MSC-06900

IO NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

SPACE SHUTTLE

BASELINE ACCOMMODATIONS FOR PAYLOADS

(NASA-TM-X-6864 2) SPACE SHITTLE BASELINE N72ACCOMMODATIONS FOR PAYLOADS (NASA) 27 Jun.1972 69 p CSCL 22BCSCL 22B

G3/31

:::W:::: X:i::::, MANNED SPACECRAFT CENTERHO U STON,TEXAS

JUNE 27, 1972Reproduced by

NATIONAL TECHNICALINFORMATION SERVICE

U S Department of CommerceSpringfield VA 22151

https://ntrs.nasa.gov/search.jsp?R=19720026211 2019-04-29T02:07:29+00:00Z

MSC-06900

SPACE SHUTTLE

BASELINE ACCOMMODATIONS FOR PAYLOADS

JUNE 27, 1972

PREPARED BYPAYLOAD ENGINEERING OFFICE

FUTURE PROGRAMS DIVISIONENGINEERING AND DEVELUPMENT DIRECTuRATE

MANNED SPACECRAFT CENTERHCUSTCN, TEXAS.

Bhia *enims Ray X

Approved: __ _2_. 'f S

Robert F. ThompsonManager, Space Shuttle Program

t~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~\

PRECEDING PAGEBLANK NOT FILMEL

CC'TENTS ,

TITLE

AbboAVIATIONS ANC ACRONYMS '. . . . . .

INTJLUUCTION . * .. . . o o .

* . I

* . a

SPACE ShLTTLE SYSTEM .. .

GENERAL PAYLOAC ACCCMMCATIONS . .

CCINFIGURATIGN OESCRIPTI Ch ..

SPACE SKi2TTLE VEtICLE . . . .

ORBITER VEHICLE .. . . .

OPERATICNS .. . . . . .. . .

PROGRAM CBJECTIVES . * . ...

MISSION PHASES . . . . , ..

SHLTTLE ABCRTS . . . . . . . ...

PERFCRPAINCE . . . . . . . . .

PERFCRIANCE CAPABILITIES . . .

PERFCRMANCE ANALYSIS . . .. . .

PERFCRMANCE DATA .· . . . . . .

SPACE SI-LTTLE/PAYLCAC ACCOMMCDATIONS

GEhERAL . . . . . * . .* . .· . .

OPERATICIAL INTERFACES . . . . .

PRELAUNCH CPERATICNS . . . . . . .

ORBITER PRELAUNCH OPERATIONS . . .

FLIGHT CPERATIONS . . . .

CREW . . . . . .

POSTFLIGHT OPERATIONS ..... .

SYSTEM/SLBSYSTEM INTERFACES . .

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CONTENTS

TITLE PAGE

STRUCTURAL/MECHANICAL INTERFACES . . . . . . . . . 36

FLUIC SYSTEM INTERFACES . . . . . . . . . . . . . 38

ELECTRICAL POWER . , . . . · . . . o * .· . . o . 40

DISPLAYS AND CONTROLS .o . . .· . . .... 40

GUICANCE AND NAVIGATION . .. . . . . . 42

STAEILIZATICh ANC CCNTROL . . . . . . . . . . .. 44

PAYLCAC CFECKOUT . . . . . . . . . . . . .. o 46

COMPLNICATIONS . o . . . . . . . . . . . . . . . 50

CREk SYSTEMS . . o o . . . . . . . . . . . . . . . 52

ENVIGRNMENTAL CCNTROL/LIFE SUPPORT SYSTEM . . . 55

PAYLCAC EAY ENVIRONMENT . . . . . . . . . . . 56

SAFETY, RELIABILITY, AND QUALITY ASSURANCE . . . . 62

SHUTTLE CAFABILITIES . . a. . . . .e I, * . 62

PAYLCAtC . . . . . . . . . . . . . . . . . . . . 62

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F IGURES

TITLE

SPACE SL'iTTLE VEPICLE ...... .a . .

URBITER VEHICLE . . . . .· . . .. o . .

SPACE SFLTTLE fISSICN PROFILE . . . . .

PAYLOAC VERSLS INCLIhAT ION . . . . . . . . .

PAYLOGA VERSLS CIRCULAR ALTITUDE REACkED . .

PAYLOAD VERSLS ELLIPTICAL CReIT ALTITUCE . . .

PAYLOAD VERSUS LCNGITUDINAL C.G. LIMITS o . .

'u(BITER TURNAROUND OPERATICNS TIMELINE .

KEMCTE MANIPULATCOR SYSTEM . . . . . .

KRS LCCAICNS . . . . . . . . . . . . . . .

MISSION SPECIALIST STATION INTERFACE . . .

URBITER/PAYLCAC CI-ECKCUT OF INTERFACE ...

UiBITER/FAYLCAC COMlMUNICATICh INTERFACE . .

Pt.A/PLSS CIPEISICNS ... . . . . ... .

PRESSURE EIRCNMENT . . . . . . . . . . .

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20

21

23

26

28

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45

41

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51

54

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TABLES

TITLE PAGE

i-1 - UPERATIGI CESIGN PARAMETERS FOR DOCKING . .

Z-11A - ORBITER/PAVLCAC COPPUIICATICN INTERFACES .

2-L1[ - ORBITEP/PFiLCAC COPMUNICATICN INTERFACES ,

i-111 - LCADIIG APC CUPPING CPTICNS . . . . . .

,i-V - TYPICAL ,AVIGATICN SYSTEM ACCURACIES . . .

.- V - MINIMUP AtqGILAR STABILITY RATES . . . . .

