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    Hubble Space Telescope

    Servicing Mission 4Media Reference Guide

    Special thanks to ever

    yone who helpedpull this book together

    Buddy Nelson Chief writer/editorMel Higashi Design and layoutPat Sharp Text and graphics integration

    Background information and images provided byPeter Leung, Dennis Connolly, Preston Burch, Mindy Deyarmin,Mark Jarosz, Susan Hendrix, Mike McClaire, Rob Navias,Stratis Kakadelis, Ray Villard, Dave Leckrone, Mike Weiss,

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    About the Covers

    he outside covers show the Hubble Space Telescopeilluminated in orbit by the rising sun, with a thincrescent limb of Earth as a backdrop. Astronauts are

    installing the second of two new Solar Arrays duringServicing Mission 3B in March 2002.

    Images on the inside covers and in Section 2 are stillsfrom photo-realistic NASA animations depicting theprimary activities that will take place during Servicing

    Mission 4.

    T

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    Who Was Edwin P. Hubble?

    ne of the great pioneers of modern astronomy,the American astronomer Edwin Powell Hubble(18891953) started out by getting a law degree

    and serving in World War I. However, after practicing lawfor one year, he decided to chuck law for astronomyand I knew that, even if I were second rate or third rate,it was astronomy that mattered.

    He completed a Ph.D. thesis on the PhotographicInvestigation of Faint Nebulae at the University of

    Chicago and then continued his work at Mount WilsonObservatory, studying the faint patches of luminousfog or nebulae in the night sky.

    Using the largest telescope of its day, a 2.5-meterreflector, he studied Andromeda and a number of othernebulae and proved that they were other star systems(galaxies) similar to our own Milky Way.

    He devised the classification scheme for galaxies that isstill in use today, and obtained extensive evidence thatthe laws of physics outside the galaxy are the same ason Earthin his own words: verifying the principle ofthe uniformity of nature.

    In 1929, Hubble analyzed the speeds of recession of anumber of galaxies and showed that the speed at whicha galaxy moves away from us is proportional to its dis-

    tance (Hubbles Law). This discovery of the expandinguniverse marked the birth of the Big Bang Theoryandis one of the greatest triumphs of 20th-century astronomy.

    In fact, Hubbles remarkable discovery could have beenpredicted some 10 years earlier by none other thanAlbert Einstein. In 1917, Einstein applied his newly devel-oped General Theory of Relativity to the problem of theuniverse as a whole. Einstein was very disturbed to dis-

    cover that his theory predicted that the universe couldnot be static, but had to either expand or contract.Einstein found this prediction so unbelievable that hewent back and modified his original theory in order toavoid this problem. Upon learning of Hubbles discover-ies, Einstein later referred to this as the biggest blunderof my life.

    ESA Bulletin 58

    Edwin Hubble (18891953) at the 48-inch Schmidt telescopeon Palomar Mountain

    The U.S. Postal Service honored astronomer Edwin Hubblewith a stamp in its American Scientists series, issued March 6,2008. The stamp shows the dome of the Mount WilsonObservatory where Hubble made observations that revealedthe expanding universe.

    O

    Photo courtesy of the Carnegie Institution of Washington

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    ew telescopes in history have had such a profoundimpact on astronomical research as the HubbleSpace Telescope. In its 18 years of operation,

    Hubble has not only helped shape scientists view of theuniverse, but it has also brought a glimpse of the wondersof the cosmos to homes worldwide. Here are some of itsmost riveting achievements.

    Hubble has made the first measurements of the compo-sition of the atmosphere of an extrasolar planet. It hasdetected sodium, carbon, water and even methane.These observations are a precursor to searches for thechemical signatures of life in worlds around other stars.

    In collaboration with other telescopes, Hubble hasshown that the expansion of our universe is accelerating,as if propelled by an unseen cosmic constituent dubbed

    dark energy. Hubble has also taken the first steps inthe attempt to characterize the properties of this darkenergy, in terms of its strength and permanence.

    Hubble has determined the rate of cosmic expansion(the Hubble Constant) to an accuracy of about four per-cent. The measured value indicates an age for theuniverse of 13.7 billion years. Hubble observations havealso firmed up the scenario in which giant black holes

    feasting on matter reside in the centers of most galaxies.The mass of these black holes was found to be tightlycorrelated with the mass of the spherical bulges of starssurrounding galactic centers.

    Finally, Hubble has taken long exposures of smallpatches of the skythe Hubble Deep Fieldsto obtainthe deepest images of the universe in visible light.These observations have revealed the rate of star for-

    mation at large in the universe over cosmic time.

    This magnificent telescope has allowed us to see, forthe first time, features of the universe that humans wereonce able to probe only with their imaginations.

    Dr. Mario Livio, astronomerSpace Telescope Science Institute

    A Truly Great Observatory

    F

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    C O N T E N T S

    Sect ion Page

    INTRODUCTION 1-1

    Hubble Space Telescope Configuration 1-4Optical Telescope Assembly 1-4

    Science Instruments 1-4Support Systems Module 1-8Solar Arrays 1-8Computers 1-8

    The Hubble Space Telescope Program 1-9

    The Value of Servic ing 1-10

    HST SERVICING MISSION 4 2-1

    Reasons for Orbita l Serv ic ing 2-2

    Orbita l Replacement Instruments and 2-3Orbita l Replacement Units

    Shutt le Support Equipment 2-5Remote Manipulator System 2-5

    Space Support Equipment 2-5Fl ight Support System 2-5Super L ightweight Interchangeable Carr ier 2-6Orbita l Replacement Unit Carr ier 2-7Mult i -Use L ightweight Equipment Carr ier 2-7

    Astronaut Roles and Training 2-9

    Extravehicular Crew Aids and Tools 2-10

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    Section Page

    Summary 3-14

    SCIENCE INSTRUMENTS 4-1

    Widef ie ld Camera 3 4-2Instrument Description 4-3WFC3 Optical Design 4-3Observations 4-5Selected Science Goals 4-5

    Cosmic Origins Spectrograph 4-6COS Instrument Design 4-7Observations 4-8Selected Science Goals 4-9

    Advanced Camera for Surveys 4-10Physical Description 4-10ACS Optical Design 4-11

    Fi l ter Wheels 4-12Observations 4-12

    Near Infrared Camera and Mult i -Object 4-12Spectrometer

    Instrument Description 4-12

    Observations 4-14

    Space Telescope Im aging Spectrograph 4-15Physical Description 4-16Observations 4-18

    Astrometry (Fine Guidance Sensors) 4-18Operational Modes for Astrometry 4-18Fine Guidance Sensor F i l ter Wheel 4-20A t t i Ob ti 4 20

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    Section Page

    Solar Arrays 5-24

    Science Instrument Command and Data 5-25Handl ing Unit

    Components 5-25Operation 5-27

    Space Support Equipment 5-28Orbital Replacement Unit Carr ier 5-28Crew Aids and Tools 5-29

    HST OPER ATIONS 6-1

    Space Telescope Science Inst i tute 6-2Scienti f ic Goals 6-3STScI Software 6-3Selecting Observation Proposals 6-3Schedul ing Telescope Observa tions 6-4

    Data Analys is and Storage 6-4

    Space Telescope Operations Control Center 6-4

    Operational Factors 6-5Orbital Characterist ics 6-5

    Celest ial Viewing 6-6Solar System Object Viewing 6-7Natural Radiat ion 6-7Maneuvering Characterist ics 6-7Target Acqusition 6-8Communications Characterist ics 6-9

    GLOSSARY 7-1

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    ILLUSTRATIONS

    Figure Page

    1 -1 T he H ubble S pa ce Te le sc ope ( HST ) sh ow n 1-3in a c lean room at Lockheed Mart in SpaceSystems Company in Sunnyvale, Cal i fornia ,before shipment to Kennedy Space Center

    is equipped with sc ience instruments andengineer ing subsystems des igned as Orbita lReplacement Units .

    1-2 HST overal l conf igurat ion and speci f icat ions 1-5

    1-3 HST miss ions f rom launch through de-orbi t . 1-6For each serv ic ing miss ionfrom SM1through SM4new instruments , repai rs andupgrades are l isted.

    1-4 Organizat ion summary for HST program 1-9

    operat ional phase

    1-5 HST data col lect ing network 1-10

    2-1 Hubble Space Telescope Servic in g Miss ion 4 2-4Orbita l Replacement Instruments (ORIs ) and

    Orbita l Replacement Units (ORUs)

    2-2 The telescope has 225 feet of handrai ls to 2-5increase astronaut mobil i ty and stabi l i ty .

    2-3 Servic ing Miss ion 4 payload bay 2-6

    conf igurat ion

    2-4 Fl ight Support System conf igurat ion 2-6

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    Figure Page

    2-10 Atl ant is rendez vo us wi th Hubble 2-13

    2-11 Detai led schedule of extravehicular 2-14act ivit ies dur ing SM4

    2-12 As tronaut Andrew Feus tel , r iding on the 2-15Shutt les robotic arm, m aneuvers theWide Field Camera 3 out of i ts storagecontainer for instal lat ion on Hubble.

    2-13 As tronaut Mik e Go od, on the Shutt le RMS, 2-17moves a replacement RSU into place in the-V3 aft shroud doors. Ast ronaut MikeMassimino provides visua l assistance toensure precise al ignment of the RSU onits mounting plate.

    2 -1 4 T he re fri ge ra to r- si ze d C osmic Origins 2-19

    Spectrograph is guided into place.Andrew Feustel holds the instrument asJohn Grunsfeld assesses al ignment.

    2-15 John Gruns feld caref ul ly removes the f i rst 2-19of two fai led circuit boards from the

    Advanced Camera for Surveys. New boardswil l be instal led and a power supplymodule attached to return the instrumentto operat ion.

    2-16 Af ter remov ing the ol d d egraded mult i- layer 2-21

    insulat ion from Bay 8 of the EquipmentSection on HST, Mike Good instal ls a NewOuter Blanket Layer panel .

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    Figure Page

    3-3 A ri ng- l ik e s truc tu re is ev ident in the bl ue 3-5

    map of a cluster s dark matter distr ibut ion.The map is superimposed on a Hubbleimage of the cluster.

    3-4 L ig ht ec hoes from the red sup ergiant star 3-7 V838 Monocerotis.

    3-5 The core of the spectacular globular 3-8cluster Omega Centaur i gl i t ters with thecombined l ight of 2 mil l ion stars.

