sts-109 hst servicing mission 3b media reference guide

8/8/2019 STS-109 HST Servicing Mission 3B Media Reference Guide

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Media Reference Guide


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Solar Arrays

Spacewalking astronauts

unfold one of Hubble's new

highly efficient solar arrays

that will provide 20 percent

more power to the orbiting

observatory.

Power Control Unit

SM3B astronaut

installs replacement

for Telescope's aging

Power Control Unit.


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Hubble Space TelescopeServicing Mission 3B

Media Reference Guide

Prepared by Lockheed Martin for

the National Aeronautics and Space Administration

Special thanks to everyone who

helped pull this book together.

Buddy Nelson Chief writer/editor

Mel Higashi Design and layout

Pat Sharp Text and graphics integration

Computer generated 3-D illustrations provided by

Tim Cole, Kevin Balch, David Green, Nick Dellwo

Background information provided by

Brian Woodworth, Donna Weaver, Ann Jenkins,

Monty Boyd, Ray Villard, Dave Leckrone


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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 degreeand serving in World War I. However, after prac-ticing law for one year, he decided to chuck law forastronomy and I knew that, even if I were secondrate or third rate, it was astronomy that mattered.

He completed a Ph.D. thesis on the PhotographicInvestigation of Faint Nebulae at the University ofChicago and then continued his work at MountWilson Observatory, studying the faint patches ofluminous fog or nebulae in the night sky.

Using the largest telescope of its day, a 2.5-mreflector, he studied Andromeda and a number of

other nebulae and proved that they were other starsystems (galaxies) similar to our own Milky Way.

He devised the classification scheme for galaxiesthat is still in use today, and obtained extensiveevidence that the laws of physics outside theGalaxy are the same as on Earthin his own words:verifying the principle of the uniformity of nature.

In 1929, Hubble analyzed the speeds of recessionof a number of galaxies and showed that the speed

at which a galaxy moves away from us is propor-tional to its distance (Hubbles Law). Thisdiscovery of the expanding universe marked thebirth of the Big Bang Theory and is one of thegreatest triumphs of 20th-century astronomy.

In fact, Hubbles remarkable discovery could havebeen predicted some 10 years earlier by none otherthan Albert Einstein. In 1917, Einstein applied hisnewly developed General Theory of Relativity tothe problem of the universe as a whole. Einstein

was very disturbed to discover that his theorypredicted that the universe could not be static, buthad to either expand or contract. Einstein foundthis prediction so unbelievable that he went backand modified his original theory in order to avoidthis problem. Upon learning of Hubbles discov-eries, Einstein later referred to this as the biggestblunder of my life.

ESA Bulletin 58

Edwin Hubble (18891953) at the 48-inch

Schmidt telescope on Palomar Mountain

O

Photo courtesy of the Carnegie Institution of Washington


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SCIENCE INSTRUMENTS 4-1Advanced Camera for Surveys 4-1

Physical Description 4-3ACS Optical Design 4-3Filter Wheels 4-4

Observations 4-4Near Infrared Camera and Multi-Object Spectrometer 4-4

Instrument Description 4-5NICMOS Specifications 4-6Observations 4-7

Space Telescope Imaging Spectrograph 4-7Physical Description 4-7STIS Specifications 4-10Observations 4-10

Wide Field and Planetary Camera 2 4-11Physical Description 4-11

WFPC2 Specifications 4-13Observations 4-14

Astrometry (Fine Guidance Sensors) 4-14Fine Guidance Sensor Specifications 4-14Operational Modes for Astrometry 4-14Fine Guidance Sensor Filter Wheel 4-15Astrometric Observations 4-15

HST SYSTEMS 5-1Support Systems Module 5-2

Structures and Mechanisms Subsystem 5-3

Instrumentation and Communications Subsystem 5-6Data Management Subsystem 5-7Pointing Control Subsystem 5-9Electrical Power Subsystem 5-11Thermal Control 5-12Safing (Contingency) System 5-13

Optical Telescope Assembly 5-14Primary Mirror Assembly and Spherical Aberration 5-15Secondary Mirror Assembly 5-18Focal Plane Structure Assembly 5-19OTA Equipment Section 5-19

Fine Guidance Sensor 5-20FGS Composition and Function 5-20Articulated Mirror System 5-21

Solar Arrays 5-21Science Instrument Control and Data Handling Unit 5-22

Components 5-22Operation 5-23

Space Support Equipment 5-24Orbital Replacement Unit Carrier 5-25Crew Aids 5-25

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Section Page

HST OPERATIONS 6-1Space Telescope Science Institute 6-1

Scientific Goals 6-2STScI Software 6-2Selecting Observation Proposals 6-2

Scheduling Telescope Observations 6-2Data Analysis and Storage 6-2

Space Telescope Operations Control Center 6-2Operational Characteristics 6-3

Orbital Characteristics 6-3Celestial Viewing 6-3Solar System Object Viewing 6-3Natural Radiation 6-4Maneuvering Characteristics 6-4Communications Characteristics 6-5

Acquisition and Observation 6-6

VALUE ADDED: The Benefits of Servicing Hubble 7-1Cost-Effective Modular Design 7-1

Processor 7-2Data Archiving Rate 7-3Detector Technology 7-3Cryogenic Cooler 7-3Solar Arrays 7-4Simultaneous Science 7-4

GLOSSARY 8-1


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Figure Page

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ILLUSTRATIONS

1-1 The Hubble Space Telescope (HST)shown in a clean room at Lockheed Martin 1-3Space Systems Company Missiles & Space in Sunnyvale, California, beforeshipment to Kennedy Space Centeris equipped with science instrumentsand engineering subsystems designed as Orbital Replacement Units.

1-2 HST overall configuration 1-4

1-3 HST exploded view 1-51-4 HST specifications 1-61-5 Organization summary for HST program operational phase 1-72-1 Hubble Space Telescope Servicing Mission 3B Orbital Replacement Units 2-32-2 Servicing Mission 3B Payload Bay configuration 2-42-3 Flight Support System configurationaft view 2-52-4 Rigid Array Carrier configuration 2-52-5 Second Axial Carrier configuration 2-62-6 Multi-Use Lightweight Equipment Carrier configuration 2-62-7 Neutral Buoyancy Laboratory at Johnson Space Center 2-72-8 The STS-109 mission has seven crewmembers: (clockwise from top) Commander 2-9

Scott D. Altman, Pilot Duane G. "Digger" Carey, Mission Specialist Nancy JaneCurrie, Mission Specialist John M. Grunsfeld, Mission Specialist Richard M.Linnehan, Mission Specialist James H. Newman and Mission SpecialistMichael J. Massimino.

2-9 Detailed schedule of extravehicular activities during SM3B 2-112-10 Deployment of new rigid solar array 2-142-11 Change-out of Power Control Unit 2-152-12 Installation of the Advanced Camera for Surveys 2-162-13 Installation of NICMOS cooling system radiator 2-172-14 Redeploying the Hubble Space Telescope 2-17

3-1 A vast city of stars in 47 Tucanae 3-23-2 Planetary nurseries under fire in Orion 3-33-3 Vast star-forming region in 30 Doradus Nebula 3-43-4 A brilliant star at the Milky Ways core 3-53-5 Hubble discovers missing pieces of Comet LINEAR 3-63-6 Mars at opposition in 2001 3-73-7 Auroral storms on Jupiter 3-83-8 Galaxy NGC 3310 ablaze with active star formation 3-103-9 Spiral galaxy NGC 4013 viewed edge-on 3-104-1 Advanced Camera for Surveys (ACS) configuration 4-2

4-2 ACS Wide Field Channel optical design 4-34-3 ACS High Resolution/Solar Blind Channels optical design 4-34-4 ACS CCD filters 4-44-5 SBC filters 4-44-6 NICMOS Cooling System (NCS) 4-54-7 Near Infrared Camera and Multi-Object Spectrometer (NICMOS) 4-54-8 NICMOS optical characteristics 4-64-9 NICMOS specifications 4-7


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Figure Page

4-10 Space Telescope Imaging Spectrograph 4-74-11 STIS components and detectors 4-84-12 Simplified MAMA system 4-94-13 STIS specifications 4-104-14 Wide Field and Planetary Camera (WFPC) overall configuration 4-12

4-15 WFPC optics design 4-134-16 WFPC2 specifications 4-134-17 Fine Guidance Sensor (FGS) 4-144-18 FGS specifications 4-145-1 Hubble Space Telescopeexploded view 5-25-2 Hubble Space Telescope axes 5-25-3 Design features of Support Systems Module 5-35-4 Structural components of Support Systems Module 5-35-5 Aperture door and light shield 5-45-6 Support Systems Module forward shell 5-4

5-7 Support Systems Module Equipment Section bays and contents 5-55-8 Support Systems Module aft shroud and bulkhead 5-65-9 High Gain Antenna 5-65-10 Data Management Subsystem functional block diagram 5-75-11 Advanced computer 5-85-12 Data Management Unit configuration 5-85-13 Location of Pointing Control Subsystem equipment 5-105-14 Reaction Wheel Assembly 5-115-15 Electrical Power Subsystem functional block diagram 5-125-16 Placement of thermal protection on Support Systems Module 5-135-17 Light path for the main Telescope 5-15

5-18 Instrument/sensor field of view after SM3B 5-165-19 Optical Telescope Assembly components 5-165-20 Primary mirror assembly 5-175-21 Primary mirror construction 5-175-22 Main ring and reaction plate 5-175-23 Secondary mirror assembly 5-185-24 Focal plane structure 5-195-25 Optical Telescope Assembly Equipment Section 5-195-26 Cutaway view of Fine Guidance Sensor 5-205-27 Optical path of Fine Guidance Sensor 5-21

5-28 Solar Array wing detail comparison 5-225-29 Science Instrument Control and Data Handling unit 5-235-30 Command flow for Science Instrument Control and Data Handling unit 5-245-31 Flow of science data in the Hubble Space Telescope 5-25


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Figure Page

6-1 Continuous-zone celestial viewing 6-46-2 HST single-axis maneuvers 6-46-3 Sun-avoidance maneuver 6-56-4 TDRS-HST contact zones 6-57-1 Advanced scientific instruments installed (or to be installed) on HST pave the 7-1

way to new discoveries.7-2 Systems maintained and upgraded during each servicing mission 7-27-3 Processor improvements 7-27-4 Data archiving rate improvements 7-37-5 Increase in onboard pixels 7-37-6 Increase in HST infrared capability 7-37-7 Productivity gains with new solar arrays 7-47-8 Simultaneous use science instruments 7-4


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hroughout history, humankind hasexpanded its knowledge of the universe by

studying the stars. Great scientists such asNicholaus Copernicus, Galileo Galilei, JohannesKepler, Issac Newton, Edwin Hubble andAlbert Einstein contributed significantly to ourunderstanding of the universe.