i-Vi - PRELIMInARY LIMIT LCOAD FACTGRS FOR PAYLCAD

. 0 0 0 * 30

. . . 0. 32

* 0 0 . 0 33

e · · 0 a 39

.. 4 0 43

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vi

ABBREVIATIONS AND ACRONYMS

BPS BITS PER SECOND

bTU/HK BRITISH THERMAL UNITS PER HOUR

C.G. CENTER OF GRAVITY

LRT CATHCDE RAY TUBE

C+W CAUTICN AND WARNING

rOb CECIBEL

DL DIRECT CURRENT

LG/ISEC CEGREES PER SECOND

-CLS5 ENVIRONMENTAL CONTROL LIFE SUPPORT SYSTEM

iVA EXTRAVEHICULAR ACTIVITY

EVLS) EXTRAVEHICULAR LIFE SUPPORT SYSTEM

IPS FEET PER SECOND

G+N GUIDANCE AND NAVIGATION

1N+L GUIDANCE NAVIGATION AND CONTROL

UbS GRCUND SUPPORT EQUIPMENT

IvA INTRAVEHICULAR ACTIVITY

KWH KILOWATT HOUR

KSL KENNEDY SPACE CENTER

LbS PCUNDS

MRI MAINTENANCE AND REFURBISHMENT FACILITY

MsC PANNED SPACECRAFT CENTER

MSS PISSICN SPECIALIST STATION

NASA NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

uMS CRBITAL MANEUVERING SYSTEM

PLu5 PAYLOAD COMMAND DECODER SUBUNIT

PCM PULSE CODE MODULATION

2

PG;A PRESSURE GARMENT ASSEMBLY

PSIA POUND PER SQUARE IhNCH ABSOLUTE

KAU REGICNAL ACQUISITICN UNIT

iLt. REACTION CONTROL SYSTEM

hK RADIOC FREQUENCY

KI.-P REQUEST FOR PROPOSAL

hMj REMOTE MANIPULATOR SYSTEM

IePC REMCTE POWER CONTRCLLER

RTIA RANGE TOWER TRANSFER ASSEMBLY

SU L,; SPACE GROUND LINK SYSTEM

ePP STCRED PROGRAM PROCESSOR

SPH SCLID ROCKET MOTOR

S:PU SPACE SHUTTLE PROGRAM OFFICE

STUIh SPACE TRACKING AND DATA NETWORK

Tou TO BE DETERMINED

TlRS TRACKING AND DATA RELAY SATELLITE SYSTEM

TLM TELEMETRY

lv TELEVISICN

UV LLTRAVIOLET

VAb VERTICAL ASSEMBLY BUILDING

Vui, VCLT DIRECT CURRENT

VH- VERY HIGH FREGUENCY

xATK TRANSMITTER

F DEGREE FAHRENHEIT

3

INTRODUCTION

THIS D'X.UMENT DESCRIBES THE SPACE SHUTTLE SYSTEM AS ITRELATtS TO PAYLCADS. ITS PURPOSE IS TO PROVIDE POTENTIALUSERS UF THE SPACE SHUTTLE WITH A UNIFORM BASE OF[INUKMATION CN THE ACCOMMODATIONS BETWEEN THE PAYLOAD ANDTHE SHUTTLE. BY UTILIZING THIS INFORMATICN, PRELIMINARYPAYLUAU PLANNING AND DESIGN STUDIES CAN BE EVALUATED ANDLUMPARtU AGAINST A COMMON SET OF SHUTTLE/PAYLOADAIC.U4MHuATIONS. THIS INFCRMATION ALSO MINIMIZES THENEtCSSITY FOR EACH PAYLOAD STUDY TO DEVELOP INFORMATION ONTHt SHUTTLE CCNFIGURATION.

THIS DOCUMENT DESCRIBES A BASELINE CONFIGURATION OF THESPAL;E SHUTTLE SYSTEM WHICH I S CONSISTENT WITH CURRENTPRU4tkAM REQUIREMENTS APPROVED BY THE SPACE SHUTTLE PROGRAMUFFItI, HOWEVER, IT SHOULD NOT BE CONSIDERED AS A SHUTTLEPRUGKAM CCNTROL CR REQUIREMENTS COCUMENT.

THLt SPALE SHUTTLE PRCGRAM REQUEST FOR PROPOSAL (RFP) NUMBER9-bC4AL-b7-2-40P RELEASED TC INDUSTRY ON MARCH 17. 1972,wITH ANY SUBSE(iUENT PROVISIONS, IS THE PRIMARY AND.UNItRULLING SOURCE DOCUMENT FOR THIS ISSUE. PARTS OF THERFP AREi REPEATED WITHIN BOTH FOR CONTINUITY AND TO ELIMINATETHt NttU FOR MANY OF THE PAYLOADS COMMUNITY TO REQUEST THEKF P,

SUMMARY LEVEL INFORMATION ON SPACE SHUTTLE CONFIGLRATION,PRkELIMINARY, PERFORMANCE DATA, ANC OPERATION PHILOSOPHY AREokikbLY DESCRIBEC. INFORMATION CN PAYLOAD INTERFACES, ASkcLATtD TO SHUTTLE CPERATIONS, SUBSYSTEMS, ENVIRONMENT,SAFETY, AND SUPPCRT EQUIPMENT, IS ALSO INCLUDED. THE SPACESHUTTLC PRELIMINARY GESIGN PHASE TO BE INITIATED SCCN WILLPkuVIJ: INDEPTH INFORMATION CN ORBITER CHARACTERISTICS.

,URitSPUNDENCE REGARDING LEVEL I PROGRAM REQUIREMENTS,iGUIUELINEt AND PLANNING SHOULD BE ADDRESSED TO NASA HQ.llctS RELATIVE TO GENERAL PRCGRAM REQUIREMENTS ANDINTiLRGENTER PROGRAM INTERACTIONS SHOULD BE ACDRESSE 10TO THEMSL SPALE SHUTTLE PRCGRAM OFFICE. INFORMAL COMMENTS ANDwUltSTIUlS ON TECHNICAL DETAILS SHOULD BE ADDRESSED TO THE'l31L PAYLOADS ENGINEERING OFFICE. PLEASE DIRECT THEINiUlKjiktS TO ThE FGLLOWING INDIVIDUALS-

J. L. HAMMERSMITHPAYLCAD OFFICE COCE MHLSPACE SHUTTLE PROGRAMNASA HQWASHINGTCN C.C. 20546202-755-8636

J., C. hEBERLIGPAYLOADS COOCRDINATION OFFICE CODE LA13NASA-PtSCHOUSTCN, TEXAS 77058713-483-237 2

H. P. CAVISPAYLOADS ENGINEERING OFFICE CODE ER4NASA-MSCHGUSTC~N TEXAS 77058713-483-3681

5

SPACE S1UTTLE SYSTEM

GENERAL PAYLOAD ACCOMMODATIONS

CAPABIL ITY/CHARACTERIST IC

STHKU(TURAL/MECHAK ICAL

MAX. PAYLOAD WT.lLAUNC H)

MAX. PAYLOAD WT.(LANU I N5)

PAYLOAD ENVELCPE

PAYLLAU C.G.