    3 -6 T hi s a rt is ts i ll us tr at io n s ho ws a d ra ma ti c 3-9close-up of the scorched extrasolar planetHD 209458b in i ts orbit only 4 mil l ion milesfrom its yel low, sun- l ike star.

    3-7 Methane abs orpt i on b y the atmosp here o f 3-10

    an extrasolar planet, HD 189733b

    3-8 This color composite focuses on the 3-1126-mile-diameter (42-ki lometer-diameter)Ar istarchus impact crater and employsultraviolet- to vis ible-color-rat io information

    to accentuate differences that potent ia l lycan diagnose i lmenite-bear ing mater ia ls( i .e. , t i tanium oxide) and pyroclast ic glasses.

    3-9 Art ist s view of Eris and Dysnomia 3-12

    3 -1 0 G oi ng , g oi ng , g on e: H ub bl e cap tu re s 3-13Uranus r ings on edge.

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    Figure Page

    4 -1 1 S pa ce Te le sc op e I ma gi ng S pe ct ro gr ap h 4-15

    (STIS)

    4 -1 2 F in e G uida nc e S en sor (F GS ) 4-19

    5 -1 Hu bbl e S pa ce Te le scope ex plode d vi ew 5-2

    5-2 Hubble Space Telescope axes 5-3

    5 -3 De si gn f ea tu re s of S uppo rt S ys te ms Mo dul e 5-3

    5 -4 S tr uc tur al c om pon ent s of S uppo rt S ys tem s 5-4Module

    5-5 Aperture door and l ight shie ld 5-4

    5-6 Support Systems Module forward shel l 5-5

    5-7 Support Systems Module af t shroud 5-6and bulkhead

    5-8 Data Management Subsystem funct ional 5-8block diagram

    5-9 Advanced computer 5-8

    5 -1 0 D at a M an ag em en t U ni t c on fi gu ra ti on 5-9

    5 -1 1 L oc at io n o f P oi nt in g C on tr ol S ub sy st em 5-11equipment

    5-12 React ion Wheel Assembly 5-12

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    Figure Page

    5 -2 4 C ut aw ay v ie w o f F in e G ui da nce S en so r 5-23

    5 -2 5 S ol ar Ar ra y d et ai l c om pa ri so n 5-25

    5 -2 6 S ci en ce I ns tr um en t C on tro l a nd D at a 5-26Handling unit

    5 -2 7 C om ma nd f lo w for S ci en ce I ns tr um en t 5-27Control and Data Handling unit

    5 -2 8 F lo w o f s ci en ce da ta in th e Hu bb le 5-28Space Telescope

    6-1 Space Telescope Science Inst itute 6-2in Balt imore

    6 -2 S pa ce Te le sc op e O pe ra ti on s C on tro l C en te r 6-5at Goddard Space Fl ight Center

    6-3 Conti nuous viewing zone cel est i al vi ewing 6-6

    6-4 HST s ingle-axis maneuvers 6-8

    6-5 Sun-avoidance maneuver 6-8

    6-6 TDRS-HST contact zones 6-9

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    Introduction

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    I n t r o d u c t i o n

    azing through his first crude telescope in the 17th century,

    Galileo discovered the craters of the Moon, the satellites of Jupiter

    and the rings of Saturn. These early observations led the way to

    todays quest for in-depth knowledge and understanding of the

    cosmos. For more than 18 years, NASAs Hubble Space Telescope(HST) has continued and expanded this historic quest.

    G

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    Since its launch in April 1990, Hubble hasprovided scientific data and images ofunprecedented resolution that have gen-erated many new and exciting discoveries.Even when reduced to raw numbers, theaccomplishments of the 12.5-ton orbiting

    observatory are impressive:

    Hubble has taken about 880,000 expo-sures.

    Hubble has observed more than 29,000astronomical targets.

    Astronomers using Hubble data havepublished 7,660 scientific papers.

    Circling Earth every 96 minutes, Hubble

    has traveled approximately 2.83 billionmiles.

    The Space Telescope Science Institute(STScI) has archived more than 38terabytes of data from Hubble.

    This unique observatory operates aroundthe clock above Earths atmosphere

    gathering information for teams of scien-tists who study the origin, evolution andnature of the universe. The telescope isan invaluable tool for examining planets,stars, star-forming regions of the MilkyWay, distant galaxies and quasars, andthe tenuous hydrogen gas lying betweenthe galaxies.

    HST can produce images of the outerplanets in our solar system that approachthe clarity of those from planetary flybys.Astronomers have resolved previouslyunsuspected details of numerous star-forming regions of the Orion Nebula inthe Milky Way and have detectedexpanding gas shells blown off byexploding stars.

    Using Hubbles high-resolution and light-gathering power, scientists have cali-brated the distances to remote galaxiesto precisely measure the expansion ofthe universe and thereby calculate itsage. They have detected and measuredthe rotation of dust, gas and starstrapped in the gravitational field at the

    cores of galaxies that portend the pres-ence of massive black holes.

    Hubbles deepest views of the universe,

    additional information on the telescopesscientific discoveries.)

    The HST mission is to spend at least20 years probing the farthest and faintestreaches of the cosmos. Crucial to fulfilling

    this objective has been a series of on-orbit manned servicing missions. Duringthese missions astronauts performplanned repairs and maintenance activi-ties to restore and upgrade the observa-torys capabilities. To facilitate this process,HST designers configured science instru-ments and vital subsystem components asOrbital Replacement Instruments (ORIs)

    and Orbital Replacement Units (ORUs)modular packages with standardized fit-tings accessible to astronauts in pressur-ized suits (see Fig. 1-1).

    The First Servicing Mission (SM1) tookplace in December 1993 and the SecondServicing Mission (SM2) in February 1997.Hubbles Third Servicing Mission was

    separated into two parts: ServicingMission 3A (SM3A) flew in December1999 and Servicing Mission 3B (SM3B) inMarch 2002. Servicing Mission 4 (SM4),the fifth visit to HST, is scheduled forlaunch in May 2009.

    SM4 astronauts will: Install two new science instruments,

    the Wide Field Camera 3 (WFC3) andthe Cosmic Origins Spectrograph (COS).

    Replace the Science InstrumentCommand and Data Handling(SI C&DH) unit with a backup.

    Replace all six nickel-hydrogen (NiH2)batteries.

    Attempt to repair the AdvancedCamera for Surveys (ACS) by installing a

    box containing new circuit boards intoits Wide Field Channel Charge-CoupledDevice (CCD) Electronics Box (CEB) andattaching a power supply module.

    Attempt to repair the Space TelescopeImaging Spectrograph (STIS) by replac-ing the Low Voltage Power Supply-2(LVPS-2) board in the Main ElectronicsBox 1 (MEB1).

    Install a refurbished Fine GuidanceSensor (FGS-2).

    Install New Outer Blanket Layer(NOBL) insulation panels.

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    same time advancing its survey anddiscovery capability through a combinationof broad wavelength coverage, wide fieldof view and high sensitivity. It replaces thesecond-generation Wide Field andPlanetary Camera 2 (WFPC2).

    COS is a fourth-generation Hubbleinstrument designed to perform high-sensitivity, moderate- and low-resolutionspectroscopy of astronomical objects inthe wavelength range of 1150 to 3200angstroms. It will be installed in the baynext to ACS, where the Corrective OpticsSpace Telescope Axial Replacement

    (COSTAR) currently resides.

    The SI C&DH unit keeps all scienceinstrument systems synchronized, helpingto process, format and temporarily storeinformation on HSTs data recorders ortransmit science and engineering data tothe ground. On September 27, 2008, theSI C&DH Side-A electronics failed. The

    redundant Side B electronics werebrought online and HST resumed scienceoperations. However, the loss of redun-dancy necessitated the replacement ofthe entire SI C&DH during SM4.

    Each of the six gyroscopes is packaged asa rate sensor assembly. These assembliesare housed in pairs inside three boxes

    called Rate Sensor Units (RSU). It is the RSUthat astronauts change when they replacegyroscopes, so gyroscopes are alwaysreplaced two at a time. All three RSUs willbe changed out during SM4.

    Hubbles six NiH2 batteries reside in twomodules, each containing three batteries.They provide the observatory with a robust,

    long-life electrical energy storage system.Astronauts will replace all six batteries.

    ACS is a third-generation imaging camerainstalled on SM3B. The camera is optimizedto perform surveys or broad imagingcampaigns.

    STIS is a powerful general-purpose spec-

    trograph that is complementary to COS.The repair during SM4 aims to return thisinstrument to working order by replacinga low-voltage power supply board that

    pointing information for Hubble and atother times will function as a scientificinstrument for astrometric science.

    To maintain the normal operating temper-ature of critical HST electrical components,

    NOBL insulation panels will be installedto mitigate degradation of some ofHubbles thermal insulation.

    Installation of the SCM on Hubbles aftbulkhead will aid rendezvous and captureof the telescope on a future mission, suchas de-orbiting the observatory.

    H u b b l e S p a c eT e l e s c o p eC o n f i g u r a t i o n

    Figure 1-2 shows the overall telescopeconfiguration and specifications. Themajor elements are:

    Optical Telescope Assembly (OTA)two mirrors and associated structuresthat collect light from celestial objects

    Science instrumentsdevices used toanalyze the images produced by the OTA

    Support Systems Module (SSM)spacecraft structure that encloses theOTA and science instruments

    Solar Arrays (SA).

    Optical Telescope AssemblyThe OTA consists of two mirrors, supporttrusses and the focal plane structure. Theoptical system is a Ritchey-Chretien design,in which two special aspheric mirrors formfocused images over the largest possiblefield of view. Incoming light travels down a

    tubular baffle that absorbs stray light.The concave primary mirror94.5 inches(2.4 meters) in diametercollects thelight and converges it toward the convexsecondary mirror, which is only 12.2 inches(0.3 meters) in diameter. The secondarymirror directs the still-converging lightback toward the primary mirror andthrough a 24-inch hole in its center into

    the Focal Plane Structure, where thescience instruments are located.