The launch of the Hubble Space Telescope in1990 signified another great step towardunraveling the mysteries of space. Spectaculardiscoveries such as massive black holes at thecenter of galaxies, the existence of precursorplanetary systems like our own, and the quan-tity and distribution of cold dark matter arejust a few examples of the Telescopes findings.

With NASAs Servicing Mission 3B, wecontinue to carry the quest for knowledge inthe 21st century.

Another Step in Our Journey to the Stars

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About the Inside Covers

Three-dimensional computer models illustrate tasks that theSTS-109 crew will perform in orbit during Servicing Mission 3B.The models enable engineers to study task feasibility and toconfirm that astronauts can safely reach and service componentsand locations on the spacecraft. These dimensionally accurate,visually correct images help the extravehicular activity servicingteam prepare to install new components and upgrade functionalsystems on the Telescope.


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1-1

azing through his firstcrude telescope in the 17thcentury, Galileo discovered

the craters of the Moon, thesatellites of Jupiter and the ringsof Saturn. These observations ledthe way to todays quest for in-

depth knowledge and under-standing of the cosmos. And fornearly 12 years NASAs HubbleSpace Telescope (HST) hascontinued this historic quest.

Since its launch in April 1990,Hubble has provided scientificdata and images of unprecedentedresolution from which many newand exciting discoveries have beenmade. Even when reduced to raw

numbers, the accomplishments ofthe 12.5-ton orbiting observatoryare impressive:

Hubble has taken about420,000 exposures.

Hubble has observed nearly

17,000 astronomical targets. Astronomers using Hubble data

have published over 3,200scientific papers.

Circling Earth every 90minutes, Hubble has traveledabout 1.7 billion miles.

This unique observatory operatesaround the clock above theEarths atmosphere gatheringinformation for teams of scien-

tists who study the origin, evolu-tion and contents of the universe.The Telescope is an invaluabletool for examining planets, stars,star-forming regions of the Milky

Way, distant galaxies and quasars,and the tenuous hydrogen gas

lying between the galaxies.

The HST can produce images ofthe outer planets in our solarsystem that approach the clarity ofthose from planetary flybys.

Astronomers have resolved previ-ously unsuspected details ofnumerous star-forming regions ofthe Orion Nebula in the Milky Wayand have detected expanding gasshells blown off by exploding stars.

INTRODUCTION

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INTRODUCTION

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Using the Telescopes high-resolution and light-gatheringpower, scientists have calibratedthe distances to remote galaxiesto precisely measure the expan-sion of the universe and therebycalculate its age. They havedetected and measured the rota-tion of dust, gas and stars trappedin the gravitational field at thecores of galaxies that portend thepresence of massive black holes.

Hubbles deepest views of theuniverse, unveiling a sea ofgalaxies stretching back nearly tothe beginning of time, haveforced scientists to rethink someof their earlier theories aboutgalactic evolution. (Section 3 ofthis guide contains additionalinformation on the Telescopesscientific discoveries.)

The Telescopes mission is to spend20 years probing the farthest andfaintest reaches of the cosmos.Crucial to fulfilling this objective isa series of on-orbit manned serv-icing missions. During thesemissions astronauts performplanned repairs and maintenanceactivities to restore and upgrade theobservatorys capabilities. To facili-tate this process, the Telescopesdesigners configured science instru-ments and several vital engineeringsubsystems as Orbital ReplacementUnits (ORU)modular packageswith standardized fittings acces-sible to astronauts in pressurizedsuits (see Fig. 1-1).

The First Servicing Mission (SM1)took place in December 1993 andthe Second Servicing Mission(SM2) in February 1997. HubblesThird Servicing Mission was sepa-rated into two parts: ServicingMission 3A (SM3A) flew inDecember 1999 and ServicingMission 3B (SM3B) is scheduledfor an early 2002 launch.

SM3B astronauts will: Install a new science instru-

ment, the Advanced Camerafor Surveys (ACS).

Fit Hubble with a new pair ofrigid solar arrays.

Replace the Power Control Unit(PCU).

Replace a Reaction WheelAssembly (RWA).

Retrofit the Near InfraredCamera and Multi-ObjectSpectrometer (NICMOS).

Install New Outer BlanketLayer (NOBL) insulation panels.

The ACS consists of three elec-tronic channels and a complementof filters and dispersers thatdetect light from the ultravioletto the near infrared (1200 to10,000 angstroms). This camerawill be able to survey a field with2.3 times the area of the WideField and Planetary Camera 2(WFPC2) currently on Hubble. Itwill provide four times as muchspatial information and up to fivetimes the sensitivity of WFPC2.The ACS will not replace WFPC2,however. WFPC2 will continuewith its spectacular observationson the Telescope.

Designed and built by GoddardSpace Flight Center (GSFC), theEuropean Space Agency (ESA)and Lockheed Martin SpaceSystems Company, the new solararrays will produce 20 percentmore power than the currentarrays. In addition, they are lesssusceptible to damage and theextreme temperature swingsinduced by Hubbles orbit.

The PCU controls and distributeselectricity from the solar arraysand batteries to other parts of theTelescope. Although it is stillfunctioning, this PCU has beenon the Telescope since 1990 andsome of its relays have failed.Replacement will ensure properoperation over the long term.

One of four RWAs will be replaced.The reaction wheels are part of anactuator system that moves thespacecraft into commanded posi-tions. Using spin momentum, thewheels move HST into positionand then keep the spacecraftstable. The wheel axes areoriented so that Hubble canoperate with only three wheels.

The NICMOS, a dormant instru-ment, will be retrofitted with anew, experimental NICMOSCooling System (NCS) to returnit to active duty.

If time permits, NOBL insulationpanels will be installed to preventdamage to Hubble from sunlightand extreme temperature changesand to maintain the Telescopesnormal operating temperature.

Hubble Space Telescope

Configuration

Figures 1-2 and 1-3 show theoverall Telescope configuration.Figure 1-4 lists specifications forthe Telescope. The majorelements are:

Optical Telescope Assembly(OTA)two mirrors and asso-ciated structures that collectlight from celestial objects

Science instrumentsdevicesused to analyze the imagesproduced by the OTA

Support Systems Module(SSM)spacecraft structurethat encloses the OTA andscience instruments

Solar Arrays (SA).

Optical Telescope Assembly

The OTA consists of twomirrors, support trusses and thefocal plane structure. The opticalsystem is a Ritchey-Chretiendesign, in which two specialaspheric mirrors form focusedimages over the largest possiblefield of view. Incoming lighttravels down a tubular baffle thatabsorbs stray light. The concave

primary mirror94.5 in. (2.4 m)in diametercollects the lightand converges it toward theconvex secondary mirror, whichis only 12.2 in. (0.3 m) in diam-eter. The secondary mirror directsthe still-converging light backtoward the primary mirror andthrough a 24-in. hole in its centerinto the Focal Plane Structure,where the science instrumentsare located.


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INTRODUCTION

1-3

Fig. 1-1

The Hubble Space Telescope (HST)shown in a clean room at Lockheed Martin

Space Systems Company Missiles & Space Operations in Sunnyvale, California,

before shipment to Kennedy Space Centeris equipped with science instruments

and engineering subsystems designed as Orbital Replacement Units.

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INTRODUCTION

1-4

Science Instruments

Hubble can accommodate eight science instruments.Four are aligned with the Telescopes main opticalaxis and are mounted immediately behind theprimary mirror. These axial science instruments are: Space Telescope Imaging Spectrograph (STIS) Faint Object Camera (FOC) Near Infrared Camera and Multi-Object

Spectrometer (NICMOS) Corrective Optics Space Telescope Axial

Replacement (COSTAR).

In addition to the four axial instruments, four otherinstruments are mounted radially (perpendicular to the

main optical axis). These radial science instruments are: Wide Field and Planetary Camera 2 (WFPC2) Three Fine Guidance Sensors (FGS).

Space Telescope Imaging Spectrograph. STISseparates incoming light into its component wave-lengths, revealing information about the atomiccomposition of the light source. It can detect abroader range of wavelengths than is possible fromEarth because there is no atmosphere to absorb

certain wavelengths. Scientists can determine thechemical composition, temperature, pressure and

turbulence of the target producing the lightall fromspectral data.

Faint Object Camera. The FOC was decommissionedin 1997 to better allocate existing resources. However,the camera remains turned on and available to scien-tists if needed. The FOC will be returned to Earthafter the ACS is installed in its place during SM3B.

Near Infrared Camera and Multi-ObjectSpectrometer. Use of this now-dormant instrumentwill resume after successful installation of NCSduring SM3B.

Corrective Optics Space Telescope AxialReplacement. COSTAR was installed on HST in 1993to fix a flaw in the shape of the primary mirror (acommon mirror fabrication defect called spherical aber-ration) that was detected shortly after Hubbles launchin 1990. Because all the instruments now on theTelescope are equipped with corrective optics, COSTARno longer is needed, but it will remain on the Telescopeuntil its slot is filled by a new science instrument on SM4.

Fig. 1-2 HST overall configuration

Forward Shell

Primary Mirror

Aft Shroud

COSTAR andScience

Instruments

Axial (4)

Radial (1)

Solar Array (2)Fine GuidanceSensor (3)

Light Shield

Aperture DoorSecondaryMirror (2)

High Gain Antenna (2)

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INTRODUCTION

1-5

Wide Field and Planetary Camera 2.WFPC2 is anelectronic camera that records images at two magnifi-cations. A team at the Jet Propulsion Laboratory (JPL)

in Pasadena, California,built the first WFPC and

developed the WFPC2.The team incorporated anoptical correction byrefiguring relay mirrors inthe optical train of thecameras. Each relay mirroris polished to a prescrip-tion that compensates forthe incorrect figure onHSTs primary mirror.Small actuators fine-tunethe positioning of thesemirrors on orbit.