OOLKING PORT I.Do

65,000 LBS

40,000 LeS NOMINAL, UP TO 65,000 LBS WITHREDUCED SAFETY FACTORS

15 FT. CIA. BY 60 FT. LENGTH

FIGURE 2.1

1.0 METER

UUCKI i, PARA-METERS

LATERAL YISALIGNMENTANGULAR MISALIGNMENTROLL MI SALIGNMENTCLCSING VELOCITY

+/-C.5 FT.+/-5.0 DEG

7.0 DEG0.5 FPS

PAYLuAD ALIGN-HENT I BAY

tLLLtTRI AL PCWER

VOL TAb t 30 VOC NOMINAL

ORBITER OPERATION PERIODS

ON-ORBIT COAST PERIODS

1000150030006000

WATTS AVG.WATTS PEAKWATTS AVG.WATTS PEAK

50 KWH CEDICATED

REDUNDANT DC EUSSES IN PAYLOAD BAY

i. 00

i.100

1TEM

0.5 DEG

ENEkG Y

6

tLUIUANCE AND NAVIGATION

URbIT NAVIGA-TIUN ALLURACIES

STDNSTAR/HOR IZONGROUND/ BEACONHCRIZON/ eEACONTORSLANDMARK

o000 FT.4000 FT.1000 FT.700 FT.300 TO 1000 FT.2000 FT.

RtHEL.VUUS RANGE

ATTLTUUEPuI{NlI NG ACCURACY

STAbILITY RATE

lATA MANAGEMENT

UMPUTA I CN

UATA TRANSFER

UATA oLiuNL INK

UATA. UPL INK

300 N. MILES WITH COOPERATIVE TARGET

0.5 DEG

TBD

0.5 DEG, 0.1 DEG

10,000 32 BIT WORDS

25,000 BPS VIA DATA BUS

265,000 BPS DIGITAL DATA, TV, ANC VOICE

2,000 BPS

ENVIRUNMENTAL CCNTRCL/LIFE SUPPORT

PtiSUNNtL ACCCP- 4 MEN, 7 CAYS NOMINALMUUATlujiS 42 MAN-DAYS WITHOUT SYSTEM CHANGES

10 MEN WITH MINOR CHANGES30 DAYS iITH, ADCITIONAL CCNSUMMABLES

L.AbIN ATMOSPHERE

hAST. MANAGEMENT

14.7 PSIA20 PERCENT OXYGEN, 80 PERCENT NITROGEN65 DEG - 80 DEG F CONTROLLED TEMPERATUREHUMIDITY CONTROLCCNTAMINATION CCNTROLCARBON DICXIDE CONTROL

WATER STORAGE 24 HOURS

ACIIVt lHERMALLCNTKUL

ORBITER CPERATIONSGO-ORBIT COAST

5200 BTU/HRTBD

PAYLUAD BAY ENVIRONMENT

ALlUUT It. LESS THAN 145 OB OVERALL

7

VIbRATI I UN

ACC:LERAT ION

LAUNCHMAX. BOOSTtNTRY

LESS THAN CURRENT LAUNCH VEHICLE

X y z

1.5+/-1.0 +/-0.25+/-0.5 +/-0.25+/-0.53.0+/-0.25 +/-0.2 +/-0.25 +/-0.3 +/-0.25-1 +/- 0.5+/-0.25 -3 +/-0.5

MIN (DEG F) MAX (DEG F

*PRELAUNCI +40LAUNCH +40CN-ORBIT -100

*EhTRY + POSTLANDING -100

*GSE CCNDITIONAL AIR AVAILABLE

THERMAL

+120+ 150+150+200

8

1..00 CONFIGURATION DESCRIPTION

1.L01O0 SPACE SHUTTLE VEHICLE

THE SPACE SHUTTLE SYSTEM CONSISTS OF AN ORBITERWITH AN EXTERNAL PROPELLANT TANK AND TWO SOLIDROCKET MOTORS (SRM'S). FIGURE 1.1 SHOWS THESHUTTLE SYSTEM AS THE VEHICLES ARE COMBINED FCRTHE LAUNCH AND INITIAL BOOST PHASES OF THEMISSION. ALTHOUGH THE ORBITER VEHICLE ISREUSABLE, ITS PROPELLANT TANKS ARE EXPENDED GNEACH MISSICN.

1.zO'00 ORBITER VEHICLE

THE BASELINE ORBITER IS A MANNED REUSABLEDELTA-WINGED VEHICLE (FIG. 1.2t. CONTAINEDWITHIN THE MAIN FUSELAGE OF THE ORBITER ARE THECREW COMPARTMENT, A PAYLOAD BAY CAPABLE OFACCCMMCDATING SINGLE OR MULTIPLE PAYLOADS UP TO15-FCCT DIAMETER BY 60-FOOT LONG, SUPPORTSUBSYSTEMSt AN ORBITAL MANEUVERING SYSTEM, AND THEMAIN PROPULSION SYSTEM ENGINES. PROTECTIONAGAINST AERODYNAMIC HEATING IS PROVIDEC DURINGASCENT ANC REENTRY BY- AN EXTERNAL THERMALPROTECTICN SYSTEM.

AERCCYNAMIC FLIGHT IS CONTROLLED THROLGH THEELEVCNS AND RUDDER, WHILE SPACE-ATTITUDE CONTROLIS ACCOMPLISHED THROUGH REACTION CONTROL SYSTEMTHRUSTERS WHICH ARE ATTACHED TO THE VEHICLE ASMODULES. TO INSURE PROPER AEROCYNAMIC CONTROLDURING ENTRY AND ATMOSPHERIC FLIGHT PHASES, THELOCATION OF PAYLOAD LONGITUDINAL CENTER-OF-GRAVITYMUST BE MAINTAINED WITHIN SPECIFIED LIMITS.MULTIPLE SETS OF PAYLOAD ATTACHMENT POINTS PROVIDETHE CAPABILITY TC RESTRAIN AND LOCATE THE PAYLOADWITHIN THE ORBITER WITHIN THESE LIMITS.

PAYLOAD HANDLING DURING ORBITAL OPERATIONSNORMALLY IS ACCOMPLISHED BY A STANDARD DEPLOYMENTAND RETRIEVAL MECHANISM. THE CONCEPT SELECTED FORTHIS BASELINE IS A PAIR OF MANIPULATOR ARMSATTACHED TO THE FCRWARC BULKHEAD CF THE PAYLOADBAY. THESE ARMS ARE STOWED BENEATH THE PAYLOADBAY CCORS WHICH OPEN TO DISCLOSE TFE FULL LENGTHAND WIDTH CF THE PAYLOAD BAY. TFE MANIPULATORSPERFORM MULTIPLE FUNCTIONS WHICH INCLUDE PAYLOAD

9

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ERECTICN, DEPLCYMENT, RETRIEVAL, AND STOWAGE BACKIN THE PAYLOAD BAY. MANIPULATORS ALSO CAN SERVETO ASSIST COCKING TPE ORBITER, WITH ANOTHERORBITING ELEMENT. CCNTROL OF MANIPULATORS ISACCOMPLISHED BY AN OPERATOR LOCATED ON THE FLIGHTDECK.