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    Fig. 1-2 HST overall configuration and specifications

    Forward Shell

    Primary Mirror

    Aft Shroud

    Space Telescope

    Imaging Spectrograph

    Near Infrared Cameraand Multi-Object Spectrometer

    Cosmic Origins Spectrograph

    Wide Field Camera 3

    Advanced Camera for Surveys

    Solar Array (2)

    Fine Guidance Sensor (3)

    Aperture Door

    Secondary Mirror

    High Gain Antenna (2)

    Hubble Space Telescope (HST)

    Weight 24,500 lb (11,110 kg)Length 43.5 ft (15.9 m)

    10 ft (3.1 m) Light Shield and Forward ShellDiameter 14 ft (4.2 m) Equipment Section and Aft ShroudOptical system Ritchey-Chretien design Cassegrain telescopeFocal length 189 ft (56.7 m) folded to 21 ft (6.3 m)

    Primary mirror 94.5 in. (2.4 m) in diameterSecondary mirror 12.2 in. (0.3 m) in diameterField of view See instruments/sensorsPointing accuracy 0.007 arcsec for 24 hoursMagnitude range 5 mv to 30 mv (visual magnitude)Wavelength range 1100 to 24,000 Angular resolution 0.1 arcsec at 6328 Orbit 304 nmi (563 km), inclined 28.5 degrees from equatorOrbit time 96 minutes per orbit

    Mission 20+ years

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    have helped astronomers, astrophysicistsand cosmologists achieve a more completeunderstanding of the universe. Stunningtechnological advances have providednew capabilities, greater wavelength cov-erage, improved resolution and sensitivity,and increased productivity (see Fig. 1-3).

    Hubble has eight instrument baysfivededicated to science instruments andthree for the guidance system. Four baysare mounted radially, or perpendicular tothe main optical axis. The other four,called axial instruments, are aligned with

    the telescopes main optical axis and aremounted immediately behind the primarymirror.

    The radial instruments have remainedrelatively constant throughout the Hubblemission. One of them, the original WPFC,was replaced by WFPC2 during SM1.WFPC2 included an upgraded set of filters,

    advanced detectors and improved ultra-violet performance. But, perhaps mostimportant, it was fitted with correctivelenses that nulled the spherical aberra-tion in the HST main mirror discovered

    Hubble pictures, recording razor-sharpimages of faraway objects in relatively broadviews. Its 48 color filters have allowedscientists to study objects in a range ofwavelengths. During SM4 WFC3 willreplace WFPC2. With its expanded capa-bilities, WFC3 will build on the heritageof excellence of these remarkable cameras.

    Three FGS units have occupied the otherthree radial positions on HST sincedeployment. A re-certified FGS replacedone of the original units during SM2, andanother of the original units was replaced

    during SM3A. A third refurbished FGSwill be installed during SM4, replacingthe SM3A unit due to a light-emittingdiode degradation problem. The FGSunits are located at 90-degree intervalsaround the circumference of the telescope.

    The FGS units have two functions:(1) provide data to the spacecrafts point-

    ing system to keep HST pointed accu-rately at a target when one or more ofthe science instruments is being used toobtain data and (2) act as a scienceinstrument when not being used to

    Launch!

    SM1

    SM2

    Launch

    SM1

    SM3A

    Hubble Missions

    SM3B

    SM4 De-Orbit

    Mission

    GyrosWide Field Camera 3

    Cosmic Origins Spectrograph

    SI C&DH Unit

    Batteries

    Fine Guidance Sensor

    STIS Repair

    ACS Repair

    New Outer Blanket Layer

    Soft Capture Mechanism

    Advanced Camera

    Solar Arrays

    Power Control Unit

    NICMOS Cooling

    SystemGyros

    Advanced Computer

    Fine Guidance Sensor

    Imaging Spectrograph

    Near Infrared CameraFine Guidance Sensor

    Wide Field and Planetary Camera 2

    COSTAR

    Gyros

    Solar Arrays

    1990 1993 1997 1999 2002 2009 NET 2020

    Fig. 1-3 HST missions from launch through de-orbit. For each servicing missionfrom SM1through SM4new instruments, repairs and upgrades are listed.

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    positions of stars in its field of view.These measurements, referred to asastrometry, advance knowledge of thedistances and motions of stars. The unitchosen to be the astrometer FGS isthe one that has the best performance.

    Axial Instrument Configurationat Deployment (1990)The Faint Object Camera (FOC) tookearly advantage of the telescopes supe-rior optical resolution, capturing imagesof objects as dim as 28th magnitude.

    The Goddard High ResolutionSpectrograph (GHRS) was utilized toobtain high-resolution spectra of brighttargets in the ultraviolet for studyingatmospheric composition and dispersion,the content of the interstellar medium,star formation and binaries, and quasarsand other extragalactic objects.

    The Faint Object Spectrograph (FOS)was designed to make spectroscopicobservations of astrophysical sourcesfrom the near ultraviolet to the nearinfrared for studying galaxy formation,how supernovae could be used to testdistance formulas, and the compositionand origin of interstellar dust. FOS alsohad a polarimeter for the study of the

    polarized light from these sources.

    The High Speed Photometer (HSP) was arelatively simple but precise light meterthat measured the brightness of objectsand any variations in that brightness overtime. HSP provided astronomers anaccurate map of stellar magnitudes.

    Axial Instrument ConfigurationFollowing SM1 (1993)The Corrective Optics Space TelescopeAxial Replacement (COSTAR) wasinstalled, replacing the HSP. While not ascientific instrument, COSTAR deployeda set of optics into the region near theHST focal plane to intercept light that

    normally would be sensed by the axialinstruments, replacing it with light cor-rected for the spherical aberration in themain mirror.

    Axial Instrument ConfigurationFollowing SM2 (1997)The Space Telescope ImagingSpectrograph (STIS) was installed, replac-ing GHRS. STIS separates incoming lightinto its component wavelengths, reveal-

    ing information about the atomic com-position of the light source. It can detecta broader range of wavelengths than ispossible from Earth because there is noatmosphere to absorb certain wave-lengths. Scientists can determine thechemical composition, temperature,pressure and turbulence of the targetproducing the lightall from spectral data.

    The Near Infrared Camera and Multi-Object Spectrometer (NICMOS) wasinstalled, replacing the FOS. It providedHubble imaging capabilities in broad-,medium- and narrowband filters, broad-band imaging polarimetry, coronagraphicimaging and slitless grism spectroscopyin the wavelength range of 0.8 to 2.5

    microns. NICMOS has three adjacent butnot contiguous cameras, designed tooperate independently, each with a dedi-cated array at a different magnificationscale. In 1998 the cryogen in NICMOSwas depleted and the instrumentbecame dormant.

    The Faint Object Camera (FOC) wasdecommissioned in 1997 to better allo-cate existing resources, but remainedturned on and available to scientists untilit was replaced by ACS during SM3B.

    COSTAR was available to provide opticalcorrection for the FOC if needed.

    Axial Instrument ConfigurationFollowing SM3A (1999)STIS was operational. The FOC wasdecommissioned. NICMOS was dormant.COSTAR was available to provide opticalcorrection for the FOC if needed.

    Axial Instrument ConfigurationFollowing SM3B (2002)The Advanced Camera for Surveys (ACS)was installed, replacing the FOC. ACSi d h di ffi i f h

    i f d (1200 10 000 )

    S

    S M d l

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    near infrared (1200 to10,000 angstroms).Following an anomaly on January 27, 2007,the Wide Field and High ResolutionChannels stopped functioning, leavingonly the Solar Blind Channel available forscience observations.

    During SM4 a cartridge containing fourcircuit boards will replace the originalfour circuit boards in the Wide FieldChannel CEB. The new cartridge is wiredin a way that bypasses the failed circuitsin the two ACS main electronics boxes(MEB). The cartridge is powered by anew low-voltage power supply (LVPS)

    mounted externally on ACS and poweredfrom a tee connector to be installed atthe ACS input power connector. This willenable the Wide Field and High ResolutionChannels to be powered from the newLVPS, circumventing the failures in bothACS MEBs. The replacement is expectedto restore functionality to both inopera-tive channels.

    NICMOS. Dormant since 1998 due tocryogen depletion, this instrument wasreturned to service following the successfulinstallation during SM3B of the NICMOSCooling System (NCS).

    STIS ceased science operations onAugust 3, 2004, due to the failure of a

    power supply within the Side-2 electronics.(The Side-2 electronics had powered theinstrument since May 16, 2001, when ashort circuit knocked out the Side-1 elec-tronics.) Currently, STIS is in safe mode:the instrument and its onboard computerare switched off but the heaters are on toensure a healthy, stable thermal environ-ment. Repair of STIS will be attempted

    during SM4.

    COSTAR. The COSTAR is no longerrequired because the FOCthe finalinstrument requiring optical correctionwas removed during SM3B.

    Axial Instrument ConfigurationFollowing SM4 (2004)COS and NICMOS will be operational. IfSM4 repairs are successful, ACS and STISwill return to service

    Support Systems ModuleThe SSM encloses the aft portion of theOTA and contains all of the structures,mechanisms, communications devices,electronics and electrical power subsys-tems needed to operate the telescope.

    This module supports the Forward Shelland Light Shield and the Aperture Doorthat, when opened, admits light. Theshield connects to the forward shell onwhich the SAs and high gain antennas(HGA) are mounted. Electrical energyfrom the SAs charges the spacecraft bat-teries to power all HST systems. Four

    antennastwo high gain and two lowgainsend and receive informationbetween the telescope and the SpaceTelescope Operations Control Center(STOCC). All commanding occursthrough the low gain antennas (LGA).

    At the rear of the telescope, the AftShroud housing the science instruments

    is attached to the SSM.

    Solar ArraysThe SAs provide power to the spacecraft.They are mounted like wings on oppositesides of the telescope, on the forwardshell of the SSM. The SAs are rotated soeach wings solar cells face the sun. The

    cells absorb the suns light energy andconvert it into electrical energy to powerthe telescope and charge the spacecraftsbatteries, which are part of the ElectricalPower Subsystem (EPS). Batteries are usedwhen the telescope moves into Earthsshadow during each orbit.

    ComputersHubbles Data Management Subsystem(DMS) contains two computers: theAdvanced Computer installed duringSM3A and the Science InstrumentControl and Data Handling (SI C&DH)unit. The Advanced Computer performsonboard computations and handles dataand command transmissions between

    the telescope systems and the groundsystem. The SI C&DH unit stores andcontrols commands received by the sci-ence instruments formats science data

    T h H b b l S Offi f th A i t Di t /P

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    T h e H u b b l e S p a c eT e l e s c o p e P r o g r a m

    Hubble represents the fulfillment of a50-year dream and 25 years of dedicatedscientific effort and political vision to

    advance humankinds knowledge of theuniverse. The HST program comprises aninternational community of engineers,scientists, contractors and institutions. It ismanaged by Goddard Space Flight Centerfor the Science Mission Directorate (SMD)at NASA Headquarters. Within Goddard,the program is in the Flight ProjectsDirectorate under the supervision of the

    associate director/program manager forHST. It is organized as two flight projects:(1) the HST Operations Project and (2) theHST Development Project.