Fine Guidance Sensors.The three FGSs have twofunctions: (1) providedata to the spacecraftspointing system to keepHST pointed accurately ata target when one ormore of the science

instruments is being used to take data and (2) act as ascience instrument. When functioning as a scienceinstrument, two of the sensors lock onto guide stars

Fig. 1-3 HST exploded view

Hubble Space Telescope (HST)

WeightLength

DiameterOptical systemFocal lengthPrimary mirrorSecondary mirrorField of viewPointing accuracyMagnitude rangeWavelength rangeAngular resolutionOrbitOrbit timeMission

24,500 lb (11,110 kg)43.5 ft (15.9 m)10 ft (3.1 m) Light Shield and Forward Shell14 ft (4.2 m) Equipment Section and Aft ShroudRitchey-Chretien design Cassegrain telescope189 ft (56.7 m) folded to 21 ft (6.3 m)94.5 in. (2.4 m) in diameter12.2 in. (0.3 m) in diameterSee instruments/sensors0.007 arcsec for 24 hours5 mv to 30 mv (visual magnitude)1100 to 24,000 0.1 arcsec at 6328 320 nmi (593 km), inclined 28.5 degrees from equator97 minutes per orbit20 years

Fig. 1-4 HST specifications

Magnetic Torquer (4)

High Gain Antenna (2)

Support SystemsModule Forward Shell

Optical Telescope AssemblySecondary Mirror Assembly

Secondary Mirror Baffle

Central Baffle

Optical Telescope AssemblyPrimary Mirror and Main Ring

Fine Guidance OpticalControl Sensor (3)

Optical TelescopeAssembly FocalPlane Structure

SupportSystemsModuleAft Shroud

Fixed HeadStar Tracker (3)and Rate GyroAssembly

Radial ScienceInstrument Module (1)

Optical Telescope AssemblyEquipment Section

Optical Telescope AssemblyMetering Truss

Main Baffle

Light Shield

ApertureDoor

Magnetom-eter (2)

Solar Array (2)

Low GainAntenna (2)

Support Systems ModuleEquipment Section

AxialScienceInstrumentModule (3)

andCOSTAR

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INTRODUCTION

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and the third measures thebrightness and relative positionsof stars in its field of view. Thesemeasurements, referred to asastrometry, are helping toadvance knowledge of thedistances and motions of starsand may be useful in detectingplanetary-sized companions ofother stars.

Support Systems Module

The SSM encloses the OTA andthe science instruments like thedome of an Earth-based observa-tory. It also contains all of thestructures, mechanisms, commu-nications devices, electronics andelectrical power subsystemsneeded to operate the Telescope.

This module supports the lightshield and an aperture door that,when opened, admits light. Theshield connects to the forwardshell on which the SAs and HighGain Antennas (HGA) aremounted. Electrical energy fromthe SAs charges the spacecraftbatteries to power all HSTsystems. Four antennas, twohigh-gain and two low-gain, sendand receive information between

the Telescope and the SpaceTelescope Operations ControlCenter (STOCC). Allcommanding occurs through theLow Gain Antennas (LGA).

Behind the OTA is the EquipmentSection, a ring of bays that housethe batteries and most of the elec-tronics, including the computerand communications equipment.

At the rear of the Telescope, theaft shroud contains the science

instruments.

Solar Arrays

The SAs provide power to thespacecraft. They are mounted likewings on opposite sides of theTelescope, on the forward shell ofthe SSM. The SAs are rotated so

each wings solar cells face theSun. The cells absorb the Sunslight energy and convert it intoelectrical energy to power theTelescope and charge the space-crafts batteries, which are partof the Electrical Power Subsystem(EPS). Batteries are used whenthe Telescope moves into Earthsshadow during each orbit.

Computers

Hubbles Data ManagementSubsystem (DMS) contains twocomputers: the AdvancedComputer, installed duringSM3A, and the ScienceInstrument Control and DataHandling (SI C&DH) unit. The

Advanced Computer performs

onboard computations andhandles data and command trans-missions between the Telescopesystems and the ground system.The SI C&DH unit controlscommands received by thescience instruments, formatsscience data and sends data tothe communications system fortransmission to Earth.

The Hubble Space

Telescope ProgramHubble Space Telescope repre-sents the fulfillment of a 50-yeardream and 25 years of dedicatedscientific effort and politicalvision to advance humankindsknowledge of the universe. TheHST program comprises an inter-national community of engi-neers, scientists, contractors andinstitutions. It is managed byGSFC for the Office of SpaceScience (OSS) at NASAHeadquarters.

The program falls under theSearch for Origins and PlanetarySystems scientific theme. WithinGSFC, the program is in the FlightPrograms and Projects Directorate,under the supervision of the

Associate Director/ Program

Manager for HST. It is organizedas two flight projects: (1) theHST Operations Project and (2)the HST Development Project.

Responsibilities for scientific over-sight on HST are divided amongthe members of the Project ScienceOffice (PSO). The PSO is designed

to interact effectively and effi-ciently with the HST Program andthe wide range of external organi-zations involved with the HST.The senior scientist for the HSTand supporting staff work in theOffice of the Associate Director/Program Manager for HST. Thisgroup is concerned with thehighest level of scientific manage-ment for the project. Figure 1-5summarizes the major organiza-tions that oversee the program.

The roles of NASA centers andcontractors for on-orbit servicingof the HST are:

Goddard Space Flight Center(GSFC)Overall managementof daily on-orbit operations ofHST and the development, inte-gration and test of replacementhardware, space support equip-ment and crew aids and tools

Johnson Space Center (JSC)

Overall servicing missionmanagement, flight crewtraining, and crew aids and tools

Kennedy Space Center (KSC)Overall management of launchand post-landing operations formission hardware

Ball AerospaceDesign, devel-opment and provision of axialscience instruments

JPLDesign, development andprovision of WFPC1 and WFPC2

Lockheed MartinPersonnel

support for GSFC to accomplish(1) development, integrationand test of replacement hard-ware and space support equip-ment; (2) system integrationwith the Space TransportationSystem (STS); (3) launch andpost-landing operations and (4)daily HST operations.


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Major subcontractors for SM3Binclude Goodrich Corporation,Honeywell, Jackson and Tull,Orbital Sciences Corporation,Computer Sciences Corporation,

Association of Universities forResearch in Astronomy (AURA),Swales Aerospace, QSS, Creareand L-3 Communications.

The HST program requires acomplex network of communica-tions among GSFC, the Telescope,Space Telescope Ground Systemand the Space Telescope ScienceInstitute. Figure 1-6 showscommunication links.

The Value of Servicing

Hubbles visionary modular designallows NASA to equip it with new,state-of-the-art instruments everyfew years. These servicing missionsenhance the Telescopes sciencecapabilities, leading to fascinatingnew discoveries about theuniverse. Periodic service calls alsopermit astronauts to tune up theTelescope and replace limited-lifecomponents.

INTRODUCTION

1-7

Organization

NASA HeadquartersOffice of Space ScienceDirectorate of Astronomy and Physics

Function

Overall responsibility for the program

Space Telescope Science Institute

Goddard Space Flight Center HST Flight Systems and

Servicing Project

Provides minute-to-minute spacecraftcontrol

Schedules, plans and supports allscience operations when required

Monitors telemetry communicationsdata to the HST

Selects observing programs fromnumerous proposals

Analyzes astronomical data

Responsible for implementing HSTServicing Program

Manages development of new HST

spacecraft hardware and serviceinstruments

Manages HST Servicing PayloadIntegration and Test Program

Primary interface with the SpaceShuttle Program at JSC

Goddard Space Flight Center Office of the Associate Director/

Program Manager for HST HST Operations Project

HST Development Project

Space Telescope OperationsControl Center

Overall HST program management HST project management Responsible for overseeing all HST

operations

Fig. 1-5 Organization

summary for HST

program operational

phase

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Fig. 1-6 HSTdata collecting

network

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Starlight

Tracking andData RelaySatellite System(TDRSS)

Payload OperationsControl Center

SpaceTelescopeScienceInstitute(STScI)

Space TelescopeOperationsControl Center(STOCC)

TDRSSGroundStation


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2-1

he Hubble Space Telescope(HST) is the first observa-tory designed for extensive

maintenance and refurbishmentin orbit. Its science instrumentsand many other componentswere planned as OrbitalReplacement Units (ORU)modular in construction withstandardized fittings and acces-sible to astronauts. Handrails,foot restraints and other built-infeatures help astronauts performservicing tasks in the Shuttlecargo bay as they orbit Earth at17,500 mph.

NASA plans to launch HSTServicing Mission 3B (SM3B) in

early 2002. The third servicingmission (SM3), originally plannedfor June 2000, had six scheduledextravehicular activity (EVA)days, followed by a reboost ofthe Telescope. However, whenthe progressive failure of severalRate Sensor Unit gyros left thespacecraft unable to performscience operations, NASA splitSM3 into two separate flights.The first flight, designated SM3Aand manifested as STS-103, waslaunched in December 1999 andincluded four scheduled EVAdays. After the flight was delayeduntil late December, NASAreduced the number of scheduledEVAs to three to ensure that the

Shuttle would be on the groundbefore the year 2000 rollover.

SM3A accomplishments includereplacement of all three RateSensor Units (six gyros), NICMOSvalve reconfiguration, installationof six Voltage/TemperatureImprovement Kits, replacementof the DF-224 Computer withthe Advanced Computer, change-out of the Fine Guidance SensorUnit-2 and mate of the associatedOptical Control ElectronicsEnhancement Kit connectors,change-out of the S-Band Single

Access Transmitter-2, replace-ment of the Engineering/ScienceTape Recorder-3 with a Solid

HST SERVICING

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HST SERVICING MISSION 3B

2-2

State Recorder and installation ofNew Outer Blanket Layers(NOBLs) over Bays 1, 9 and 10.

SM3B is manifested as STS-109aboard the Space ShuttleColumbia (OV-102) to belaunched to a rendezvous altitude

of approximately 315 nauticalmiles. During the planned 11-daymission, the Shuttle willrendezvous with, capture andberth the HST to the FlightSupport System (FSS). Followingservicing, the Shuttle willunberth Hubble and redeploy itto its mission orbit.