DURING ORBITAL OPERATICNS, PAYLOADS CAN BE DOCKEDTO THE ORBITER, REMAIN WITHIN THE PAYLOAD BAY, ORBE CEPLOYED ANC RELEASED FROM THE ORBITER.AIRLCCKS AND/OR HATCHES ARE PROVIDED TC PERMITSHIRTSLEEVE ACCESS TO PRESSURIZED PAYLOADS ANDPRESSURE SUIT ACCESS TO THE UNPRESSURIZED PAYLOADBAY.

THE ORBITER CREW COMPARTMENT HOUSES THE FLIGHTCREW, PASSENGERS, CONTROLS AND DISPLAYS, AS WELLAS MOCST OF THE AVIONICS AND ENVIRONMENTAL CONTROLSYSTEP. AN UPPER DECK PROVIDES CREW STATIONS TCACCCMPLISH ALL FLIGHT OPERATIONS OF THE ORBITERAND CCNTRCL CF THE MANIPULATOR SYSTEM. PROVISIONSFOR PAYLCAC MCNITCRING, PASSENGER ACCOMMODATION,ELECTRONICS, ANC ENVIRONMENTAL CONTROL/LIFESUPPCRT SYSTEMS ARE INCLUDED ON A LOWER DECK.THE ENTIRE COMPARTMENT IS TEMPERATURE, PRESSURE,HUMIDITY, AND ATMOSPHERE CONTROLLEC TO PROVIDE ASEA LEVEL TYPE 'SHIRTSLEEVE' ENVIRONMENT FOR THEPERSCNNEL AND EQUIPMENT. A CREW OF FOUR CAN BEACCCMMCDATED IN THE PRESSURIZED CABIN FOR ABASELINE MISSION CURATION OF 7 DAYS. UP TO SIXADDITICNAL PERSONS CAN BE ACCOMMODATED FOR SHORTERDURATION PISSIONS WITH MINOR CHANGES TO THE CABININTERIOR. THE ORBITER DESIGN ALSO HAS THECAPABILITY TO EXTEND TFE ORBITAL STAY TIME UP TC30 DAYS. FOR MISSIONS IN EXCESS OF 7 DAYS, THEWEIGHT CF THE EXPENDABLES SHALL BE CHARGED AGAINSTTHE PAYLCAC.

THE CRBITER AVIONICS SYSTEM PROVIDES THE FUNCTIONSFOR GUIDANCE, NAVIGATICN, AND CONTROL (FOR THEORBITER AND FOR THE MATED ORBITER/BOOSTER)iCOMMUNICATIONS, LIMITEC AVIONICS EQUIPMENTPERFCRMANCE MONITCRING AND ONBOARD CHECKOUT,ELECTRICAL POWER DISTRIBUTION, CONDITIONING ANDCONTRCLt TIMING, AND DISPLAYS AND CONTROLS..CERTAIN OF THESE CAPABILITIES CAN BE TIME SHAREDFOR SUPPORT CF PAYLOADS. THESE INCLUDECAPABILITIES FOR ELECTRICAL POWER CISTRIBUTION ANDCGNTROL, MASTER CAUTION AND WARNING, NAVIGATIONALINITIALIZATION, AND COMMUNICATIONS. ORBITERAVICNIC SYSTEM ALSO PROVIDES COMPUTATIONCAPABILITY FOR DATA PROCESSING AND CONTROL FORLIMITED FUNCTIONAL END-TO-END CHECKOUT OF

12

PAYLCAGS.

13

1.O00 OPERATIONS

,. 3010 PROGRAM CBJECTIVES

THE BASIC CBJECTIVES OF THE SPACE SHUTTLE PROGRAMARE TO DEVELOP A SYSTEM WHICH CAN ECONOMICALLYDELIVER PAYLOADS TO ORBIT, PERFORM ORBITALOPERATICNS, RETURN FROM ORBIT, AND BE REFURBISHEDFOR REUSE. THE BASIC CPERATIONAL OBJECTIVE IS TOOPTIMIZE SHUTTLE SUBSYSTEM CESIGN, GROLNODEPENDENCE, AND OPERATIONS CONCEPTS TO PROVIDEMAXIPMU PRCBABILITY OF MISSION SUCCESS AT MINIMUMRRCGRAM CCST. SPECIFIC OPERATIONAL CRITERIA AREAS FCLLChS-

A. LONG TERM CCMBINEC STORAGE AND OPERATIONALSERVICE LIFE

B. TCTAL VEHICLE TURN AROUND TIME FROM ORBITALMISSION LANDING TO LAUNCH READINESS, LESSTHAN 14 CALENCAR CAYS

C. DESIGN REQUIREMENT OF INTACT ABORT

D. BASELINE MISSION DURATION OF 7 DAYS

E. HCRIZCNTAL LANDING

1.0O9O0 MISSION PHASES

BASICALLY, THE MISSION PHASES OF THE SPACE SHUTTLESYSTEM ARE PRELAUNCH, LAUNCH, ASCENT, ORBITALOPERATICNS, DEORBIT ANC LANDING, POSTLANDING, ANDREFURBISHMENT. THESE PHASES REPRESENT THE TYPICALOPERATICNAL SEQUENCE ILLUSTRATED IN FIGURE 1.3.

i.3OzOl PRELAUNCH - PRELAUNCH CPERATIONS START kITH THEINITIAL CHECKOUT AND PREPARATION OF. THE SPACESHUTTLt FCR A PARTICULAR MISSION. PAYLOACDETAILED SUBSYSTEM CHECKOUT AND PREPARATIONS ARECCNDUCTED INDEPENDENT CF THE ORBITER PREPARATIONS,AND ARE CCPPLETED PRIOR TO INSTALLATION OF THEPAYLCAC IN THE ORBITER. UPON COMPLETION OF THEORBITER AND PAYLOCAD INDEPENDENT CHECKS, THEPAYLCAC IS INSTALLEC IN THE ORBITER PAYLCAD- BAY.FOLLCWING PAYLOAC INSTALLATION, PAYLCAD ANDORBITER SYSTEM INTERFACES ARE VERIFIED FCRCONTINUITY AND SAFETY. NEXT, THE ORBITER WITH AN

FIGURE-1.3

(

15

EXTERNAL PROPELLANT TANK IS ATTACHED TO THE SRM 'SAND VEHICLE INTERFACE CHECKS ARE PERFORMED. INTHIS CCNFIGURATICKN THE SPACE SHUTTLE SYSTEM ISMATEC TO THE LAUNCH UMBILICAL TOWER FORTRANSPCRTATICN TO ThE LAUNCH PAD.