    Responsibilities for scientific oversight ofHST are divided among the members ofthe Project Science Office (PSO). ThePSO is designed to interact effectivelyand efficiently with the HST Program andthe wide range of external organizationsinvolved with Hubble. The HST seniorscientist and supporting staff work in the

    Office of the Associate Director/ProgramManager for HST. This group is con-cerned with the highest level of scientificmanagement for the project.

    Figure 1-4 summarizes the major organi-

    zations that oversee the program. Theroles of NASA centers and contractors foron-orbit servicing of the HST are: Goddard Space Flight Center

    (GSFC)Overall management of dailyon-orbit operations of HST and thedevelopment, integration and test ofreplacement hardware, space supportequipment, and crew aids and tools

    Johnson Space Center (JSC)Overallservicing mission management, flightcrew training, and crew aids and tools

    Kennedy Space Center (KSC)Overallmanagement of launch and post-landing operations for mission hardware

    Ball AerospaceDesign, developmentand provision of axial science instruments

    Jet Propulsion Laboratory (JPL)

    Design, development and provision ofWFPC1 and WFPC2 Lockheed MartinPersonnel support

    for GSFC to accomplish (1) develop-ment, integration and test of replace-

    Organization Function

    NASA Headquarters Overall responsibility for the programSpace and Science Mission DirectorateAstrophysics Division

    Goddard Space Flight Center Overall HST program management Office of the Associate Director/ HST project management

    Program Manager for HST Responsible for overseeing all HST HST Operations Project operations HST Development Project HST Flight Systems and Responsible for implementing HST

    Servicing Project Servicing Program Manages development of new HST

    spacecraft hardware and science instruments Manages HST Servicing Payload Integration

    and Test Program Primary interface with the Space Shuttle

    Program at Johnson Space Center

    Space Telescope Operations Provides minute-to-minute spacecraft controlControl Center at GSFC Schedules, plans and supports all science

    operations when required Monitors telemetry communications data to

    the HST

    S T l S i I tit t S l t b i f

    ment hardware and space support The HST program requires a complex

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    ment hardware and space supportequipment; (2) system integration withthe Space Transportation System (STS);(3) launch and post-landing operationsand (4) daily HST operations

    Association of Universities for

    Research in Astronomy (AURA)Responsible for the operation of theSpace Telescope Science Institute(STScI), which oversees science opera-tions for GSFC.

    Major subcontractors for SM4 includeAnalex, Alliant Techsystems (ATK),Computer Sciences Corporation, Eagle

    Pitchard Industries, FMW CompositeSystems, Goodrich Corporation,Honeywell, Jackson and Tull, L-3Communications, Mantech, OrbitalSciences Corporation, Stinger GhaffarianTechnologies, Inc. (SGT) and Swales.

    The HST program requires a complexnetwork of communications amongGSFC, the telescope, space telescopeground system and STScI. Figure 1-5shows communication links.

    T h e V a l u eo f S e r v i c i n g

    Hubbles visionary modular design hasallowed NASA to equip it with new,state-of-the-art instruments every fewyears. These servicing missions have

    enhanced the telescopes science capa-bilities, leading to fascinating new dis-coveries about the universe. Periodicservice calls have also permitted astro-nauts to tune up the telescope andreplace limited-life components.

    Fig. 1-5 HST data-collecting network

    Space Telescope

    Science Institute

    Baltimore, Md.Ground Station

    White Sands, N.M.

    Hubble Space

    Telescope

    Tracking and

    Data Relay Satellite

    Light

    Data

    Data

    Data

    Goddard Space

    Flight CenterGreenbelt, Md.

    K7444_104

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    HSTServicingMission4

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    Hubb le Space Te le scopeS e r v i c i n g M i s s i o n 4

    he Hubble Space Telescope (HST) is the first observatory designed

    for extensive maintenance and refurbishment in orbit. Its

    science instruments and many other components were planned as

    orbital replacement units (ORU)modular in construction with

    standardized fittings and accessible to astronauts. Handrails, footrestraints and other built-in features help astronauts perform servicing

    tasks in the shuttle cargo bay as they orbit Earth at nearly 17 000 mph

    T

    NASA plans to launch HST Servicing and HST Servicing Mission (SM3B) in

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    p gMission 4 (SM4), the fifth Hubble visit, inMay 2009. Originally scheduled for 2004,SM4 was postponed after the ColumbiaSpace Shuttle tragedy in 2003 becauseof NASAs safety concerns. But following

    the successful recovery of the Shuttleprogram and a thorough re-examinationof SM4 risks, the agency approved themission to Hubble.

    During HST Servicing Mission 3B, flownin March 2002, accomplishments includedreplacement of both European SpaceAgency (ESA) flexible solar arrays with

    rigid solar arrays (SA3) and the associateddiode box assemblies (DBA-2). A newscience instrument, the AdvancedCamera for Surveys (ACS), was installed.The power control unit (PCU) and reactionwheel assembly (RWA) were replaced.The Electronics Support Module (ESM)was installed. The Near Infrared Cameraand Multi-Object Spectrometer (NICMOS)

    was retrofitted with a new cooling system,returning the dormant instrument toservice. New Outer Blanket Layer (NOBL)insulation was placed over Bay 6.

    SM4 is manifested as STS-125 aboard theSpace Shuttle Atlantis (OV-104) and willbe launched to a rendezvous altitude ofapproximately 304 nautical miles. During

    the planned 11-day mission, the Shuttlewill rendezvous with, capture and berththe HST to the Flight Support System(FSS). Following servicing, the Shuttle willunberth Hubble and redeploy it to itsmission orbit.

    Five extravehicular (EVA) days are scheduledduring the SM4 mission. Atlantis cargo

    bay is equipped with several devices tohelp the astronauts: The FSS will berth and rotate the

    telescope. Large, specially designed equipment

    containers will house the ORUs. Astronauts will work and be maneu-

    vered as needed from the Shuttlerobot arm.

    SM4 will benefit from lessons learnedon NASAs previous on-orbit servicingmissions: the Solar Maximum repair

    g2002, which was actually the fourth visitto Hubble. NASA has incorporated theselessons in detailed planning and trainingsessions for Atlantis crewmembers:Commander Capt. USN, ret., Scott D.

    Altman, pilot Capt. Gregory C. Johnsonand mission specialists USNRC K. MeaganMcArthur, John M. Grunsfeld, Col. USAFAndrew J. Feustel, Michael J. Massiminoand Michael Good.

    R e a s o n s f o r O r b i t a l

    S e r v i c i n gHST is a national asset and an invaluableinternational scientific resource that hasrevolutionized modern astronomy. Toachieve its full potential, the telescopewill continue to conduct extensive, inte-grated scientific observations, includingfollow-up work on its many discoveries.

    Although the telescope has numerousredundant parts and safemode systems,such a complex spacecraft cannot bedesigned with sufficient backups to handleevery contingency during a missionlasting more than 20 years. Orbital serv-icing is the key to keeping Hubble inoperating condition. NASAs orbital serv-

    icing plans address three primary mainte-nance scenarios: Incorporating technological advances

    into the science instruments andORUs

    Normal degradation of components Random equipment failure or

    malfunction.

    Technological Advances. Throughout thetelescopes life, scientists and engineershave upgraded its science instrumentsand spacecraft systems. For example,when Hubble was launched in 1990, itwas equipped with the Goddard HighResolution Spectrograph and the FaintObject Spectrograph. A second-generationinstrument, the Space Telescope Imaging

    Spectrograph (STIS), took over the func-tion of those two instrumentsaddingconsiderable new capabilitieswhen itwas installed during SM2. A slot was then

    solid-state recorder (SSR) replaced an O r b i t a l R e p l a c e m e n t

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    Engineering/Science Tape Recorder(E/STR). During SM3A the original DF-224computer was replaced with a faster,more powerful advanced computerbased on the Intel 80486 microchip.

    Similarly, the ACS with most sensitiveimages at visible and near-infrared wave-lengths was installed during the 2002visit to Hubble.

    Component Degradation. Servicingplans take into account the need for rou-tine replacements, for example, restoringHST system redundancy and limited-life

    items such as spacecraft thermal insula-tion and gyroscopes.

    Equipment Failure. Given the enormousscientific potential of the telescopeand the investment in designing,developing, building and putting it intoorbitNASA must be able to correctunforeseen problems that arise from ran-

    dom equipment failures or malfunctions.The Space Shuttle Program provides aproven system for transporting astronautsfully trained for on-orbit servicing of thetelescope.

    Originally, planners considered using theShuttle to return the telescope to Earthapproximately every five years for main-

    tenance. However, the idea was rejectedfor both technical and economic reasons.Returning Hubble to Earth would entail asignificantly higher risk of contaminatingor damaging delicate components.Ground servicing would require anexpensive clean room and support facili-ties, including a large engineering staff,and the telescope would be out of action

    for a year or morea long time to sus-pend scientific observations.

    Shuttle astronauts can accomplish mostmaintenance and refurbishment within an11-day on-orbit mission with only a briefinterruption to scientific operations andwithout the additional facilities and staffneeded for ground servicing.

    pInst ruments and Orbi ta lR e p l a c e m e n t U n i t s

    Advantages of ORIs and ORUs include

    modularity, standardization and accessibility.

    Modularity. Engineers studied varioustechnical and human factors criteria tosimplify telescope maintenance.Considering the limited time availablefor repairs and the astronauts limitedvisibility, mobility and dexterity in theEVA environment, designers simplified

    the maintenance tasks by planning entirecomponents for replacement.

    ORUs are self-contained boxes installed andremoved using fasteners and connectors.They range from small fuses to phone-booth-sized science instruments weighingmore than 700 pounds (318 kg). Figure 2-1shows the ORIs and ORUs for SM4.

    Standardization. Standardized bolts andconnectors also simplify on-orbit repairs.Captive bolts with 7/16-inch, double-height hex (hexagonal) heads hold manyORU components in place. To remove orinstall the bolts, astronauts need only a7/16-inch socket fitted to a power tool ormanual wrench. Some ORUs do not contain

    these fasteners. When the maintenancephilosophy changed from Earth-return toon-orbit servicing, other componentswere selected as replaceable units aftertheir design had matured. This addeda greater variety of fasteners to theservicing requirements, including non-captive 5/16-inch hex head bolts andconnectors without wing tabs. Despite

    these exceptions, the high level of stan-dardization among units reduces thenumber of tools needed for the servicingmission and simplifies astronaut training.