Five EVA days are scheduledduring the SM3B mission.Columbias cargo bay is equipped

with several devices to help theastronauts: The FSS will berth and rotate

the Telescope. Large, specially designed equip-

ment containers will house theORUs.

Astronauts will work and bemaneuvered as needed from theShuttle robot arm.

SM3B will benefit from lessons

learned on NASAs previous on-orbit servicing missions: the 1984Solar Maximum repair mission,the 1993 HST First ServicingMission (SM1), the 1997 HSTSecond Servicing Mission (SM2)and the 1999 HST ThirdServicing Mission (SM3A). NASAhas incorporated these lessons indetailed planning and trainingsessions for Columbia crewmem-bers Scott Altman, Duane Carey,Nancy Currie, John Grunsfeld,

James Newman, MichaelMassimino and RichardLinnehan.

Reasons for Orbital

Servicing

HST is a national asset and aninvaluable international scientificresource that has revolutionizedmodern astronomy. To achieve itsfull potential, the Telescope will

continue to conduct extensive,integrated scientific observations,including follow-up work on itsmany discoveries.

Although the Telescope hasnumerous redundant parts andsafemode systems, such a

complex spacecraft cannot bedesigned with sufficient backupsto handle every contingencylikely to occur during a 20-yearmission. Orbital servicing is thekey to keeping Hubble in oper-ating condition. NASAs orbitalservicing plans address threeprimary maintenance scenarios: Incorporating technological

advances into the scienceinstruments and ORUs

Normal degradation of

components Random equipment failure or

malfunction.

Technological Advances.Throughout the Telescopes life,scientists and engineers haveupgraded its science instrumentsand spacecraft systems. Forexample, when Hubble waslaunched in 1990, it wasequipped with the Goddard High

Resolution Spectrograph and theFaint Object Spectrograph. Asecond-generation instrument,the Space Telescope ImagingSpectrograph, took over the func-tion of those two instrumentsadding considerable new capabili-tieswhen it was installedduring SM2 in 1997. A slot wasthen available for the NearInfrared Camera and Multi-Object Spectrometer (NICMOS),which expanded the Telescopesvision into the infrared region ofthe spectrum. In addition, onboth SM2 and SM3A a newstate-of-the-art Solid StateRecorder (SSR) replaced anEngineering/Science TapeRecorder (E/STR). Similarly,during SM3A the original DF-224Computer was replaced with afaster, more powerful AdvancedComputer based on the Intel80486 microchip.

Component Degradation.Servicing plans take into accountthe need for routine replacements,for example, restoring HST systemredundancy and limited-life itemssuch as spacecraft thermal insula-tion and gyroscopes.

Equipment Failure. Given theenormous scientific potential ofthe Telescopeand the invest-ment in designing, developing,building and putting it intoorbitNASA must be able tocorrect unforeseen problems thatarise from random equipmentfailures or malfunctions. TheSpace Shuttle program provides aproven system for transportingastronauts fully trained for on-orbit servicing of the Telescope.

Originally, planners consideredusing the Shuttle to return theTelescope to Earth approximatelyevery 5 years for maintenance.However, the idea was rejectedfor both technical and economicreasons. Returning Hubble toEarth would entail a significantlyhigher risk of contaminating ordamaging delicate components.Ground servicing would require

an expensive clean room andsupport facilities, including alarge engineering staff, and theTelescope would be out of actionfor a year or morea long time tosuspend scientific observations.

Shuttle astronauts can accom-plish most maintenance andrefurbishment within a 10-dayon-orbit mission with only abrief interruption to scientificoperations and without the addi-

tional facilities and staff neededfor ground servicing.

Orbital Replacement

Units

Advantages of ORUs includemodularity, standardization andaccessibility.

Modularity. Engineers studiedvarious technical and human


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factors criteria to simplifyTelescope maintenance.Considering the limited timeavailable for repairs and theastronauts limited visibility,mobility and dexterity in theEVA environment, designerssimplified the maintenance tasks

by planning entire componentsfor replacement.

ORUs are self-contained boxesinstalled and removed usingfasteners and connectors. Theyrange from small fuses to phone-booth-sized science instrumentsweighing more than 700 pounds(318 kg). Figure 2-1 shows theORUs for SM3B.

Standardization. Standardized

bolts and connectors also

simplify on-orbit repairs. Captivebolts with 7/16-inch, double-height hex heads hold manyORU components in place. Toremove or install the bolts, astro-nauts need only a 7/16-inchsocket fitted to a power tool ormanual wrench. Some ORUs do

not contain these fasteners.When the maintenance philos-ophy changed from Earth-returnto on-orbit servicing, othercomponents were selected asreplaceable units after theirdesign had matured. This added agreater variety of fasteners to theservicing requirements, includingnon-captive 5/16-inch hex headbolts and connectors withoutwing tabs. Despite these excep-tions, the high level of standardi-

zation among units reduces the

number of tools needed for theservicing mission and simplifiesastronaut training.

Accessibility. To be serviced inspace, Telescope componentsmust be seen and reached by anastronaut in a bulky pressure

suit, or they must be withinrange of an appropriate tool.Therefore, most ORUs aremounted in equipment baysaround the perimeter of thespacecraft. To access these units,astronauts simply open a large doorthat covers the appropriate bay.

Handrails, foot restraint sockets,tether attachments and othercrew aids are essential to safe,efficient on-orbit servicing. In

anticipation of such missions,

Fig. 2-1 Hubble Space Telescope Servicing Mission 3B Orbital Replacement Units

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31 foot-restraint sockets and225 feet of handrails weredesigned into the Telescope. Footrestraint sockets and handrailsgreatly increase astronautsmobility and stability, affordingthem safe worksites convenientlylocated near ORUs.

Crew aids such as portable lights,special tools, installationguiderails, handholds andportable foot restraints (PFR) alsoease servicing of Hubble compo-nents. Additionally, footrestraints, translation aids andhandrails are built into variousequipment and instrumentcarriers specific to each servicingmission.

Shuttle Support Equipment

To assist astronauts in servicingthe Telescope, Columbia will carryinto orbit several thousandpounds of hardware and SpaceSupport Equipment (SSE),including the Remote

Manipulator System (RMS), FSS,Rigid Array Carrier (RAC),Second Axial Carrier (SAC) andMulti-Use LightweightEquipment (MULE) carrier.

Remote Manipulator System

The Columbia RMS, also knownas the robotic arm, will be usedextensively during SM3B. Theastronaut operating this device

from inside the cabin is desig-nated the intravehicular activity(IVA) crewmember. The RMSwill be used to: Capture, berth and release the

Telescope Transport new components,

instruments and EVA astro-

nauts between worksites Provide a temporary workplatform for one or both EVAastronauts.

Space Support Equipment

Ground crews will install fourmajor assemblies essential forSM3Bthe FSS, RAC, SAC andMULEin Columbias cargo bay(see Fig. 2-2).


2-4

Fig. 2-2 Servicing Mission 3B Payload Bay configuration

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0 50 100 150 200 250 300

Solar Array IIStowed

Power ControlUnitReplacement(PCU-R)

Second AxialCarrier (SAC)

HST PortableFoot Restraint(PFR)

Solar Array 3Deployed 180 deg(Cell Side Up) HST Outline

MULE

LOPE

NCS Radiator

SOPE

ESM (in SoftEnclosure)

HST PortableFoot Restraint

(PFR)

Flight SupportSystem (FSS)Outline

ManipulatorFoot Restraint(MFR)

AftFixture

NICMOS CryoCooler (NCC)

Solar Array IIStowagePlatform

Rigid ArrayCarrier (RAC)

ASIPE

Acronyms

ESMASIPE LOPE MULE NCS NOBL SOPE

AxialScientificInstrument

ProtectiveEnclosure

ElectronicsSupportModule

Large OrbitalReplacementUnit (ORU)

ProtectiveEnclosure

Multi-UseLightweightEquipment

Carrier

NICMOSCoolingSystem

Small ORUProtectiveEnclosure

New OuterBlanketLayer

(StowedUnder SAC)

Inches


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Flight Support System

The FSS is a maintenance platform used to berththe HST in the cargo bay after the Columbia crewhas rendezvoused with and captured the Telescope(see Fig. 2-3). The platform was adapted from theFSS first used during the 1984 Solar Maximumrepair mission. It has a U-shaped cradle that spans

the rear of the cargo bay. A circular berthing ringwith three latches secures the Telescope to thecradle. The berthing ring can rotate the Telescopealmost 360 degrees (176 degrees clockwise or coun-terclockwise from its null position) to give EVAastronauts access to every side of the Telescope.

The FSS also pivots to lower or raise the Telescope asrequired for servicing or reboosting. The FSSsumbilical cable provides power from Columbia tomaintain thermal control of the Telescope during theservicing mission.

Rigid Array Carrier

The RAC is located in Columbias forward cargo bay. Ithas provisions for safe transport to orbit of the third-generation Solar Arrays (SA3) and associated second-generation Diode Box Assemblies (DBA2), and forreturn from orbit of the second-generation Solar Arrays(SA2) and their associated Diode Box Assemblies(DBA). The RAC also includes the MLI Repair Tool,two SA2 Spines, spare PIP pins, a spareDBA2, two portable connector trays,two spare SADA Clamps, the MLI Tent,

Large and Small MLI Patches, four SA2Bistem Braces, a Jettison Handle andtwo Auxiliary Transport Modules (ATM)to house miscellaneous smaller hardware(see Fig. 2-4).

Second Axial Carrier

The SAC is centered in Columbias cargobay. It has provisions for safe transport ofORUs to and from orbit (see Fig. 2-5). Inthe SM3B configuration: The Advanced Camera for Surveys

(ACS) is stored in the AxialScientific Instrument ProtectiveEnclosure (ASIPE).

The Power Control Unit (PCU)and PCU Transport Handle arestored on the starboard side.

The NICMOS Cryo Cooler (NCC), WFPC ThermalCover and Fixed Head Star Tracker (FHST) Coversare stored on the port side.

The NOBL Transporter (NT) contains the newprotective coverings to be installed on theTelescope equipment bay doors.