1.JaO4U LAUNCH - FOLLOWING TRANSPORTATION TO THE PAD,FINAL LAUNCH READINESS OF THE SPACE SHUTTLE SYSTEMAND FINAL VERIFICATION OF THE PAYLOAD STATUS PLUSLCACING OF ANY TIME CRITICAL ELEMENTS AREACCOPPLISHED. THE CREW AND PASSENGERS ENTER FORTHE TERMINAL COUNTDOWN AND LAUNCH AFTER THEPRCPELLANTS ARE LCADED.

. 30O. .ASCENT - LIFTOFF INITIATES THE MISSION SEQUENCETIMERS, AND THE SRMIS AND ORBITER MAIN ENGINESPROPEL THE SPACE SHUTTLE TO THE -DESIRED STAGINGVELOCITY AND ALTITUDE. AT STAGING, THE SRM'SBURN GUT, AND THE SRM CASES SEPARATE FROM THEORBITER. AFTER THE ORBITER ACHIEVES LOW EARTHORBIT, THE ORBITER MAIN ENGINES ARE SHUT DOWN, THEMAIN TANK IS SEPARATED FROM THE ORBITER, AND THETANK. IS DECRBITEC BY A SMALL RETROROCKET.

1. O.4 GORBITAL CPERAT INS - THE ORBITER ORBITALMANEUVERING SYSTEM (OMS) ENGINES BURN THE ORBITERFRCM THE INSERTION ORBIT TO THE DESIRED ORBITALPOSITICN, CR TO A RENDEZVOUS WITH ANOTHER ORBITINGELEMENT. ATTITUDE CONTROL AND CRITICALTRANSLATION MANEUVERS ARE PERFORMED BY THE ORBITERREACTICh CCNTROL SYSTEM IRCS) THRUSTERS. THE RCSALLOWS THE ORBITER TO MAINTAIN THE DESIRED ORBITALATTITUDE FCR PAYLCAC CPERATIONS, OR TO PERFORMDOCKING MANEUVERS. WHEN THE ORBITER HAS ATTAINEDTHE CESIRED ORBITAL PCSITION AND ATTITUDE, THEPAYLCAD IS REACIED FOR OPERATIONS. PAYLOADOPERATIONS DURING THE ORBITAL MISSION PHASE MAY BEPERFCRMED WITH THE PAYLOAD STILL IN THE PAYLACDBAY, ATTACHED TO THE ORBITER, OR DEPLOYED ANDRELEASEC FROM THE ORBITER. PAYLOAD OPERATIONS,WHICh MAY REQUIRE RADIO FREQUENCY (RFJ AND/ORHARDCLINE INTERFACE BETWEEN THE PAYLOAD, THEGRB'ITER VEHICLE, AND SOMETIMES ThE GROUND, ARECONCERNED WITH SUCH FUNCTIONS AS COMMAND ANDCCNTROL, DATA TRANSFER, MONITORING AND CHECKOUT,TRACKING AND RANGING, AND INSPECTION. PAYLOADOPERATICNS, WHICH NORMALLY REQUIRE SOME PHYSICALINTERFACE EETWEEN THE PAYLOAD AND THE ORBITERVEHICLE, ARE CONCERNEC WITt SUCH FUNCTIONS ASDEPLCYMENT, ERECTION CR RELEASE, LOGISTICS,MAINTENANCE, SERVICING, RETRIEVAL, RETRACTION, ANDSTOWAGE. PAYLOAD DEPLOYMENT AND RETRIEVALOPERATICNS GENERALLY WILL BE ACCOMPLISHED BY

16

REMCTE MANIPULATOR ARMS MOUNTED rT AND SUPPLIED BYTHE ORBITER VEHICLEo THESE ARMS WILL BECCNTRCLLED FROM AN GPERATIONS STATION IN ThEORBITER CREW CABIN WITH VISUAL DISPLAYS.FLGCCLIGHTSe AND PREPRGGRAMEC COMPLTER CONTROLS TCASSIST Tf-E OPERATOR DURING THESE OPERATIONS. FCRPAYLCACS WHICH REMAIN ATTACHED TC THE ORBITER MCCULE DEPLOYMENT WILL BE AVAILABLE IF REQUIRED.IF ERECTICN OR CEPLCYMENT IS REQUIREDe THEMAhIIFULATCRS OR PAYLCAD SUPPLIED SPECIALMECHANICAL SYSTEMS CAN BE USED.

L.0).O: DECRBIT ANC LANCING - UPON COMPLETION OF THEORBITAL CPERATIONS, THE ORBITER IS PREPARED FORDEGREIT ANC ENTRY. THIS EVENT IS INITIATED BY THEFIRING OF THE OMS ENGINES TO PROVIDE SLFFICIENTDELTA-V TC DEORBIT THE ORBITER, AND ORIENTING THEORBITER TC THE PROPER ANGLE CF ATTACK TOACCCOPLISH ENTRY. CURING REENTRYt THE ORBITER ISPROTECTED eY AN EXTERNAL THERMAL PROTECTICN SYSTEMWHICH INSULATES STRUCTURE AND PAYLOAD FROM THEREENTRY AERODYNAMIC HEATING. FOLLOWING REENTRY,THE ORBITER CHANGES ATTITUDE FOR ATPCSPHERICFLIGHT TC THE LANCING SITE. AFTER ACQUISITION CFTHE LANDCING SITE, THE CRBITER MAKES A FINALAPPRCACH AND HORIZCNTAL LANDING.

o.jO£it POST LANDING - FCLLOWING LANCING, THE ORBITER ISTOWEC TC THE SAFING AREA WHERE THE CREW ANDPASSENGERS DISEMBARK. AFTER A CGOLCOWN PERIOD CF(TBD)t CRITICAL PAYLOAC ITEMS MAY BE REMOVED FROMTHE PAYLCAD BAY OR SUPPORTED BY GROUND SUPPORTEQUIPFENT (GSE). THE ORBITER AND PAYLOAD ARE THENDEFUELED AND SAFEC. UPON COMPLETICN OF THE SAFINGOPERATICNSt THE ORBITER IS TOWED TO THEMAINTENANCE AND REFURBISHMENT BUILDING.