    Accessibility. To be serviced in space,Hubble components must be seen andreached by an astronaut in a bulky pres-sure suit, or they must be within range of

    an appropriate tool. Therefore, mostORUs are mounted in equipment baysaround the perimeter of the spacecraft.To access these units, astronauts simply

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    Fig.2-1HubbleSpaceTelescopeServicingMission4

    OrbitalReplacementInstruments(ORIs)andOrbitalReplacementUnits(ORUs)

    K7444_2

    01

    CosmicOrig

    insSpectrograph(COS)

    IntoAftShroud

    ThreeRateSensorUnits(RSU)

    IntoAftShroud

    AdvancedCamerafor

    Surveys(ACS)repair

    InAftShroud

    ScienceInstrument

    ControlandData

    Handling(SIC&DH)unit

    IntoBay10

    WideFieldCamera3(WFC3)

    IntoAftShroudRadialBay

    Sixbatteries

    IntoBays2and3

    SpaceTelescopeImaging

    Spectrograph

    (STIS)repair

    InAftShroud

    New

    OuterBlanket

    L

    ayer(NOBL)

    insulation

    O

    ntoBays5and8

    Handrails, foot restraintsockets tether attach

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    sockets, tether attach-ments and other crewaids are essential tosafe, efficient on-orbitservicing. In anticipa-

    tion of such missions,31 foot-restraint socketsand 225 feet ofhandrails weredesigned into the tele-scope (see Fig. 2-2).Foot-restraint socketsand handrails greatlyincrease astronaut

    mobility and stability,affording them safeworksites convenientlylocated near ORUs.

    Crew aids such as portable lights, specialtools, installation guiderails, handholdsand portable foot restraints (PFR) alsoease servicing of Hubble components.

    Additionally, foot restraints, translationaids and handrails are built into variousequipment and instrument carriers spe-cific to each servicing mission.

    S h u t t l e S u p p o r tE q u i p m e n t

    To assist astronauts in servicing the tele-scope, Atlantis will carry into orbit justover 11 tons of hardware consisting ofthe Space Support Equipment (SSE), newinstruments, replacement hardware andcrew aids and tools (CATS). The SSEcomprises the FSS, Super LightweightInterchangeable Carrier (SLIC), Orbital

    Replacement Unit Carrier (ORUC) andMulti-Use Lightweight Equipment (MULE)Carrier.

    Remote Manipulator SystemThe Atlantis Remote Manipulator System(RMS), more commonly known as therobotic arm, will be used extensivelyduring SM4. The astronaut operating this

    device from inside the cabin is designatedthe intra-vehicular activity (IVA) crew-member. The RMS will be used to: Capture, berth and release the telescope

    Space Support EquipmentGround crews will install four majorassemblies essential for SM4 in theAtlantis payload baythe FSS, SLIC,

    ORUC and MULE (see Fig. 2-3).

    Flight Support SystemThe FSS is a maintenance platform usedto berth the HST in the payload bay afterthe Atlantis crew has rendezvoused withand captured the telescope (see Fig. 2-4).The platform was adapted from the FSSfirst used during the Solar Maximum

    repair mission and was converted to usewith HST. It has a U-shaped cradle thatspans the rear of the bay. A circularberthing ring with three latches securesthe telescope to the cradle. The berth-ing ring can rotate Hubble almost360 degrees (176 degrees clockwise orcounterclockwise from its null position)to give EVA astronauts access to every

    side of the telescope.

    The FSS also has the capability to pivotthe telescope, if required for servicing orreboosting. The FSSs umbilical cableprovides power from Atlantis to maintainthermal control of the telescope duringthe servicing mission.

    On SM4 the FSS also carries a SoftCapture Mechanism (SCM) on itsberthing and positioning system plat-form. When attached to the HST aft bulk-

    Fig. 2-2 The telescope has 225 feet of handrails to increase

    astronaut mobility and stability.

    K7444_202

    Wide Field Camera 3

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    Fig. 2-3 Servicing Mission 4 payload bay configuration

    Cosmic Origins

    Spectrograph

    Multi-use Lightweight

    Equipment Carrier

    Flight Support System

    Orbital Replacement

    Unit Carrier

    Super Lightweight

    InterchangeableCarrier

    Soft Capture

    Mechanism

    Science Instrument Control and

    Data Handling (SI C&DH) Unit

    Fine Guidance Sensor

    Wide Field Camera 3

    Batteries

    Rate Sensor Units

    K7444_203

    Fig. 2-4 Flight Support System configuration

    Contingency

    L-HandleStowage

    Portable Foot Restraint (PFR)

    Soft Capture Mechanism (SCM)Berthing and Positioning

    System (BAPS)

    90-Degree

    PFR Socket

    Converter

    BAPS Support PostK7444_204

    Super LightweightInterchangeable CarrierThe SLIC is located in Atlantis forwardpayload bay (see Fig. 2-5). It has provi-

    battery modules. The SLIC also includesa spare wide-field handhold, one spareFine Guidance Sensor (FGS) handhold,spare power distribution unit (PDU) fuse

    WFC3 Scientific

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    SLICAft View

    Telescope Axial Replacement (COSTAR)cross strap. Returning from orbit post-servicing, the SLIC will also carry homethe Wide Field and Planetary Camera 2(WFPC2) and the two original NiH2 batterymodules.

    Orbital Replacement Unit CarrierThe ORUC is centered in Atlantis pay-

    load bay. It provides safe transport ofinstruments and ORUs to and from orbit(see Fig. 2-6). In the SM4 configuration: The Cosmic Origins Spectrograph

    (COS) is stored in the Axial ScientificInstrument Protective Enclosure (ASIPE).

    The FGS is stored in the RadialScientific Instrument ProtectiveEnclosure (FSIPE).

    Three Rate Sensor Units (RSU) arestored on the starboard side SmallORU Protective Enclosure (SOPE).

    The ORUC houses other hardware,including the handholds for the FGSand the WFPC that are stored on theport side forward fixture, an aft fix-ture, a scientific instrument safety bar,a multi-layer insulation (MLI) repairtool, two STS PFRs and an extender,two translation aids (TA) and a STISMain Electronics Box (MEB) replace-

    t It l i t ili

    house miscellaneous CATS for theSTIS and ACS repair work, and eightaft shroud latch repair kits.

    Some of the protective enclosurescontrol the temperature of the newORUs via heaters and thermal insulation,providing a controlled environment thatkeeps the hardware within normal oper-

    ating temperatures. The ASIPE enclosureis isolated from the pallet to protectscience instruments from loads generatedat liftoff and during Earth return.

    Multi-Use LightweightEquipment CarrierThe MULE is located in Atlantis aft pay-load bay (see Fig. 2-7). It has provisionsfor safe transport of ORUs to orbit: The Contingency ORU Protective

    Enclosure (COPE) contains spareORUs and tools.

    The MULE Integrated NOBLContainer (MINC) contains the newNOBL protective coverings to beinstalled on the telescopes SupportSystems Module Equipment Section(SSM-ES) bay doors.

    The MULE also carries three LatchOver Center Kits (LOCKs) and low gain

    t t ti (LGAPC)

    Instrument Protective

    Enclosure (WSIPE)

    Battery Plate Assemblies

    (BPA) with Battery Module

    Assemblies (BMA)

    COSTAR V-Harness

    Stowage Pouch

    Battery Cooling System

    (BCS) DuetingSpare Fuse Plug Bracket

    FGS Handhold

    Stowage Assembly

    K7444_205A

    Fig. 2-5 Super Lightweight Interchangeable Carrier (SLIC) configuration

    Small ORU Protective

    Enclosure (SOPE)Wid Fi ld d

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    K7444_206

    K7444_207A

    Fig. 2-6 Orbital Replacement Unit Carrier (ORUC) configuration

    MULEAft View

    Flexible Multiplexer

    Demultiplexers (FMDMs)

    Contingency ORU Protective

    Enclosure (COPE)

    Power Distribution and

    Switching Unit (PDSU)

    MULE Integrated

    NOBL Container (MINC)

    Cameras (3) with

    Interface Plate/

    Flexures/Tilt Plates

    Navigator

    GPS Receiver

    Global Positioning System (GPS)

    Antennas with Mount Plate

    Science Instrument Control and

    Data Handling (SI C&DH) Unit

    Space Cube

    Integrated Control

    Electronics (ICE)

    Low Gain AntennaProtective Cover (LGAPC)

    Main Electronics Box (MEB-R)

    Cover Stowage

    Center Translation Aid (TA)FGS Handhold

    Aft Fixture

    Power Regulator

    Junction Box (PRJU)

    Forward Fixture

    Translation Aid (TA) New ORU Protective

    Enclosure (NOPE)

    Axial Scientific

    Instrument Protective

    Enclosure (ASIPE)

    Enclosure (SOPE)

    Auxiliary Transport

    Module (ATM-2)

    Load Isolation

    System (LIS)

    Wide Field and

    Planetary Camera

    (WFPC) Handhold

    A s t r o n a u t R o l e sa n d T r a i n i n g

    McArthur trained specifically for captureand redeployment of the telescope,

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    a n d T r a i n i n g

    To prepare for SM4, the seven-memberAtlantis crew trained extensively at NASAs

    Johnson Space Center (JSC) in Houston,Texas, and Goddard Space Flight Center(GSFC) in Greenbelt, Md.

    Although there has been extensive crosstraining, each crewmember also hastrained for specific tasks. Training forMission Commander Scott Altman andPilot Gregory Johnson focused on ren-

    dezvous and proximity operations, suchas retrieval and deployment of the tele-scope. The two astronauts rehearsedthese operations using JSCs ShuttleMission Simulator, a computer-supportedtraining system. In addition, theyreceived IVA training: helping the EVAastronauts into suits and monitoring theiractivities outside the Atlantis cabin.