The SAC houses other hardware, including theMLI Recovery Bag, eight Aft Shroud Latch RepairKits, Handrail Covers and Caddies, PCU HarnessRetention Device, Scientific Instrument Safety Bar,Cross Aft Shroud Harness (CASH), an Aft Fixture,two STS PFRs and an Extender, two Translation

Fig. 2-3 Flight Support System configuration aft view

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AcronymsAMSB Advanced Mechanism Selection BoxCEP Contamination Environment PackageCMP Contamination Monitoring Package

EPDSU Enhanced Power Distribution and Switching UnitIPCU Interface Power Control UnitPDSU Power Distribution and Switching UnitPPCU Port Power Conditioning UnitSIP Standard Interface PanelSPCU Starboard Power Conditioning Unit

CEP-2

BAPS Support Post

EPDSUBracket

SIP DepartureBracket

CEP-1

Fig. 2-4 Rigid Array Carrier configuration

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SA3ForwardX-Constraint

SparePIP-PinBracket

DBA2

ATM1ATM2

SA2 Spines

CTSB

SADACPUA

JettisonHandle

SA2 Aft Latch

SA2 ForwardLatch

Note: For clarity, MLI coversare not shown


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Aids (TA), one ASIPE mini-TAand the Bays 5, 10 and DBAThermal Covers.

The protective enclosure, itsheaters and thermal insulationcontrol the temperature of thenew ORUs, providing an environ-

ment with normal operatingtemperatures. Struts between theASIPE enclosure and the palletprotect Science Instruments fromloads generated at liftoff andduring Earth return.

Multi-Use Lightweight Equipment

Carrier

The MULE is located in Columbiasaft cargo bay (see Fig. 2-6). It has

provisions for safe transport ofthe NCS Radiator, ElectronicsSupport Module (ESM), LargeORU Protective Enclosure (LOPE)and Small ORU ProtectiveEnclosure (SOPE).

Astronaut Roles

and Training

To prepare for SM3B, the seven-member Columbia crew trained

extensively at NASAs Johnson

Space Center (JSC) in Houston,Texas, and Goddard Space FlightCenter (GSFC) in Greenbelt,Maryland.

Although there has been exten-sive cross training, eachcrewmember also has trained forspecific tasks. Training forMission Commander Scott

Altman and Pilot Duane Carey

focused on rendezvous and prox-imity operations, such asretrieval and deployment of theTelescope. The two astronautsrehearsed these operations usingJSCs Shuttle Mission Simulator,a computer-supported trainingsystem. In addition, they receivedIVA training: helping the EVAastronauts into suits and moni-

toring their activities outside theColumbia cabin.

The five Mission Specialists alsoreceived specific training, startingwith classroom instruction onthe various ORUs, tools and crewaids, SSE such as the RMS (therobotic arm) and the FSS.Principal operator of the roboticarm is Mission Specialist NancyCurrie, who also performs IVAduties. The alternate RMS oper-ator is Commander Altman.

Currie trained specifically forcapture and redeployment of theTelescope, rotating and pivotingthe Telescope on the FSS andrelated contingencies. Theseoperations were simulated withJSCs Manipulator DevelopmentFacility, which includes a mockupof the robotic arm and a


2-6

Fig. 2-5 Second Axial Carrier configuration

Fig. 2-6 Multi-Use Lightweight Equipment Carrier configuration

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K1175_206

OPA

Translation

Aid

Translation Aid

EPDSU

ASLR Kits

SOPE

Aft Fixture

ASIPE

NT

2-Axis1/4-turnLatch

EVACenter Bolts

1-Axis 1/4-turnLatch

3-Axis1/4-turnLatch

NCSRadiator

ESM(Soft EnclosureShown inPhantom)

NCC(Soft EnclosureShown in Phantom)

LOPE

PFR


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suspended helium balloon withdimensions and grapple fixturessimilar to those on theTelescope. RMS training alsotook place at JSCs NeutralBuoyancy Laboratory (NBL),enabling the RMS operator andalternates to work with indi-

vidual team members. Forhands-on HST servicing, EVAcrewmembers work in teams oftwo in the cargo bay. AstronautsJohn Grunsfeld, RichardLinnehan, James Newman andMichael Massimino loggedmany days of training for thisimportant role in the NBL, a40-foot (12-m)-deep water tank(see Fig. 2-7).

In the NBL, pressure-suited

astronauts and their equipmentare made neutrally buoyant, acondition that simulatesweightlessness. Underwatermockups of the Telescope, FSS,RAC, SAC, MULE, RMS and theShuttle cargo bay enabled theastronauts to practice the entireSM3B EVA servicing. Suchtraining activities help the astro-nauts efficiently use the limitednumber of days (5) and duration

(6 hours) of each EVA period.

Other training aids at JSChelped recreate orbital condi-tions for the Columbia crew. Inthe weightlessness of space, thetiniest movement can set instru-ments weighing several hundredpounds, such as ACS, intomotion. To simulate the delicateon-orbit conditions, models ofthe instruments are placed onpads above a stainless steel floor

and floated on a thin layer ofpressurized gas. This allows crewmembers to prac-tice carefully nudging the instruments into theirproper locations.

Astronauts also used virtual reality technologies intheir training. This kind of ultrarealistic simulationenabled the astronauts to see themselves next tothe Telescope as their partners maneuver them intoposition with the robotic arm.

Extravehicular Crew Aids and Tools

Astronauts servicing HST use three different kindsof foot restraints to counteract the weightless envi-ronment. When anchored in a Manipulator FootRestraint (MFR), an astronaut can be transportedfrom one worksite to the next with the RMS. Usingeither the STS or HST PFR, an astronaut establishesa stable worksite by mounting the restraint to any of

Fig. 2-7 Neutral Buoyancy Laboratory at Johnson Space Center

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2-8

31 different receptacles placedstrategically around the Telescopeor 17 receptacles on the RAC, SAC,FSS and MULE.

In addition to foot restraints, EVAastronauts have more than 150tools and crew aids at their disposal.

Some of these are standard itemsfrom the Shuttles toolbox whileothers are unique to SM3B. Alltools are designed for use in aweightless environment by astro-nauts wearing pressurized gloves.

The most commonly used ORUfasteners are those with 7/16-inch,double-height hex heads. Thesebolts are used with three differentkinds of fittings: J-hooks, captivefasteners and keyhole fasteners. To

replace a unit, an astronaut uses a7/16-inch extension socket on apowered or manual ratchet wrench.Extensions up to 2 feet long areavailable to extend his or her reach.Multi-setting torque limitersprevent over-tightening of fastenersor latch systems.

For units with bolts or screws thatare not captive in the ORU frame,astronauts use tools fitted with

socket capture fittings and speciallydesigned capture tools so thatnothing floats away in the weight-less space environment. To gripfasteners in hard-to-reach areas,they can use wobble sockets.

Some ORU electrical connectorsrequire special devices, such as aconnector tool, to loosen circularconnectors. If connectors have nowing tabs, astronauts use a specialtool to get a firm hold on the

connectors rotating ring.

Portable handles have beenattached to many larger ORUs tofacilitate removal or installation.Other tools and crew aids includetool caddies (carrying aids), tethers,transfer bags and a protective coverfor the Low Gain Antenna (LGA).

When working within theTelescopes aft shroud area, astro-nauts must guard against opticscontamination by using specialtools that will not outgas or shedparticulate matter. All tools arecertified to meet this requirement.

Astronauts of Servicing Mission 3B

NASA carefully selected andtrained the SM3B STS-109 crew(see Fig. 2-8). Their unique set ofexperiences and capabilities makesthem ideally qualified for thischallenging assignment. Brief biog-raphies of the astronauts follow.

Scott D. Altman,NASA Astronaut(Commander, USN)

Scott Altman of Pekin, Illinois, iscommander of SM3B. He receiveda bachelor of science degree inaeronautical and astronauticalengineering from the Universityof Illinois in 1981 and a master ofscience degree in aeronauticalengineering from the NavalPostgraduate School in 1990.

Altman has logged over 4000flight hours in more than 40 types

of aircraft, and over 664 hours inspace. He was the pilot on STS-90in 1998, a 16-day Spacelab flight.He also was the pilot on STS-106in 2000, a 12-day mission toprepare the International SpaceStation for the arrival of its firstpermanent crew. Altman was oneof two operators of the robot armtransporting the EVA crew duringthe STS-106 space walk. Altmanwill command the crew of STS-109

for SM3B and serve as the alternateRMS operator.

Duane G. Digger Carey,NASA Astronaut(Lieutenant Colonel, USAF)

Duane Carey, Columbia pilot onSM3B, is from St. Paul, Minnesota.He received a bachelor of sciencedegree in aerospace engineering and

mechanics and a master of sciencedegree in aerospace engineeringfrom the University of Minnesota-Minneapolis in 1981 and 1982,respectively. Carey flew the A10Aduring tours in England, Louisianaand the Republic of Korea and theF-16 in Spain. He worked as an

F-16 experimental test pilot andSystem Safety Officer at EdwardsAir Force Base. He has logged over3700 hours in more than 35 typesof aircraft. Carey was selected as anastronaut candidate by NASA in1996 and, having completed 2 yearsof training and evaluation, hasqualified for flight assignment as apilot on STS-109.

Nancy Jane Currie, Ph.D.,NASA Astronaut

(Lieutenant Colonel, USA)

Nancy Currie, the RMS operatoron SM3B, is from Troy, Ohio.Currie received her bachelor of artsdegree in biological science fromOhio State University in 1980, amaster of science degree in safetyfrom the University of SouthernCalifornia in 1985 and a doctoratein industrial engineering from theUniversity of Houston in 1997. AMaster Army Aviator, she has

logged 3900 flying hours in avariety of rotary and fixed wingaircraft. She was selected by NASAin 1990 and became an astronautafter completion of her training in1991. Currie has logged over 737hours in space. She was a missionspecialist on STS-57 in 1993, STS-70in 1995 and STS-88 in 1998.

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

John Grunsfeld is an astronomerand an EVA crewmember (EV1 onEVA Days 1, 3 and 5) on the SM3Bmission. He was born in Chicago,Illinois. Grunsfeld received a bach-elor of science degree in physicsfrom the Massachusetts Institute ofTechnology in 1980 and a master ofscience degree and a doctor ofphilosophy degree in physics from


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Fig. 2-8 The STS-109 mission has seven crewmembers: (clockwise from top) Commander Scott D. Altman,

Pilot Duane G. Digger Carey, Mission Specialist Nancy Jane Currie, Mission Specialist John M. Grunsfeld,

Mission Specialist Richard M. Linnehan, Mission Specialist James H. Newman and Mission Specialist

Michael J. Massimino.