.0.01 Q MAINTENANCE AND REFURBISHMENT - IN THE MAINTENANCEAREA A RECCVERED CR NON-CEPLCYED PAYLOAD FROM THEORBITER AND RETURNED TC THE PAYLOAD SERVICE AREA,WHILE SCHEDULED REFURBISHMENT WORK IS STARTEC ChTHE CRbITER SUBSYSTEMS. TYPICAL ITEMS FOR ORBITERREFURBISHMENT INCLUDE SELECT THERMAL PRCTECTICNSYSTEM PANELS, ENVIRCNMENTAL ANC LIFE SUPPORTSYSTEM CANISTERS AND FILTERS, AND ANY MA INTENANCEITEM NOTED DURING FLIGIT. WITH THE COMPLETION CFTHE MAINTENANCE AND REFURBISHMENT WORK, THEORBITER IS PREPAREC FOP THE PRELALNCH OPERATIONSOF THE NEXT MISSION.

17

i. 0300 6HUTTLE ABCRTS

A RECUIREMENT OF TI-E SHUTTLE IS THE INTACT ABORTAND RECCVERY OF THE CREW, ORBITER, AND PAYLOAC.TO FRC¥VIE THIS CAPABILITY, THE SHUTTLE HASSEVERAL ABCRT MODES AVAILABLE FOR THE VARIOUSPHASES GF THE MISSION.

THE PERFCRMANCE CAPABILITY TO MEET THiSREQUIREMENT IS AS FOLLCWS-

A. CREW ANC PASSENGER INSERTION THROUGH LAUNCHCCMMIT - TI E SH UTTLE PROVIDES EMERGENCYEGRESS FOR CREW AND PASSENGER EVACUATION TO ASAFE AREA IN A MAXIMUM TIME OF 2 MINUTES.

B. LAUNCH COMMIT THRCUGH RETURN-TO-SITE - THESHUTTLE HAS THE CAPABILITY CF INTACT ABORTAND RETURN TO THE LAUNCH SITE. OFF-THE-PADABCRT WILL UTILIZE SEPARATE ABORT SRP'S. THESYSTEM DESIGN WILL INCLUDE PROVISICNS FOREXTERNAL TANI SEPARATION AND CISPOSAL.

C. RETURN-TO-SITE THROUGH ORBIT INSERTICN - THEORBITER HAS THE CAPABILITY tWITH ONE MAINENGINE OUT) TO ABORT ONCE ARCUND AND RETURNTO THE PRIMARY LANDING SITE FROM THE POINT INTHE FLIGHT TRAJECTORY WHERE A DIRECI RETURNYT SITE CAPABILITY ENOS.

D. CRBITAL AND REENTRY - THE ABORT MACE AFTERORBIT INSERTION WILL BE EARLY MISSIONTERMINATION AND RETURN TO A SLITABLE LANDINGSITE.

18

i.400 PERFCRMANCE

.. 4100L PERFCRMANCE CAPAERLITIES

THE REFERENCED MISSIONS FOR THE SPACE SHUTTLE AREDESCRIEEC IN THE FOLLOWING PARAGRAPHS AND AREGIVEN TO DEFINE eASELINE PERFORMANCE CAPABILITIESONLY.

FOR PERFORMANCE CCMPARISGNS, MISSICNS 1 AND 2 WILLBE LAUNCHEC FROM KENNECY SPACE CENTER IKSC) INTOAN INSERTICN ORBIT OF 50 BY 100 NAUTICAL MILESMISSICN 3 hILL BE LAUNCHED INTO THE SAME INSERTIONORBIT FROM THE WESTERN TEST RANGE. THE MISSIONON-OREIT TRANSLATIONAL DELTA-V CAPABILITY ( INEXCESS GF THAT REQUIRED TO ACHIEVE THE INSERTIONORBIT AND THAT REQUIREC FOR ON-ORBIT AND ENTRYATTITUCE CCNTROL) IS STATED FOR EACH MISSICN ANDINCLUDES Ch-ORBIT CELTA-V RESERVES. THE REACTICNCCNTPCL SYSTEM IRCS) TRANSLATION DELTA-V REQUIREDFOR EACH MISSION IS USED TO ACCOMPLISH ALLRENDEZVCUS AND DOCKING MANEUVERS AFTER TERMINALPHASE INITIATION.

MISSILN I IS A PAYLOAD DELIVERY MISSION TC A 1CCNAUTICAL MILE CIRCULAR ORBIT. THE MISSION WILL BELAUNCHED DUE EAST, AND REQUIRES A PAYLOACCAPAeILITY OF 65,000 POUNDS WITH THE ORBITERVEHICLE AIRBREATHING ENGINES REMOVED. THE PURPOSEOF THIS MISSION WILL BE ASSUMED TO BE PLACEMENTAND/CR RETRIEVAL OF A SATELLITE. THE ORBITERVEHICLE CN-ORBIT TRANSLATICNAL DELTA-V REQUIREMENTIS 950 FEET PER SECONC IFPS) FRCM THE ORBITALI4ANEUVER SUBSYSTEM (OMS) AND 120 FPS FROM THE RCS.

MISSIGN 2 IS A RESUPPLY MISSION TO AN ORBITALELEMENT IN A 270 NAUTICAL MILE CIRCULAR ORBIT Al55 GEGREES INCLINATICN. THE RENDEZVOUS ISACCOCPLISHED USING A 17-ORBIT CCELLIPTICRENCEZVCUS SEQUENCE (SEQUENCE IS FOR REFERENCEONLY). THE PAYLCAD REQUIREMENT IS 25,000 POUNDS,WITH THE AIR8REATHING ENGINES. THE ORBITERVEHICLE CN-ORBIT TRANSLATICNAL DELTA-V REQUIREMENTIS 1,400 FPS FROM THE CMS ANC 120 FPS FROM THERCS5

$ISSICN 3 IS A PAYLOAD DELIVERY MISSION TO A lCCNAUTICAL MILE CIRCULAR POLAR ORBIT AND RETURN TOLAUNCH SITE IN A SINGLE REVOLUTION. THE PAYLOADREQUIREMENT IS 40,000 POUNDS WITH ORBITER VEHICLE

19

AIRBREATHING ENGINES REMOVED. THE ORBITER VEHICLEON-ORBIT TRANSLATION DELTA-V REQUIREMENT IS 500FPS FROP THE OMS AND 150 FPS FROM- THE RCS.