    The five mission specialists receivedspecific training, starting with classroominstruction on the various ORUs, tools andcrew aids, SSE such as the RMS (roboticarm) and the FSS. Principal operator ofthe robotic arm is Mission SpecialistMegan McArthur, who also performsintra-vehicular activities. The alternate

    RMS operator is Commander Altman.

    yrotating and pivoting the telescope onthe FSS and handling related contingen-cies. These operations were simulatedusing JSCs Manipulator Development

    Facility, which includes a mockup of therobotic arm and a suspended helium bal-loon with dimensions and grapple fix-tures similar to those on the telescope.Other RMS training took place at JSCsNeutral Buoyancy Laboratory (NBL),enabling the RMS operator and alter-nates to work with individual team mem-bers. For hands-on HST servicing, EVA

    crewmembers work in teams of two inthe cargo bay. Astronauts John Grunsfeld,Andrew Feustel, Michael Good andMichael Massimino logged many days oftraining for this important role in theNBL, a 40-foot-deep (12-m), 6.2-million-gallon water tank (see Fig. 2-8).

    In the NBL pressure-suited astronauts

    and their equipment are made neutrallybuoyant, a condition that simulatesweightlessness. Underwater mockups ofthe telescope, FSS, SLIC, ORUC, MULE,RMS and the Shuttle payload bayenabled the astronauts to practice theentire SM4 EVA servicing. This traininghelps them efficiently use the limitednumber of days (five) and duration (six

    hours) of each EVA period.

    Other training aids at JSC helped recreateorbital conditions for the Atlantis crew.

    their reach. Multi-setting torque limitersprevent over-tightening of fasteners or

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    In the weightlessness of space, the tiniestmovement can set instruments weighingseveral hundred pounds, such as theCOS, into motion. Astronauts used virtual

    reality technologies to practice handlinglarge masses in space, such as nudginginstruments into their proper locations.This kind of ultra-realistic simulationenabled the astronauts to see them-selves next to the telescope as theirpartners maneuvered them into positionwith the robotic arm.

    A WFC3 and an FGS 1-G simulator werebuilt for the crews to practice guiderailalignment and mass handling techniques.A STIS simulator enabled crewmembersto practice removal of the 111 fastenerson the STIS covers with flight-like tools.

    E x t r a v e h i c u l a r C r e w

    A i d s a n d T o o l s

    Astronauts servicing HST use three differ-ent kinds of foot restraints to counteractthe weightless environment. Whenanchored in a manipulator foot restraint(MFR), an astronaut can be transportedfrom one worksite to the next with theRMS. Using either the STS or HST PFR,an astronaut establishes a stable worksiteby mounting the restraint to any of30 receptacles placed strategicallyaround the telescope or 17 receptacleson the SLIC, ORUC, FSS and MULE.

    In addition to foot restraints, EVA astro-nauts have more than 150 CATS at their

    disposal. Some of these are standarditems from the Shuttles toolbox whileothers are unique to SM4. All tools aredesigned for use in a weightless environ-ment by astronauts wearing pressurizedgloves.

    The most commonly used ORU fastenersare those with 7/16-inch, double-height

    hex heads. These bolts are used withthree different kinds of fittings: J-hooks,captive fasteners and keyhole fasteners.To replace a unit, astronauts use a 7/16-

    latch systems.

    For units with bolts or screws that are notcaptive in the ORU frame, astronauts use

    tools fitted with socket capture fittings andspecially designed capture tools so thatnothing floats away in the weightless spaceenvironment. To grip fasteners in hard-to-reach areas, they can use wobble sockets.

    Some ORU electrical connectors requirespecial devices, such as a connector toolto loosen circular connectors. If connectorshave no wing tabs, astronauts use aspecial tool to get a firm hold on theconnectors rotating ring.

    Portable handles have been attached tomany larger ORUs to facilitate removal orinstallation. Other tools and crew aidsinclude tool caddies (carrying aids), tethers,

    transfer bags and a protective cover forthe low gain antenna (LGA).

    When working within the telescopes aftshroud area, astronauts must guardagainst optics contamination by usingspecial tools that will not outgas or shedparticulate matter. All tools are certifiedto meet this requirement.

    A s t r o n a u t s o f S e r v i c i n g M i s s i o n 4

    NASA carefully selected and trained theSM4 STS-125 crew (see Fig. 2-9). Theirunique set of experiences and capabili-ties makes them ideally qualified for this

    challenging assignment. Brief biographiesof the astronauts follow.

    Scott D. Altman, NASA Astronaut(Commander, USN)Scott Altman of Pekin, Ill., is commanderof SM4. He received a Bachelor ofScience degree in aeronautical andastronautical engineering from theUniversity of Illinois in 1981 and a Masterof Science degree in aeronautical engi-neering from the Naval PostgraduateS h l l h l d

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    He was the pilot on STS-90 in 1998, a16-day Spacelab flight, and on STS-106

    John M. Grunsfeld, Ph.D.,NASA Astronaut

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    in 2000, a 12-day mission to prepare theInternational Space Station for the arrivalof its first permanent crew. He was thecommander of STS-109, the most recent

    Hubble Servicing Mission (SM3B) in 2002.Altman is also an experienced RMS oper-ator. He was one of two operators of therobotic arm transporting the EVA crewduring the STS-106 space walk. Heserved as the alternate RMS operator forSM3B and will serve again as the alter-nate RMS operator for SM4. STS-125 willbe his second trip to Hubble.

    Gregory C. Johnson,NASA Astronaut (Captain, USNRC)Gregory Johnson, the Atlantis pilot onSM4, is from Seattle, Wash. He receiveda Bachelor of Science degree in aero-space engineering from the University ofWashington in 1977. He received his

    naval aviator wings in 1978, graduatedfrom the U.S. Air Force Test Pilot Schoolat Edwards AFB, Calif., in 1984 and didflight tests in A6E and F/A 18A aircraft.Johnson became a NASA research pilotat JSC in April 1990. He has served asthe commanding officer of four NavalReserve units and currently is assigned assenior research officer in the Office of

    Naval Research 113, based at the NavalPostgraduate School in Monterey, Calif.He has logged over 9000 hours in50 aircraft and over 500 carrier landings.Johnson was selected as an astronautcandidate by NASA in 1998 and, havingcompleted two years of training andevaluation, has qualified for flight assign-ment as a pilot on STS-125.

    K. Megan McArthur, Ph.D.,NASA AstronautMegan McArthur, the RMS operator onSM4, is from Honolulu, Hawaii, but con-siders California to be her home state.McArthur received a Bachelor of Sciencedegree in aerospace engineering from theUniversity of California at Los Angeles in

    1993 and a Doctorate in Oceanographyfrom the University of California at SanDiego in 2002. McArthur was selected as

    t t did t b NASA i 2000

    NASA AstronautJohn Grunsfeld is an astronomer and anEVA crewmember (EV1 on EVA days 1, 3and 5) on the SM4 mission. He was born inChicago, Ill. Grunsfeld received a Bachelor

    of Science degree in physics from theMassachusetts Institute of Technology in1980 and a Master of Science degreeand a Doctor of Philosophy degree inphysics from the University of Chicago in1984 and 1988, respectively. Grunsfeldreported to JSC in 1992 for a year oftraining and became qualified for flightselection as a mission specialist. He has

    logged over 835 hours in space. On hisfirst mission, STS-67 in 1995, Grunsfeldand the crew conducted observations tostudy the far-ultraviolet spectra of faintastronomical objects and the polarizationof ultraviolet light coming from hot starsand distant galaxies. Grunsfeld flew onSTS-81 in 1991 on the fifth mission todock with Russias Mir Space Station andthe second to exchange U.S. astronauts.STS-125 will be his third trip to serviceHubble. He was aboard STS-103 in 1999,performing two space walks duringSM3A, and aboard STS-109 in 2002, per-forming three space walks during SM3B.

    Andrew J. Feustel, Ph.D.,

    NASA AstronautAndrew Feustel is an EVA crewmember(EV2 on EVA days 1, 3 and 5) on SM4. Hewas born in Lake Orion, Mich. Feustelreceived a Bachelor of Science degree insolid earth sciences and a Master ofScience degree in geophysics, both fromPurdue University, as well as a Doctoratein geological sciences specializing in

    seismology from Queens University,Kingston, Ontario, Canada, in 1995.Feustel reported to JSC in 2000 and,having completed two years of trainingand evaluation, is qualified for flightassignment as a mission specialist onSTS-125.

    Michael J. Massimino, Ph.D.,NASA AstronautMik M i i i EVA b

    stealth bomber. His last duty was servedas operations officer and F-15 test weaponsystems officer He has logged over 2100

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    Mike Massimino is an EVA crewmember(EV1 on EVA days 2 and 4) on the SM4mission. His hometown is FranklinSquare, N.Y. He received a Bachelor of

    Science degree in industrial engineeringwith honors in 1984 from ColumbiaUniversity. He also received Master ofScience degrees in mechanical engineer-ing and in technology and policy, and amechanical engineering degree and adoctorate in mechanical engineeringfrom the Massachusetts Institute ofTechnology in 1988, 1990 and 1992,

    respectively. Massimino flew as a missionspecialist aboard STS-109 in 2002, per-forming two space walks to serviceHubble during SM3B. STS-125 will beMassiminos second space flight, wherehe will perform two more space walks toservice the telescope.

    Michael T. Good,

    NASA Astronaut (Colonel, USAF)Michael Good is an EVA crewmember(EV2 on EVA days 2 and 4) on SM4. Hewas born in Parma, Ohio, but considersBroadview Heights, Ohio, to be hishometown. Good received a Bachelor ofScience degree and a Master of Sciencedegree in aerospace engineering fromthe University of Notre Dame in 1984 and1986, respectively. He received his aviatorwings in 1989, graduated from the U.S.Air Force Test Pilot School at EdwardsAFB in 1994 and flew and tested the B-2

    systems officer. He has logged over 2100hours in more than 30 different types ofaircraft. Good was selected as an astro-naut candidate by NASA in 2000 and,

    having completed two years of trainingand evaluation, is qualified for flightassignment as a mission specialist onSTS-125.

    S e r v i c i n g M i s s i o nA c t i v i t i e s

    After berthing the telescope on FlightDay 3 of SM4, the seven-person Atlantiscrew will begin an ambitious servicingmission. Five days of EVA tasks arescheduled. Each EVA session is scheduledfor six hours.

    Rendezvous with HubbleAtlantis will rendezvous with Hubble in

    orbit 304 nautical miles (563 km) aboveEarth (see Fig. 2-10). Prior to approach,in concert with the Space TelescopeOperations Control Center (STOCC) atGSFC, Mission Control at JSC willcommand HST to stow the high gainantennas (HGA) and close the aperturedoor. As Atlantis approaches the tele-scope, Commander Altman will controlthe thrusters to avoid contaminating HSTwith propulsion residue. During theapproach the Shuttle crew will remain inclose contact with Mission Control.

