L

evel

Rat

io Pressure (delta)

Temperature (theta)

4 . Parametrics

Engine

4 . Parametrics

● Engine(ROTAX 914)

4 . Parametrics

Weight

4 . Parametrics

4 . Parametrics

4 . Parametrics

1 . Fuselage , wing , tail 각각의 wetted area 도출 . 2 . (Drag , lift )max 및 (L/D)max 도출 .

3 . 전체적인 항공기 형상 도출 .

Configuration

4 . Parametrics

1 . Fuselage

a . 원형 실린더 모양을 기초로 설계 시작 = > how to choice of length and span length ?

b . IC Engine 의 Vmax = 120kts => length to span ratio = 약 0.6 ~ 0.7

c . Length = 30 , span length = 48

=> length to span ratio = 0.625

L = 30 ft , D = 3ft Swet_fuselage = (3.14*(L/D))*D^2 = 282 . 7433

Length to span ratio

0.0

0.5

1.0

1.5

2.0

2.5

0 300 600 900 1200

Vmax (Kts)

SideView

L EndView

D

4 . Parametrics

2 . Wing and tails

Swet_wing = 2*(0.9*Sref) = 225

Sref = 125 => 면적을 이용하여 날개 형상 생각

1 1.6

48ft

Swet_vt = 37.5 , Swet_ht = 62.5=> 절반의 합력 계산 = > Swet_angular=36.4434*2 = 72.8869

total Swet_tail = Swet_angular+Swet_vt = 72.8869+37.5 = 110.3869

Total Swet = 282.7433+225+110.3869 = 618.1302

Cfe 0.004

e 0.8

AR 18.432

Cd.Max 0.0349

Cl.Max 0.899

(L/D)max 25.7636

(L/D) 23.1872

4 . Parametrics

wing loading = 2241.51/125 = 17.93 Waf/Sref = 4.5

TREND 에 만족 !! Wetted AR = 48^2/618.1302 = 3.727 (L/D)max = 25.7636

Regional Turboprops(airframe structure only - Roskam)

5

10

15

20

25 35 45 55

GTOW/Sref (psf)

Waf

/Sre

f (ps

f)

Maximum L/D trends

0

5

10

15

20

25

30

35

0 2 4 6 8

Wetted AR = b 2̂/Swet

(L/D

)max

Manned aircraftGlobal Hawk (est)

4 . Parametrics

3 . Model

L , D 동일 . L1 = 3 , L2 = 6

Reduce of Total Swet !!

LL1 L2

D

L , D L , D , L1 , L2

Swet of fuselage 282.7433 251.6772

Swet of wing 225 230.9946

Swet of tails 110.3869 110.3869

Total Swet 618.1302 593.0586

4 . Parametrics

4 . Engine 의 위치

Tractor 방식이 아닌 Pusher 방식 .

장점 : 표면 마찰 항력 및 wetted area 를 줄인다 .

단점 : 랜딩 기어가 길어야 함 .

5 . Inverted V-tail 선정

장점 : Roll-yaw coupling 현상 제거 단점 : 지면 여유가 적음

4 . Parametrics

6 . 전체적인 3 면도

4 . Parametrics

Performance

4 . Parametrics

Engine start and taxi : 20 min at idle power (fuel flow=0.1*WdotF0)Takeoff : 1 min at maxium power (fuel flow=WdotF0)

-Initial data

W0 Sref Bhp/W0 SFC0 Swet

2241 lb 123.3 ft^2 0.05 0.47 587.2

FF L/Dmax AR Cfe E

0.29 24 18 0.0045 0.8

Take off performance

Vto Vs W3 Prop TOP D_to BFL

58.92 kts 53.57 kts 2196.18 lb

253.51 1851.05 ft

3127 ft

4 . Parametrics

Climb 2

Vclimb2 D Ta SFC WdotF ROC TTC

149.4 fps

90.3 lb 94 lb 0.47 43.24 lb/h

10.1 fpm 2470 min

Climb 1

Vclimb1 D Ta SFC WdotF ROC TTC

99.52fps 91.5 lb 375.25 lb

0.47 52.44 lb/h

770.82 fpm

32.43 min

Average climb

Vclimb WdotF ROC TTC Dclimb

74.4 fps 47.84 lb/h 390.5 fpm 64min 78.4 nm

4 . Parametrics

Initial cruise start at 25K ft altitude

W4 Vcr

2145 lb 80 kts

Lending weight

W19

1623 lb

Total Range

RF Rcr Dcilmb R

13301 nm 1610nm 78.41 nm 1688.41nm

5 . Conclusion

FAA Sejong Univ.

Pre-conceptDesign

Iteration Data

Selecting Data

MQ-1 Predator Development

Feedback

Reference

1 . Lecture note2 . Road map3 . http://en.wikipedia.org/wiki/MQ-1_Predator4 . http://science.howstuffworks.com/predator.htm/printable5 . http://www.fas.org/irp/imint/tesar.htm6 . http://www.hansfamily.kr/438 7 . http://www.pagefarm.net/wiki/index.php?title=The_CIA's_Role_in_the_War_on_Terror#MQ-1_Predator8 . http://www.air-attack.com/videos/53/page/2#http://www.youtube.com/watchwatch?v=LTPHdLNcPUc 9 . http://www.vectorsite.net/twuav_13.html#m2    10 . http://www.americanspecialops.com/cia-special-operations/ 11 . www.dtic.mil/ndia/2005expwarfare/hastert.pdf 12 . Jane’s book13 . http://www.rotaxservice.com/rotax_engines/rotax_914UL.htm14 . http://www.fas.org/irp/program/collect/gnat-750.htm15 . http://en.wikipedia.org/wiki/General_Atomics_GNAT16 . http://science.howstuffworks.com/predator.htm/printable17 . http://www.airforce-technology.com/projects/predator/18 . http://www.air-attack.com/videos/53/RQ-1-Predator.html19 . http://kr.youtube.com/watch?v=Tirfa7Ng78s20 . http://www.zibb.com/aerospace/theme/aircraft/MQ-1+Predator+%2F+RQ-1+Predator+A21 . http://www.airforce-technology.com/projects/predator/predator6.html22 . http://www.militaryaircraft.de/pictures/military/aircraft/MQ-1/MQ-1.html23 . http://inventors.about.com/library/inventors/blRQ_1_Predator_Unmanned.htm24 . http://www.gruntsmilitary.com/rq1.shtml25 . http://www.army-technology.com/projects/predator/specs.html

Thank you

Q&A