A..40i00 PERFORMANCE ANALYSIS

THE PERFCRMANCE GIVEN IS BASED ON THE MOST SEVEREOF THE THREE REFERENCE MISSIONS, THE DELIVERY OF A65,000-PCUND PAYLOAC TO A 28.5 DEGREES INCLINATIONORBIT. THE CURRENT DESIGN APPRCACH FOR THEORBITAL MANEUVERING SYSTEM (OMS) IS TO HAVE TkOSETS CF CMS TANKS INTEGRALLY MOLNTED, HAVING ATOTAL CAPACITY CF 1000 FPS WITH A 65,000-POUNDPAYLCAC. EXTRA TANKAGE CAN BE INSTALLED TOPROVIDE AN ADDIT ICNAL 1500 FPS TO MEET THERECUIRED 2500 FPS CAPACITY. THIS ACDDITIONALTANKAGE AND PROPELLANTS MAY BE LOCATED IN THEPAYLCAC BAY.

i.4U300 PERFCRPANCE DATA

FIGURE 1.4 SHOWS THE SHUTTLE PAYLOAD VERSLSINCLINATIONS FCR VARIOUS CIRCULAR ORBITALALTITUDES REACHED. THE CMS PROPELLANT WAS LCADEDTO THE EXTENT NECESSARY TO PROVIDE EXACTLY THEON-CRBIT DELTA-V REQUIRED FOR EACH MISSION. THISDELTA-V IS GIVEN AT THE RIGHT SIDE OF THE FIGUREFOR EACH CURVE AS TOTAL CMS DELTA-V. AT THE LEFTCF EACH CURVE IS GIVEN THE CCRRESPONDING CIRCULARORBITAL ALTITUDE THAT THE SHUTTLE CAN REACH,CIRCULARIZE AT, AND RETROFIRE FROM, WHILEMAIiTAINING A TCTAL OF 170 FPS RESERVE FORRENDEZVOUS AND/OR CONTINGENCIES. THE OMS IS NOTUSED AT ANY TIME IN THE LAUNCH PHASE, I*E., PRIORTO THE SHUTTLE REACHING THE 50 BY 100 NAUTICALWILE INJECTION ORBIT. THE TOTAL INJECTED WEIGHTAT ANY GIVEN INCLINATION IS A CONSTANTt ANDREPRESENTS THE MAXIMUM CAPABILITY OF THE SHLTTLETO THAT INCLINATION. THE VARIATION IN PAYLOACBETWEEN ALTITUDES IS DUE TO TRADING PAYLOAD FORCMS PRCFELLANT.

FIGURE 1.5 SHOWS PAYLOAD AS A FUNCTION OF CIRCULARORBIT ALTITUDE REACHED, MAINTAINING A 50 FPS O/MDELTA-V RESERVE. FOR THIS PLCT INSERTION ISALWAYS INTC A 50 EY 100 NAUTICAL MILE ORBIT, ANDANY ADVITICNAL ALTITUDE IS ACHIEVED BY THE OPSALCNE. ALL PERFORMANCE CALCULATIONS ARE BASECUPON CARRYING THE ENTIRE PAYLOAD THROUGHOLT ALL OF

20

Parallel burn-SRMlaunch

Orbital altitude,h, n. mi. (170 fpsOMS reserve)

20 40 60 80 100

Add-in OMS tankageincluded wherenecessary

Required

IOMS AV

500 fps

- 950 fps

1425 fps

1910 fps120

Inclination deg

PAYLOAD VERSES INCLINATIONS

FIGURE - 1.4

60

0

!

21

Parallel burn SRM launchOMS AV reserve = 50 fps

Main engines shut down in50 x 100 n. mi. insertionorbit

200 300 400 500 600 700

Circular orbit altitude - n. mi.

PAYLOAD VERSES CIRCULAR ORBITS ALTITUDE

FIGURE - 1.5

Inclination80

60

vo

CL

40

20 -

0 100

22

THE DELTA-V MANEUVERS. THIS WOULD ALLOW THEVEHICLE TO DEORBIT IN THE EVENT THAT THE PAYLOADFCR ANY REASCN CCULD NOT BE DEPLOYED. IT WOULDALSO BE THE CASE If ONE PAYLOAD WAS DELIVERED TCORBIT AND ANOTHER PICKED UP FOR RETURN TO EARTH.FOR THIS FIGURE PAYLOAC IS TRADED DIRECTLY FOR OMSPRCPELLANT UNTIL THE OPS TANKS ARE FULL. THISFIGURE CCES NOT INCLUDE ANY RENDEZVOUS ALLGWANCE.FOR RENDEZVGUS MISSIONS, 120 FPS EXTRA OMS MUST BERESERVED FOR THE RENDEZVOUS MANEUVERS. THISREDUCES THE CIRCULAR ORBITAL ALTITUDE THAT CAN BEREACHEC WITH ANY PAYLOAD AND ANY CONFIGURATION BY25 NAUTICAL MILES.

FIGURE 1.6 SHOWS THE CAPABILITY OF THE SHLTTLE TCDELIVER PAYLOAD TO A HIGH ELLIPTICAL ORBIT. THESEDATA ASSUME THAT THE MAIN ENGINES ARE SHUT DOWN INTHE NOMINAL 50 EY 100 NAUTICAL MILE INJECTIONORBIT. THE DISPOSABLE TANK IS THEN JETTISONED ANDTHE CRBIT RAISED TC .OC BY 100 NALTICAL MILES WITHTHE CMS SYSTEM. AFTER THIS IS DONE, THE CMSSYSTEM IS THEN USED TC RAISE ThE APOGEE. THEUPPER CURVE ASSUMES A DIRECT DEORBIT AT APOGEE.WITH REENTRY COMING AT PERIGEE. THIS CAN BE DONEIN THCSE CASES WHERE THERE IS NO SPECIFICREQUIREMENT ON THE POSITIONING OF THE APSICES CFTHE ELLIPSE. IN TIAT CASE, THE ORIENTATION CAN BESELECTED TC ALLOW THE PROPER APSICAL POSITION FORDIRECT ENTRY FROM APOGEE. THE BOTTOM CURVE IS FCRTHOSE CASES WHERE THE SHUTTLE MUST RECIRCULARIZEAT 100 NAUTICAL MILES BEFORE DEORBIT. THIS WOULDBE TFE CASE IF SCME FARTICULAR APOGEE POSITICNWERE RECUIRED FOR THE PAYLOAC WHERE ENTRY WERE NOTPOSSIBLE AT PERIGEE.