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the University of Chicago in 1984 and 1988, respec-tively. Grunsfeld reported to the Johnson Space Centerin 1992 for a year of training and became qualified forflight selection as a mission specialist. He has loggedover 835 hours in space. On his first mission, STS-67 in1995, Grunsfeld and the crew conducted observationsto study the far ultraviolet spectra of faint astronomicalobjects and the polarization of ultraviolet light coming

from hot stars and distant galaxies. Grunsfeld flew onSTS-81 in 1997 on the fifth mission to dock withRussias Space Station Mir and the second to exchangeU.S. astronauts. Grunsfelds latest flight was aboardSTS-103 in 1999 where he performed two space walksto service Hubble on SM3A.

Richard M. Linnehan, DVM, NASA Astronaut

Rick Linnehan is a doctor of veterinary medicine andan EVA crewmember (EV2 on EVA Days 1, 3 and 5) onSM3B. He was born in Lowell, Massachusetts.Linnehan received a bachelor of science degree in

Animal Sciences from the University of NewHampshire in 1980 and his DVM degree from the OhioState University College of Veterinary Medicine in1985. Linnehan reported to the Johnson Space Centerin 1992 for a year of training and became qualified forflight selection as a mission specialist. He has logged786 hours in space. His first mission was aboard theSTS-78 Life and Microgravity Spacelab, the longestSpace Shuttle mission to date (17 days). This missioncombined both microgravity studies and a life sciencespayload. STS-90 was his second Spacelab mission.During the 16-day flight, Linnehan and the crew served

as both experimental subjects and operators for 26 indi-vidual life science experiments focusing on the effectsof microgravity on the brain and nervous system.

James H. Newman, Ph.D., NASA Astronaut

Jim Newman is an EVA crewmember (EV1 on EVADays 2 and 4) on SM3B. He was born in the TrustTerritory of the Pacific Islands (now the FederatedStates of Micronesia), but considers San Diego,California, to be his hometown. Newman received abachelor of arts degree in physics (graduating cumlaude) from Dartmouth College in 1978, and a master

of arts degree and a doctorate in physics from RiceUniversity in 1982 and 1984, respectively. Selected byNASA in 1990, Newman flew as a mission specialiston STS-51 in 1993, STS-69 in 1995 and STS-88 in1998. He has logged over 32 days in space, includingfour space walks. On STS-51, Newman and the crewdeployed the Advanced Communications TechnologySatellite and the Orbiting and Retrievable Far andExtreme Ultraviolet Spectrometer on the Shuttle PalletSatellite. On STS-69, Newman and the crew deployedand retrieved a SPARTAN satellite and the Wake Shield

Facility. On STS-88, the first International SpaceStation assembly mission, Newman performed threespace walks to connect external power and dataumbilicals between Zarya and Unity.

Michael J. Massimino, Ph.D., NASA Astronaut

Mike Massimino is an EVA crewmember (EV2 on EVA

Days 2 and 4) on the SM3B mission. He was born inOceanside, New York. He attended ColumbiaUniversity, receiving a bachelor of science degree inindustrial engineering with honors in 1984. He alsoreceived master of science degrees in mechanical engi-neering and in technology and policy, a mechanicalengineering degree and a doctorate in mechanical engi-neering from the Massachusetts Institute ofTechnology (MIT) in 1988, 1990 and 1992, respec-tively. Massimino was selected as an astronaut candi-date by NASA in 1996 and, having completed 2 yearsof training and evaluation, is qualified for flightassignment as a mission specialist. STS-109 will be

Massiminos first space flight, where he will performtwo space walks to service the HST.

Servicing Mission Activities

After berthing the Telescope on Flight Day 3 of SM3B,the seven-person Columbia crew will begin an ambi-tious servicing mission. Five days of EVA tasks arescheduled. Each EVA session is scheduled for 6 hours(see Fig. 2-9).

Rendezvous With Hubble

Columbia will rendezvous with Hubble in orbit 315nautical miles (504 km) above the Earth. Prior toapproach, in concert with the Space TelescopeOperations Control Center (STOCC) at GSFC,Mission Control at JSC will command HST to stowthe High Gain Antennas (HGA) and close the aperturedoor. As Columbia approaches the Telescope,Commander Altman will control the thrusters toavoid contaminating HST with propulsion residue.During the approach the Shuttle crew will remain inclose contact with Mission Control.

As the distance between Columbia and HST decreasesto approximately 200 feet (60 m), the STOCC groundcrew will command the Telescope to perform a finalroll maneuver to position itself for grappling. TheSolar Arrays (SA) will remain fully deployed parallel toHubbles optical axis.

When Columbia and HST achieve the proper position,Mission Specialist Currie will operate the robotic armto grapple the Telescope. Using a camera mounted atthe berthing ring of the FSS platform in the cargo bay,


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

Once the Telescope is secured, the crew will remotelyengage the electrical umbilical and switch Hubble frominternal power to external power from Columbia. PilotCarey will then maneuver the Shuttle so that the HSTSAs face the Sun, recharging the Telescopes sixonboard nickel-hydrogen (NiH2) batteries.

Extravehicular Servicing ActivitiesDay by Day

Each EVA servicing period shown in Fig. 2-9 is aplanning estimate; the schedule will be modified as

needed as the mission progresses. During the EVAs,HST will be vertical relative to Columbias cargo bay.Four EVA mission specialists will work in two-personteams on alternate days. John Grunsfeld and RickLinnehan comprise one team, and Jim Newman andMike Massimino the other.

One astronaut, designated EV1, accomplishes prima-rily the free-floating portions of the EVA tasks. Hecan operate from a PFR or while free floating. Theother astronaut, EV2, works primarily from an MFR

mounted on Columbias robotic arm (RMS), removing

and installing the ORUs on the Hubble. EV1 assistsEV2 in removal of the ORUs and installation of thereplaced units in the SM3B carriers.

To reduce crew fatigue, EVA crewmembers swapplaces once during each EVA day: the free floatergoes to the RMS MFR and vice versa. InsideColumbias aft flight deck, the off-shift EVAcrewmembers and the designated RMS operatorassist the EVA team by reading out procedures andoperating the RMS.

EVA Day 1: Replace V2 Solar Array and Diode

Box Assembly and install Diode Box Controllercross-strap harness.

At the beginning of EVA Day 1 (the fourth day of themission), the first team of EVA astronauts, Grunsfeldand Linnehan, suit up, pass through the Columbiaairlock into the cargo bay and perform the initialsetup. To prevent themselves from accidentallyfloating off, they attach safety tethers to a cablerunning along the cargo bay sills.

6-hour EVA period

EVA

1

EVA2

EVA3

EVA4

UnschEVA

Contingencies (unscheduled)

EVA5

Hubble Space TelescopeHST Development Project

SA and Diode Box

-V2

HGA Deploy**

Setup

:55

HST SM3B EVA Scenario

Reboost**

r

ACS-V2

NCS/ESM-V2

PCUcleanup

SA and Diode Box

+V2

PCU-V3

PCU-V3

Priority Task Times

1. RW 1:052. -V2 SA-3/Diode Box 4:352. +V2 SA-3/Diode Box 4:052. Diode Box Controller3. PCU Prep3. PCU 5:353. PCU Cleanup 0:404. ACS 2:505. NCS/ASCS (CASH) 0:155. NCS/ASCS (ESM) 1:305. NCS (NCC) 2:305. NCS (CPL and radiator) 2:35

6. RSU 2:307. MLI Repair 5 and 6 1:007. MLI Repair 7 and 8 1:05

RW

Close

:30

NCS/NCC

+V2-V3

Set

:30

NCS/CPL/radiator

+V2-V3

PCUPrep

PCUPrep

DBCconn

Set:15

Close:40

R.MF

RPCUPrep

PCUPrep

M

F

R

M

F

R

Set:15

Set

:15

CASH

Close

:30

Closeout1:00

M

F

R

Close:30

DBCConn

Goddard Space Flight Center

PCU

NOBL

-V3

-V2 +V2

+V3SA-3ACS

ASCS

SA-3NCS

Fig. 2-9 Detailed schedule of extravehicular activities during SM3BK1175_209


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Grunsfeld (EV1) does varioustasks to prepare for that daysEVA servicing activities. Theseinclude deploying the ASIPEmini-Translation Aid (TA),deploying the port and starboardTAs as required, removing theMFR from its stowage location

and installing it on the RMSgrapple fixture, installing theLow Gain Antenna ProtectiveCover (LGAPC), removing theBerthing and Positioning System(BAPS) Support Post (BSP) fromits stowage location andinstalling it on the FSS, andinspecting the P105 and P106umbilical covers. Meanwhile,Linnehan (EV2) brings out of theairlock the Crew Aids and Tools(CATs) and installs the MFR

handrail to the MFR on the RMS.

The BSP is required to dampenthe vibration that the servicingactivities will induce into thedeployed SAs. Prior to the BSPinstallation, the IVA teamcommands the HST to an 85-degree pivot angle. The twocenter push-in-pull-out (PIP) pinsare installed each day andremoved each night in case the

Shuttle must make an emergencyreturn to Earth. EV1 removes theBSP from its stowage position inthe FSS cradle, and then installsone end to the BAPS ring with aPIP pin and the aft end to theFSS cradle with another PIP pin.Finally the BSP is commanded toits 90-degree limit and the twocenter PIP pins are installed.

After the initial setup, the EVAcrew will replace the V2 Solar

Array and Diode Box Assemblyon the Telescope. They will alsoinstall the Diode Box Controller(DBC) cross-strap harness. FirstEV1, who is free floating,retrieves the HST PFR and APEand transfers them to EV2 in theMFR. EV2 moves to the HST andinstalls the PFR on HST footrestraint receptacle 8 for the freefloaters use. EV1 translates to

the RAC to retrieve the DBCcross-strap harness and a PortableConnector Tray, and temporarilystows them on the Telescope.Then he ingresses the PFR.Together the astronauts retractthe V2 SA2 PrimaryDeployment Mechanism (PDM).