    As the distance between Atlantis andHST decreases to approximately 200 feet(60 m) the STOCC ground crew will

    During EVAs HST will be vertical relativeto Atlantis cargo bay. Four EVA missionspecialists will work in two-person teams

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    (60 m), the STOCC ground crew willcommand the telescope to perform afinal roll maneuver to position itself forgrappling. The Solar Arrays (SA) will

    remain fully deployed parallel toHubbles optical axis.

    When Atlantis and HST achieve theproper position, Mission SpecialistMcArthur will operate the robotic arm tograpple the telescope. Using a cameramounted at the berthing ring of the FSSplatform in the cargo bay, she will

    maneuver the telescope to the FSS,where it will be berthed and latched.

    Once the telescope is secured, the crewwill remotely engage the electrical umbil-ical and switch Hubble from internalpower to external power from Atlantis.Pilot Johnson will then maneuver theShuttle so that the HST SAs face the sun,

    recharging the telescopes six onboardNiH2 batteries.

    Extravehicular Servicing ActivitiesDay by DayFigure 2-11 shows the schedule for fiveplanned six-hour EVA sessions. Eachservicing period shown is a planningestimate; the schedule will be modified

    as needed as the mission progresses.

    specialists will work in two person teamson alternate days. One team, Grunsfeldand Feustel, will conduct the first, thirdand fifth spacewalks and the other team,

    Good and Massimino, will conduct thesecond and fourth spacewalks.

    One astronaut, designated EV1, accom-plishes primarily the free-floating por-tions of the EVA tasks. He can operatefrom a PFR or while free floating. Theother astronaut, EV2, works primarilyfrom an MFR mounted on Atlantis

    robotic arm (RMS), removing andinstalling the ORUs on Hubble. EV1assists EV2 in removal of the ORUs andinstallation of the replaced units in theSM4 carriers. Inside Atlantis aft flightdeck, other crewmembers assist the EVAteam by reading out procedures andoperating the RMS.

    EVA Day 1: Install Wide FieldCamera 3 and replace ScienceInstrument Control and DataHandling (SI C&DH) Unit.During EVA Day 1 (the fourth day of themission), the first team of EVA astronauts,John Grunsfeld and Andrew Feustel, willperform initial setup activities, the plannedDay 1 HST servicing activities and some

    get-ahead tasks for the remaining EVAs.

    Goddard Space Flight Center

    HST SM4 EVA Timeline

    Notes1. At the end of ACS Part 1, two cards have been

    removed.

    2. Aft shroud door open/close for V2 doors is shorter

    than for the other doors due to LOCKs installation.

    3. ACS Part 2 is not shown in the timeline becauseFGS 2 is a higher priority than one of the SI repairs.

    The ACS Part 1 task is scheduled in support of

    preparing the telescope for completion of the ACS

    repair task (ACS Part 2) on EVA 5 if the STIS repair

    is not successful. In that case, FGS would be

    deleted from EVA 5 and replaced with ACS Part 2.

    4. If ACS Part 2 is added into EVA 5 (replacing FGS),

    the total task duration for that block would be 2:15,

    and the task would be performed after the Bay 3

    battery installation. The entire EVA would be

    executed with V3 forward and with an EVA

    phased elapsed time of 6:00. The clock starts whenthe EVA crewmembers switch to internal power.

    5. To complete ACS during EVA 3, the EVA would

    have to be extended past 6:30, possibly by as

    much as 55 to 60 minutes (with LOCKs installed)

    They begin the EVAs by suiting up andpassing through the Atlantis airlock intothe cargo bay to perform the initial setup.

    The crew then opens the WSIPE andinstalls the WFPC2 handhold, which wasretrieved from the forward fixture, to

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    g y p pTo prevent themselves from accidentallyfloating off, they attach safety tethers to acable running along the cargo bay sills.

    Grunsfeld (EV1) does various tasks to pre-pare for the days EVA servicing activities.These include removing the MFR from itsstowage location and installing it on theRMS end effector and installing theBerthing and Positioning System (BAPS)Support Post (BSP) on the FSS. The BSP isrequired to dampen the vibration that

    servicing activities will induce into thedeployed SAs. The crew then inspects theP105 and P106 umbilical covers for debris,deploys the center translation aid (TA),and installs the LGAPC. Meanwhile,Feustel (EV2) brings the CATs out of theairlock and attaches the MFR handle tothe MFR on the RMS.

    After the initial setup, the EVA crew pro-ceeds with replacing WFPC2 with WFC3.EV1, who is free floating, translates toORUC and deploys the aft fixture used fortemporarily stowing WFPC2 after it isremoved from HST. EV2 retrieves the FGShandhold from the forward fixture andinstalls the handhold on WFPC2. He thendisengages the WFPC2 blind mate con-

    nector, the WFPC2 ground strap bolt andthe A-latch. Next EV2 removes WFPC2from HST and stows it on the aft fixture.

    ,WFC3. Before removing WFC3 from theWSIPE, the crew disengages two ventvalves, a ground strap and the A-latch.When these tasks are complete, EV2maneuvers the WFC3 to the HST whileon the RMS (see Fig. 2-12). EV1 assistswith the installation of WFC3 into theHST aft shroud radial bay. EV2 engagesthe A-latch, ground strap and blind mateconnector prior to removing the WFPChandhold for EV1 to stow. The crew givesa go to the ground to proceed with

    powering up the WFC3 while they pro-ceed with stowing the WFPC2 into theWSIPE for return. EV2 installs WFPC2into the WSIPE via RMS with assistancefrom EV1. When both tasks are com-plete, the crew closes the WSIPE andstows the instrument handholds and theforward and aft fixtures.

    Following the WFC3 installation, the EVAcrew proceeds to the SI C&DH unitreplacement. EV1 translates to the star-board side of the MULE at the aft end ofthe payload bay, opens an MLI thermalcover on the aft face of the MULE, anddisengages seven of eight bolts thatsecure the SI C&DH-R in place.

    Meanwhile, EV2 is maneuvered on theRMS to Bay 10 and opens the door. EV2then disengages the 10 bolts that secure

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    the SI C&DH unit to the inner surface ofthe door, and disengages the electricalconnection drive stud. After removing

    EVA Day 2: Replace Rate SensorUnits (RSU), install Bay 2 nickel-hydrogen bat

    tery module and, if

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    the SI C&DH unit, EV2 inspects the doorside connector receptacles for damageor foreign object debris.

    In concert, EV1 disengages the final boltfrom the SI C&DH-R unit and removes itfrom the MULE. EV1 then translates tothe swap position atop the MULE star-board tower and hands off the replace-ment unit to EV2, still aboard the RMS,for installation on the Bay 10 door. EV1takes the failed unit back to the MULE to

    store for Earth return.

    As EV1 secures the failed unit to theMULE, EV2 returns to Bay 10 on the RMSand inspects the SI C&DH-R connectors.Next EV2 installs the new unit on thedoor, engages the connector drive stud,verifying that the box moves down evenlyand maintains proper alignment, and

    reinstalls 10 bolts to secure the unit tothe inner surface of the Bay 10 door. EV2then closes and latches the door.

    If time permits, EV1 performs get-aheadtasks. These include installing LOCKs onthe -V2 doors, lubing the +V2 and FGS-2(+V3) door bolts, and activating the SoftCapture Mechanism (SCM).

    Prior to ingressing the crew cabin, EV1 andEV2 complete daily payload bay closeoutsto safe the Shuttle in the event they mustrelease HST and terminate the missionearly. EV1 inspects the FSS main umbilicalmechanism, disengages the two centerPIP pins on the BSP, configures the centerTA and takes a tool inventory. Meanwhile

    EV2 prepares the CATs installed on theMFR handrail for return into the airlockand egresses the MFR. EV1 releases theMFR safety tether from the grapple fixturefor contingency Earth return. Aftercompleting the EVA Day 1 tasks, bothastronauts return to the airlock and performthe airlock ingress procedure.

    y g y ,time permits, install Soft CaptureMechanism (SCM).During EVA Day 2, the second team of

    EVA astronauts, Mike Massimino (EV1)and Mike Good (EV2), will focus onreplacing three RSUs (two gyros per RSU)and the Bay 2 NiH2 battery module.

    Fewer daily setup tasks are required forEVA Day 2 due to steps taken on EVADay 1. After completing the airlockegress procedure, EV1 performs the

    following setup tasks for the EVA:configure the MFR and BAPS post anddeploy the center TA. Meanwhile EV2exits the airlock with some of the EVADay 2 required CATs already installed onthe MFR toolboard. The crew preparesthe MFR and middeck CATS stowedprior to the EVA. Then they install theMFR with the toolboard on the RMS. The

    remaining CATS needed for the EVAs arestored in various containers known asORU protective enclosures (OPEs) orauxiliary transport modules (ATMs) in thecargo bay.

    To replace the RSUs, the crew needs toopen the -V3 side of HST to access thethree RSUs for changeout. The EVA crew

    begins by gathering some more toolsand the replacement RSU. The replace-ment RSUs are stowed in the SOPE. Thenew RSUs will be installed in the follow-ing order: RSU-2R, RSU-3R, RSU-1R.

    Together the astronauts retrieve theRSU-2R from the SOPE and the RSUChangeout Tool (RCT)sometimes

    referred to as the Pic-Stikfrom theSOPE lid. While EV2 configures hisworkstation for the task, EV1 assists inpreparing RSU-2R by removing protec-tive connector caps before EV2 stows itin a thermal protective bag for transla-tion to the HST. The SOPE is temporarilyclosed by EV1 as he returns for theremaining two RSUs.

    The astronauts now move to the -V3 aftshroud doors. From the RMS, EV2retracts the Fixed Head Star Tracker

    secured, they reposition the Cross AftShroud Harness (CASH) to a lower angledhandrail position in the aft shroud. This

    When the RSU-1 tasks are complete, EV1will have stowed all of the replaced RSUs(RSU-2, -3, and -1) in the SOPE where the

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    allows better access to the RSUs.