EV1 then engages the PDM lockand installs the PortableConnector Tray. While still in thePFR, EV1 demates the SA2connectors from the DBA whileEV2 retrieves the WFPC Coverand installs it on the V3 AftShroud in support of the PCUchange-out on EVA Day 3.

Next the astronauts remove theV2 SA2 from the Telescope.They disengage the SADA

Clamp, remove SA2, translate itto the RAC and install it on thestarboard shelf via the SADAClamp and forward constraintPIP pin mechanical attachments.

EV1 translates back to theTelescope and removes the V2DBA by disengaging theremaining X-connector drivemechanism and releasing thefour J-hook bolts while EV2

retrieves the DBA2 from theRAC and translates it to EV1 atthe Telescope worksite. Theastronauts swap hardware andEV1 installs the DBA2 on theTelescope while EV2 translates tothe RAC with the DBA andinstalls it and closes its thermalcover. EV1 installs the DBCcross-strap harness onto theTelescope and mates it to theV2 DBA2.

With the DBA2 now installed onthe Telescope, the astronautsbegin the installation work forthe replacement Solar Array.Both translate to the RAC. EV2disengages Latch 5, deploys themast and engages the two mastbolts. EV1 ingresses the aft PFR,releases and pivots Latch 3 toclear the tang, disengages thetwo tang bolts, stows the tang

and engages the two tang bolts.EV2 disengages Latch 2. EV1pivots Latch 3 to the stowedposition and installs the PIP pin,deploys the MLI flap over thetang interface and releases Latch4. EV1 stabilizes SA3 while EV2releases Latch 1. The astronauts

then remove SA3 from the RAC.

Both crewmembers install SA3onto the Telescope by properlyorienting SA3 and inserting theSADA into the SADA Clampuntil the three soft dock tangsengage. EV1 engages the SADAClamp closed and mates the SA3electrical interfaces. EV2 trans-lates back to the RAC andperforms the SA2 close-out work:engaging the aft latch, the

forward latch and the twoforward constraint bolts.

Then the astronauts deploy theSA3 panel, engage the panellocking bolts and release the SA3brake. EV1 routes the DBC cross-strap harness to the +V2 side,removes the HST PFR andtemporarily stows it on the

ASIPE, and removes and stows aPortable Connector Tray on the

RAC. Meanwhile, EV2 maneu-vers to the V3 aft shroud andinstalls the two FHST covers inpreparation for the PCU change-out on EVA Day 3.

At this time, the astronautsperform the MFR swap:Grunsfeld ingresses the MFR andLinnehan becomes the free floater.EV1 (the free floater) translates tothe ASIPE, retrieves the PFR fromtemporary stowage and transfers

it to EV2, who installs it in footrestraint receptacle 19 in prepara-tion for EVA Day 2. EV1 retrievesthe Bay 10 Thermal Cover andinstalls it over Bay 10 of theTelescope while EV2 disengagesand removes the Telescopes +V2trunnion EPS panel, mates theDBC cross-strap harness andinstalls an MLI tent over the EPSpanel cavity.


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For the daily close-out, EV1inspects the FSS main umbilicalmechanism, disengages the twocenter PIP pins on the BSP,retracts the mini-TA, retracts theport and starboard TAs ifrequired, and takes a tool inven-tory. Meanwhile EV2 prepares

the CATs installed on the MFRhandrail for return into theairlock and egresses the MFR.EV1 releases the MFR safetytether from the grapple fixturefor contingency Earth return.

After completing the EVA Day 1tasks, both astronauts return tothe airlock and perform theairlock ingress procedure.

EVA Day 2: Replace +V2 SolarArray and Diode Box

Assembly and Reaction WheelAssembly 1 (RWA-1)

During EVA Day 2, Newman(EV1) and Massimino (EV2) willreplace the +V2 Solar Array andDiode Box Assembly on theTelescope and complete the DBCinstallation by mating it to the+V2 SA3. They also will replacethe RWA-1.

Fewer daily setup tasks arerequired for EVA Day 2 than forEVA Day 1. After completing theairlock egress procedure, EV1reconnects the safety strap on theMFR, installs the two BSP centerPIP pins and deploys the mini-TA. EV2 exits the airlock withthe EVA Day 2 required CATsinstalled on the MFR handrailand installs the MFR handrail.

After completing the daily setup

tasks, the astronauts begin thetasks for the +V2 Solar Arrayand Diode Box Assemblychange-outs, which are similarto the V2 Solar Array andDiode Box Assembly change-outsperformed during EVA Day 1.First EV1 and EV2 retrieve theHST PFR and APE and installthem on HST foot restraintreceptacle 19. EV1 translates to

the RAC to retrieve a PortableConnector Tray and temporarilystows it on the Telescope. Thenhe ingresses the PFR.

Together the astronauts retractthe +V2 SA2 PDM. EV1 thenengages the PDM lock and

installs the Portable ConnectorTray. Still in the PFR, EV1demates the SA2 connectorsfrom the DBA while EV2 disen-gages five of six bolts on eachdoor of Telescope Bays 2, 3 and 4in support of the PCU change-out on EVA Day 3.

Next the astronauts remove the+V2 SA2 from the Telescope.They disengage the SADAClamp, remove SA2, translate it

to the RAC and install it on theport shelf via the SADA Clampand forward constraint PIP pinmechanical attachments.

EV1 translates back to theTelescope and removes the +V2DBA by disengaging the remainingX-connector drive mechanism andreleasing the four J-hook boltswhile EV2 retrieves the DBA2 fromthe RAC and translates it to EV1 at

the Telescope worksite. The astro-nauts swap hardware and EV1installs the DBA2 on the Telescopewhile EV2 translates to the RACwith the DBA and installs it andcloses its thermal cover.

With the +V2 DBA2 nowinstalled on the Telescope, theybegin installation work for thereplacement Solar Array. Bothastronauts translate to the RAC.EV2 disengages Latch 5, deploys

the mast and engages the twomast bolts. EV1 ingresses theforward PFR, releases and pivotsLatch 3 to clear the tang, disen-gages the two tang bolts, stowsthe tang and engages the two tangbolts. EV2 disengages Latch 2.EV1 pivots Latch 3 to the stowedposition and installs the PIP pin,deploys the MLI flap over the tanginterface and releases Latch 4.

EV1 stabilizes SA3 while EV2releases Latch 1. Both removeSA3 from the RAC.

Working together, the astronautsinstall SA3 onto the Telescope byproperly orienting SA3 andinserting the SADA into the

SADA Clamp until the three softdock tangs engage. EV1 engagesthe SADA Clamp closed andmates the SA3 electrical inter-faces, then mates the DBC cross-strap harness to the +V2 DBA2.EV2 translates back to the RACand performs the SA2 close-outwork: engaging the aft latch, theforward latch and the twoforward constraint bolts.

Both astronauts work together

again to deploy the SA3 panel,engage the panel locking boltsand release the SA3 brake (seeFig. 2-10). EV1 removes the HSTPFR and APE and stows them onthe FSS, and removes and stowsthe Portable Connector Tray onthe RAC.

Upon completion of the SAchangeout task, the EVA crewwill replace the RWA-1. EV1

translates to the LOPE on the aftstarboard side of the MULE,opens the lid, removes the twoRWA1-R wing tab connectorsfrom the LOPE pouch andsecures them to the RWA1-Rhandle Velcro, disengages thethree keyway bolts, removes thereplacement RWA-1 (RWA1-R)and translates to the top of thestarboard MULE.

EV2 maneuvers to Bay 6 and

opens the Bay 6 door, dematesthe two RWA-1 wing tab heaterconnectors from the heaterbracket, demates the two RWA-1wing tab connectors fromRWA-1, disengages the threeRWA-1 keyway bolts andremoves RWA-1 from HST Bay 6.Then he maneuvers to thestarboard MULE location andperforms an RWA swap with EV2.


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EV1 maneuvers with RWA1-R to the Bay 6 worksite,installs it on HST, engages the three keyway boltsand mates the four wing tab electrical connectors.Then he closes the Bay 6 door.

After transferring the RWA1-R to EV2 and receivingRWA-1 from EV2, EV1 translates back to the LOPE,installs the RWA-1 in the LOPE, engages the threekeyway bolts, stows the two wing tab connectors inthe LOPE pouch and closes the LOPE lid.

EV1 retrieves the Bay 5 Thermal Cover and installsit in the retracted position on the Telescope Bay 5 inpreparation for the PCU change-out on EVA Day 3.EV1 also retrieves the doorstop extensions andinstalls them on the +V2 aft shroud doorstops inpreparation for the NCS Radiator installation onEVA Day 5.

For the daily close-out, EV1 inspects the FSS main

umbilical mechanism, disengages the two center PIPpins on the BSP, retracts the mini-TA, retracts theport and starboard TAs if required and takes a toolinventory. Meanwhile EV2 prepares the CATsinstalled on the MFR handrail for return into theairlock and egresses the MFR. EV1 releases the MFRsafety tether from the grapple fixture for contin-gency Earth return. After completing the EVA Day 2tasks, both astronauts return to the airlock andperform the airlock ingress procedure.

EVA Day 3: Replace PCU.

During EVA Day 3, Grunsfeld (EV1) and Linnehan(EV2) will replace the PCU in the Telescope Bay 4.

After the airlock egress procedure, EV1 reconnectsthe safety strap on the MFR, installs the two BSPcenter PIP pins and deploys the mini-TA. EV2 exits

the airlock with the EVA Day 3 required CATsinstalled on the MFR handrail and installs the MFRhandrail.

Both astronauts complete the daily setup tasks, thenbegin the PCU change-out. EV1 translates to theRAC to retrieve the Power Distribution Unit (PDU)fuse plug caddy and battery stringers and transfersthem to EV2. EV2 translates to the Telescope Bay 3,opens the bay door, demates the three batteryconnectors, installs caps to deadface the batterypower and temporarily closes the door. He thentranslates to Bay 2 and performs the same procedure

for the Bay 2 battery.

Meanwhile EV1 translates to Bay 5 and deploys thethermal cover, retrieves the DBA thermal cover,translates to the +V2 DBA2 and installs its thermalcover. Then he translates to Bay 10 and deploys thethermal cover, retrieves the DBA thermal cover,translates to the -V2 DBA2 and installs its thermalcover. EV1 deploys the FHST covers on theTelescope, then translates to the SAC, retrieves theHarness Retention Device and transfers it to EV2 atthe Bay 4 worksite.

EV2 opens the Bay 4 door and installs the HarnessRetention Device and door stay. EV2 removes the sixinboard PDU Fuse Plugs to gain sufficient access tothe PCU connectors on the left side. EV1 retrievesthe PCU handhold from the SAC and temporarilystows it by the +V2 trunnion. Then he translates tothe airlock and recharges his suit with oxygen,enabling him to extend his EVA time. EV2 disen-gages seven of 10 PCU keyway bolts and demates allbut the last six connectors (30).

At this point, EV1 and EV2 perform the MFR

swap. EV2 completes demating the remainingPCU connectors, installs the PCU handhold,disengages the three remaining bolts, disengagesthe PCU groundstrap and removes the PCU fromthe Telescope.

EV1 translates to the starboard SAC where thereplacement PCU (PCU-R) is located, ingresses thePFR, opens the thermal cover, disengages the sixkeyway bolts and removes the PCU-R from the SAC.

Fig. 2-10 Deployment of new rigid solar array

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EV1 and EV2 swap boxes at the SAC worksite. EV2translates with the PCU-R back to the Telescopeworksite, installs it, engages seven keyway bolts andengages the groundstrap (see Fig. 2-11). EV1 stowsthe PCU on the SAC, engages the six keyway bolts,retightens the two PCU handhold wing bolts,egresses the PFR and reinstalls the PCU thermalcover. He then translates to the airlock and recharges

his suit with oxygen. EV2 mates the 36 connectorson the PCR-R, a difficult and time-consuming task.

EV1 inspects the Telescope exterior handrails to beused for the ACS and NCS tasks on EVA Days 4 and5 and, if required, installs handrail covers. EV2 rein-stalls the PDU fuse plugs, removes the HarnessRetention Device, removes the door stay and closesthe Bay 4 door with one J-bolt. He re-opens theBay 3 door, remates the battery connectors andcloses the door with one J-bolt. Then he performsthe same procedure for the Bay 2 battery. After thePDU fuse plugs are reinstalled, EV1 translates to the

+V2 DBA2, retrieves the thermal cover, stows it onits Bay 5 thermal cover stowage pouch and retractsthe Bay 5 thermal cover. He translates to the -V2DBA2, retrieves the thermal cover, stows it on itsBay 10 thermal cover stowage pouch and retracts theBay 10 thermal cover. Next EV1 retrieves theHarness Retention Device and stows it on the SAC.Then he retracts the FHST covers, receives the PDUfuse plug caddy and battery stringers from EV2, andstows them on the RAC. If time allows, EV2removes the WFPC thermal cover and stows it onthe SAC.

For the daily close-out, EV1 inspects the FSS mainumbilical mechanism, disengages the two center PIPpins on the BSP, retracts the mini-TA, retracts theport and starboard TAs if required and takes a toolinventory. Meanwhile EV2 prepares the CATsinstalled on the MFR handrail for return into theairlock and egresses the MFR. EV1 releases the MFRsafety tether from the grapple fixture for contin-

gency Earth return. After the completion of the EVADay 3 tasks, both astronauts return to the airlockand perform the airlock ingress procedure.

EVA Day 4: Replace FOC with ACS, install ESMand perform PCU cleanup tasks.

During EVA Day 4, Newman (EV1) andMassimino (EV2) will replace the Faint ObjectCamera (FOC) with the ACS, install the ESM inthe Telescope aft shroud and do the remainingPCU cleanup tasks. After the airlock egress proce-dure, EV1 reconnects the safety strap on the

MFR, installs the two BSP center PIP pins anddeploys the mini-TA. EV2 exits the airlock withthe EVA Day 4 required CATs installed on theMFR handrail and installs the MFR handrail.

The astronauts complete the daily setup tasks,then begin the FOC/ACS change-out. EV1 deploysthe aft fixture, retrieves the COSTAR Y-harnessfrom the RAC port ATM and stows it on theTelescope aft shroud. EV2 opens the V2 aftshroud doors. EV1 and EV2 work together toremove the FOC from the Telescope. EV1 demates

the four FOC connectors, disconnects the FOCpurge line and disconnects the groundstrap. EV2disengages the FOC A-Latch and EV1 disengagesthe FOC B-Latch. Then EV2 removes the FOCfrom the Telescope and stows it on the aft fixture.

EV1 and EV2 now work together to install theCASH. Even though the CASH is part of the NCSinstallation, it is installed now to maximize EVAtimeline efficiencies and eliminate the need to openthe V2 aft shroud doors a second time on EVA Day 5.EV1 and EV2 retrieve the CASH from the SAC andinstall it on handrails inside the aft shroud.

EV1 and EV2 retrieve the ACS from the ASIPE. EV1configures the aft ASIPE PFR, opens the ASIPE lid,disconnects the ACS groundstrap and deploys theB-Latch alignment aid. EV2 disengages the A-Latchand EV1 disengages the B-Latch. They both removethe ACS from the ASIPE. EV1 closes the ASIPE lidand engages one lid latch to maintain thermalstability inside the ASIPE. The astronauts continue towork together to install the ACS into the Telescopeaft shroud (see Fig. 2-12). They insert the ACS alongthe guiderails, deploy the B-Latch alignment aid arm,

Fig. 2-11 Change-out of Power Control Unit

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engage the B-Latch and A-Latch, stow the alignmentaid, tether the ESM groundstrap to the ACS handrail,reinstall the HST groundstrap and mate the four ACSconnectors.

Next the astronauts install the FOC into the ASIPE.EV2 retrieves the FOC from the aft fixture whileEV1 re-opens the ASIPE lid. EV2 inserts the FOCinto the ASIPE guiderails while EV1 stows the aft

fixture and engages the FOC B-Latch. EV2 engagesthe A-Latch. EV1 disengages the FOC groundstrapbolt and installs the groundstrap on FOC, thencloses the ASIPE lid and engages the five lid latches.

After completing the FOC installation into the ASIPE,the astronauts perform the MFR swap. They retrievethe ESM from the MULE and install it in the V2 aftshroud. Then they install the ACS ESM groundstrapon the ESM, retrieve the Y-harness from temporarystowage, demate the four COSTAR connectors, matefour Y-harness connectors to the COSTAR harnesses,mate four Y-harness connectors to COSTAR and

mate four Y-harness connectors to the ESM. EV2mates the four CASH connectors to the ESM. Nowthey are ready to close the V2 aft shroud doors.

The PCU cleanup task follows the FOC/ACSchange-out and the ESM installation. EV1 removesthe Bay 10 thermal cover and stows it on the ASIPE,then removes the Bay 5 thermal cover and stows iton the ASIPE. He also articulates the aft ASIPE PFRto its landing configuration. Meanwhile, EV2engages the remaining five J-bolts on each door of

Bays 2, 3 and 4. Then the astronauts remove theFHST and WFPC covers from the Telescope andstow them on the SAC.

For the daily close-out, EV1 inspects the FSS mainumbilical mechanism, disengages the two center PIPpins on the BSP, retracts the mini-TA, retracts theport and starboard TAs if required and takes a tool

inventory. Meanwhile EV2 prepares the CATsinstalled on the MFR handrail for return into theairlock and egresses the MFR. EV1 releases the MFRsafety tether from the grapple fixture for contin-gency Earth return. After completing the EVA Day 4tasks, both astronauts return to the airlock andperform the airlock ingress procedure.

EVA Day 5: Install the NCC and NCS Radiator.

During EVA Day 5, Grunsfeld (EV1) and Linnehan(EV2) will install the remaining NCS hardware.

After the airlock egress procedure, EV1 reconnects

the safety strap on the MFR, installs the two BSPcenter PIP pins and deploys the mini-TA. EV2 exitsthe airlock with the EVA Day 5 CATs installed onthe MFR handrail and installs the MFR handrail.

Both astronauts complete the daily setup tasks,then begin the NCS installation. EV2 opens theTelescope +V2 aft shroud doors while EV1 retrievesthe Cryo Vent Line (CVL) bag and NCS sock bagfrom the RAC port ATM and the NCC groundstrapand cryo vent insert from the RAC starboard ATM.Together the astronauts prepare the NICMOS for

the NCS installation. They remove the NICMOSCVL and stow it in the CVL bag, close the NICMOSvent line valve, disengage the NICMOS groundstrapfrom NICMOS, install the NCC groundstrapadapter on NICMOS and install the cryo ventinsert. EV1 retrieves the P600 harness from theRAC starboard ATM. EV2 retrieves the NCC fromthe SAC and opens the neon bypass valve whileEV1 closes the NCC contamination cover.

Both astronauts install the NCC into the Telescopeaft shroud. EV2 installs the NCC groundstrap onNCC and mates the four CASH connectors. EV1

translates to the MULE and releases some of theNCS Radiator latches and shear ties. At this point,they perform the MFR swap.

Next comes retrieval of the NCS Radiator. EV1closes the left aft shroud door and together withEV2 disengages the remaining latches, removesthe NCS Radiator from the MULE and opens theNCS Radiator handrail latches. They install theNCS Radiator onto the exterior of the Telescopeaft shroud.


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Fig. 2-12 Installation of the Advanced Camera for Surveys

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EV1 prepares the NCC by installing the coolant inand coolant out cryo valve heaters and neon lineswhile EV2 installs the NCC power cable to the EPStest panel and reinstalls theMLI tent. They install theNCS Radiator conduitthrough the cryo vent insertopening in the aft bulkheadand engage the cryo ventinsert latches and lockingbolts (see Fig. 2-13). Thenthe NCS Radiator harnessesare mated to the NCS, theNCC saddle thermal coveropened and the CPL evapo-rator removed from thesock and tethered to thebulkhead standoff by EV1.EV2 opens the NCSRadiator diode box, checkssome LEDs and switches,

and closes the diode boxcover. He installs the CPLevaporator in the saddle,installs the saddle cover,engages its two bolts andcloses the NCC saddlethermal cover. Together theastronauts close the aftshroud doors. The crew willthen stow the CVL andNCS sock bags in the RACport ATM.

The final close-out procedure follows the NCS instal-

sts-109 hst servicing mission 3b media reference guide

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