    The RSU changeout now consists ofsetting up an STS PFR from which EV1will secure himself so that he can assist inremoval and installation of the RSU. EV1handles the connector demating andremoval/handoff of the RSU-2 beingreplaced. He also assists in the connectorremating after RSU-2R is installed. EV2focuses on grappling the RSU-2 with thePic-Stik and releasing the three boltswith the Pistol Grip Tool (PGT). Oncereleased, EV1 is in position to reachand hold the RSU for handoff andstowage on the MFR until the new RSUis installed. Installation of the RSU-2R isa tricky process requiring precise align-ment of the RSU onto the mountingplate with EV1 providing visual assistance(see Fig. 2-13). With Pic-Stik in one hand

    and PGT in the other, EV2 engages thebolts and then removes the Pik-Stik andstows it while EV1 mates the connectors.

    Upon completion of the RSU-2 installation,the free floater EV1 reconfigures for theRSU-3 changeout task by stowing RSU-2back in the SOPE and retrieving RSU-3R.The crew then repeats the process of trans-

    lation, temporary stowage and installationonly this time with RSU-3R. The task is thesame and is repeated again for removal ofRSU-1 and installation of RSU-1R.

    replacement units were stored. He alsoretrieves and stows the STS PFR and RCT.

    If time permits, EV1 will retrieve the PowerInput Element (PIE) harness from the SOPEand partially install it as a get-ahead taskfor ACS on EVA Day 3. This is primarilybecause connector access is better fromthe -V3 location. Both astronauts thenreinstall CASH onto the aft shroudhandrails, close the doors and engage thedoor latch bolts. The task is not completeuntil the FHST #2 and #3 door seals are re-extended. Before leaving the worksite, EV1reconfigures the ASIPE PFR and port TAfor COS installation on EVA Day 3.

    While EV2 prepares for the Bay 2 batterytask, EV1 translates back to the airlock,stows the RSU bag and retrieves the EVAHelmet Interchangeable Portable (EHIP)

    battery bag and tools. If time permits, EV1will translate to the SCM EVA interface,install the EHIP battery and operate theSCM single-bolt-driving interface before re-stowing the EHIP battery. This will leave theSCM attached to HST upon deployment.

    Upon completion of the SCM task, EV1translates back to the SLIC to begin the

    battery replacement activity. EV2 opensthe HST Bay 2 door and installs a manualdoor stay. Removing the replacementbattery from SLIC involves disengaging

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    14 bolts to disconnect the replacementbattery from the battery plate assembly(BPA). Before removing the HST Bay 2b tt EV2 di t th b tt h

    EV2 perform the typical tool retrieval andsetup of the MFR.

    Wh th t t h l t d th

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    battery, EV2 disconnects the battery har-ness connections one at a time andinstalls protective caps over the batteryconnectors. After all connectors aresecured, EV2 disengages the 14 boltsand removes the battery. EV1 and EV2then swap the old batteries for the new.Both EV crewmembers reverse the pro-cedures to secure the batteries on SLICand HST. In a final step, EV2 rotates thebattery isolator switch to the on posi-tion, thus activating the batteries, beforeclosing the bay door.

    The remainder of EVA Day 2 is spent onany get-ahead tasks not performed onEVA Day 1, if time permits. Once againprior to ingressing back into the crewcabin, the EVs complete daily payloadbay closeouts to safe the Shuttle in theevent they must release HST and termi-

    nate the mission early. EV1 inspects theFSS main umbilical mechanism, disen-gages the two center PIP pins on theBSP, configures the center TA and takesa tool inventory. Meanwhile EV2 pre-pares the CATs installed on the MFRhandrail for return into the airlock andegresses the MFR. EV1 releases theMFR safety tether from the grapple

    fixture for contingency Earth return.After completing the EVA Day 2 tasks,both astronauts return to the airlock andperform the airlock ingress procedure.

    EVA Day 3: Replace the CorrectiveOptics Space Telescope AxialReplacement (COSTAR) with the

    Cosmic Origins Spectrograph(COS) and perform AdvancedCamera for Surveys (ACS) RepairPart 1 tasks.EVA Day 3 will be a challenging andexciting day for astronauts JohnGrunsfeld (EV1) and Andrew Feustel(EV2). The crewmembers begin their first

    rotation, so this will be the secondspacewalk for John and Andrew. Theywill remove the COSTAR, install the COSin its place and then perform the ACS

    When the astronauts have completed thedaily setup tasks, EV1 deploys the aft fix-ture and EV2 opens the -V2 aft shrouddoors to access the COSTAR. EV1 andEV2 work together to remove the COSTARfrom the telescope. EV1 releases theCOSTAR Y-harness from the handrail andrepositions it in the restraint tool installedon the center guiderail strut. EV1 thendemates the four COSTAR connectorsand disconnects the ground strap beforethey disengage the COSTAR A- and B-latches. While on the RMS, EV2 removesCOSTAR from the telescope and tem-porarily stows it on the aft fixture.

    Now the crew can retrieve the COS fromthe ASIPE. While working from the aftASIPE PFR, EV1 opens the ASIPE lid, dis-connects the COS ground strap anddeploys the B-latch alignment aid prior

    to disengaging the A- and B-latches. EV2removes the COS while on the RMS.Once it is removed, EV1 closes the ASIPElid and engages one lid latch to maintainthermal stability inside the ASIPE. Theastronauts will return to install COSTARfor Earth return after completing theCOS installation. They continue to worktogether to install the COS along

    guiderails into the telescope aft shroud(see Fig. 2-14). The installation is aidedby deployment of the B-latch alignmentaid arm. Next the astronauts engage theA- and B-latches, stow the alignment aid,reinstall the HST ground strap and matethe four COS connectors. Together theyclose the V2 aft shroud doors.

    As they prepare to install COSTAR intothe ASIPE, the ground has already beengiven the go to start testing the COSinstrument. Installation of the COSTARinto the ASIPE is the reverse of the COSremoval. After it is installed, EV2 closes theASIPE lid and engages the five lid latches.

    Meanwhile EV1 has begun setting up for

    the ACS repair task, which is also in theV2 bay of the aft shroud. The ACS repairis a very delicate operation compared tothe COS task. Due to limited EVA time on

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    As a free-floating crewmember, EV1maneuvers to the LOPE and NOPE toretrieve tools. EV1 ingresses the STS PFR

    within the aft shroud to perform most ofthe ACS repair. The ACS task involvesmany steps and tools. Using the S-bandSingle Access Transmitter (SSAT) tool,EV2 disengages four non-captive fastenersfrom the ACS WFC CEB assembly topcover and seats them in a fastener reten-tion block (FRB). Next EV1 installs theelectro-magnetic interference (EMI) grid

    cutter, cuts the grid from ACS WFC CEBassembly and restows the cutter/gridassembly into its transport enclosure.

    The grid removal leaves the CEB chassiscover exposed for access to the 32 smallfasteners that must be removed to

    replace the failed computer cards. Thefastener capture plate (FCP) is installed forremoval of all the captive fasteners. Afterall fasteners are released, the cover, screwsand the FCP assembly are removed.

    After EV1 removes the CEB cover, EV1removes circuit cards #1 and #2 from theCEB chassis and installs the cards in the

    card stowage enclosure (see Fig. 2-15),thus completing the ACS Part 1 repair. Iftime permits and the crew is given a

    Fig. 2-14 The refrigerator-sized Cosmic Origins Spectrograph is guided into place.Andrew Feustel holds the instrument as John Grunsfeld assesses alignment.

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    go to continue, EV1 will proceed withremoval of the remaining two cards andinstallation of the new flight computer.EV2s primary duty throughout the task is

    doors. EV1 ingresses the PFR, which wasplaced within the HST aft shroud, whileEV2 is on the RMS supporting the STISrepair task

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    EV2 s primary duty throughout the task isto assist with the tool retrieval andstowage while EV1 performs the repair. Ifthe crew is unable to complete the ACSPart 2 repair on EVA Day 3, a temporarycover is placed over the CEB opencomputer chassis as a protection untilEVA Day 5. (See Fig. 2-11 EVA timelineNotes for details.)

    When either one or both parts of theACS task are complete, depending ontime available, the crew proceeds withnominal daily closeouts. EV1 inspects theFSS main umbilical mechanism, disen-gages the two center PIP pins on theBSP, reconfigures the center TA andtakes a tool inventory. Meanwhile EV2prepares the CATs installed on the MFRhandrail for return into the airlock andegresses the MFR. EV1 releases the MFRsafety tether from the grapple fixture forcontingency Earth return. After thecompletion of the EVA Day 3 tasks, bothastronauts return to the airlock and per-form the airlock ingress procedure.

    EVA Day 4: Perform SpaceTelescope Imaging Spectrograph

    (STIS) repair and install New OuterBlanket Layer (NOBL).On EVA Day 4, astronauts Mike Massimino(EV1) and Mike Good (EV2) are sched-uled for their second and final EVA. Theday will focus on the restoring the failedSTIS instrument and installing twoNOBLs. The STIS repair will focus on thelow-voltage power supply circuit card.

    This will be similar to the ACS repair taskin that the instrument must be openedto access the internal computer boards.A major difference is that STIS requires111 small fasteners to be removed com-pared to 32 for ACS.

    The egress procedure and tool setup forthe Day 4 EVA is similar to that of previ-

    ous EVAs. After completing the dailysetup tasks, the crew is ready to beginthe STIS repair. EV1 translates to theORUC t fi th ASIPE TA d

    repair task.

    EV1 and EV2 now work in unison per-forming the delicate surgery on the STISinstrument. EV1 begins by installing theClamp Removal Tool (CRT) onto the MEBclamp. After removing the clamp bydisengaging a few fasteners, EV1 transfersthe MEB clamp with the tools to EV2 forstowage into the trash bag.

    Now the major challenge is to install

    the FCP on the MEB cover and remove107 fasteners. The STIS FCP is much largerthan the ACS FCP. While EV1 is workingon the fasteners, EV2 egresses the MFRand translates to stow and retrieve toolsfrom the ATM. After all fasteners havebeen removed, the FCP, screws andcover assembly can be removed. Thecrew must complete a final step by cut-

    ting a few thermistor wires to free theFCP/MEB cover assembly from the STISenclosure. EV2 ingresses the MFR on theRMS and receives the FCP/MEB coverfrom EV1 and stows it temporarily.

    With the MEB cover on the STIS enclo-sure removed, the astronauts begin theprocess of replacing the low-voltage

    power supply-2 (LVPS-2) card. EV1receives tools from EV2, removes theLVPS-2 from the MEB and stows it in thecard soft transport enclosure. EV1 handsoff the failed power supply and receivesthe new LVPS-2R for installation into theMEB. Installation of this circuit card is avery delicate operation and extreme caremust be take