,WITH THE SHUTTLE LAUNCHED INTO A HIGH ELLIPSE, APAYLCAC SATELLITE CCULC EE PLACED INTO A CIRCULARORBIT AT APOGEE ALTITUCE WITH A SINGLE BURN OF ATHIRC STAGE. THIS WOULD ALLOW THE USE OF A SINGLESIPPLE PRCPULSION STAGE CN THE PAYLOAD.

23

\ :Integratank

StructuralOMS_

design limitl I--__

D irect deorbit*at apogee

\ ,N

Parallel burn SRM launchMain engines shut downin 50 x 100 n. mi. in-

._sertion orbit, 28.50inclinationPerigee = 100 n. mi.orbit circularized at100 n. mi. beforeinsertion to ellipse

No rendezvous - OMSA V reserve = 50 fps

I ii i N Supplemental Recircularized OMS tankage

- at 100 n. rmi. -\installed urrent before deorbit Current TPS

design limit

_ _ _ _ _ _ I _ _ II 1 T I. \ t,~ ~ ~~ I I

500 1000 1500 2000 3000

Apogee altitude - n. mi.

*Performance indicated is dependenton operational constraints

PAYLOAD VERSES ELLIPTICAL ORBIT ALTITUDE

FIGURE - 1.6

80

60

0

-o

oQ040

20

0

I

SPACE SHUTTLE/PAYLCAD ACCOMMODATICNS

GENERAL

THIS SECTICN DEFINES ThE SPACE SHUTTLE/PAYLOADOPERATICKAL. PHYSICAL, AND FUNCTIONALACCCPCDOAT IONS PRCVIDEO BY THE SPACE SHUTTLESYSTEM. THE APPROACH BEING TAKEN IS TO MAXIMIZETHE BENEFITS TO THE PAYLOADS WITH MINIMUM IMPACTCN THE OGBITER.

i. I00

25

2.LO CPERATICNAL INTERFACES

Z./OLOO PRELAUNCH OPERATIONS

/.HO101 PAYLCAC CHECKOUT - INCOMING PAYLOADS ANDEXPERIMENTS WILL BE RECEIVED AT THE PAYLOADSERVICE AREA WHERE FINAL PAYLOAD INSPECTION,CHECKCUT, AND INTEGRATED TESTS WILL BE PERFORMED.IF THE INSTALLATION OF AN INDIVIDUAL EXPERIMENTINTC a PAYLOAD IS REQUIRED, IT WILL BEACCOMPLISHED IN THIS AREA. ANY DEFICIENCIESDISCCVEREC DURING THESE OPERATIONS kILL BECORRECTED PRIOR TO INSTALLATION OF THE PAYLOADINTC THE OPBITER.

THE CCNCEPT OF PAYLOAC CHECKOUT AND ASSEMBLYPROVIDES MAXIMUM FLEXIBILITY FCR THE VARIOUSPAYLCAC RECUIREMENTS AND DECCUPLES THE OPERATIONALCROITER VEHICLE CHECKCUT FROM THE PAYLOADCHECKCUT. THIS IS ACCOMPLISHED BY THE USE CF6TRUCTURAL INTERFACE FIXTURE FOR PHYSICAL ANDMECHANICAL CRBITER/PAYLCAC INTERFACE CHECKS, ANCWITH ELECTRONIC ANALOG UNITS FOR ELECTRICAL POWER,DATA MANAGEMENT, CONTROL, ANC COMMN ICAT ININTERiFACE CHECKS BEThEEN THE ORbITER AND THEPAYLCAD.

DURING ALL PHASES CF THE PRELAUNCH OPERATIONS,SPECIAL EMPHASIS WILL eE PLACED GN CONTAMINATIONCGNTRCL PRCCEDURES TO PROTECT SENSITIVE PAYLOACELEMENTS.

-. oZOUZ PAYLCAC CENTER-OF-GRAVITY - PRECISE INFORMATION GNTHE PAYLCAC MASS CENTER-OF-GRAVITY (C.G.o MUST BEESTABLISHED PRIOR TO INSTALLATION OF THE PAYLOADIN THE CRBITER. FOR AeORTS AND ENTRY, THE PAYLOADC.G. IS RESTRICTED IN THE LONGITUDINAL AXIS TCTHE ENVELOPE SHOWN IN FIGURE 2.1.

,~,~0.0 PAYLCAC INSTALLATION - THE INSTALLATION CF THEPAYLCAD INTO THE OREITER MAY OCCUR AT EITHER OFTWO FACILITIES- THE SHUTTLE MAINTENANCE AND-REFURBISHMENT FACILITY (MRF), CR THE VERTICALASSEMBLY BUILDING (VAB). THE CAPABILITY TO CHANGEOUT PAYLCOAS ON TFE PAC WILL EXIST FCR CONTINGENCYPURPESES CNLY AND SHOULD NOT BE CCNSIDERED AS ANORMAL CR PLANNEC OPERATION. NORMALLY, THEPAYLOAC IS INSERTEC INTO THE ORBITER PAYLOAD BAYWHILE THE CRBITER IS IN THE HORIZONTAL POSITION INTHE MRF. FOLLOWING INSTALLATION AND ESTABLISHMENT

26

Ex

cEE

-oI

UE

I

·X-

A

IO

~_

>

tocu

o

c

l I

I-

o

l I

Cu

inI

L O

L

C4

->o

W e

_I II

Ia

E CC

sql Jo spuesnoip u! 146!aM peolIed

27

OF ELECTRICAL AND CTHER INTERFACES, VALIDATION CFTHESE INTERFACES IS ACCOMPLISHED.

Zi.ZOlC4 VEHICLE INTEGRATION - THE NEXT PHASE OF PRELAUNCHOPERATICNS INVOLVES THE MATING OF THE ORBITER ANDTHE SRM'S. THE PAYLOAD PRELAUNCH OPERATI'CNS MUSTSE EASICALLY COMPLETED SINCE ACCESS TO THE PAYLOADIS LIMITED TO PAYLOAD MONITORING VIA SHUTTLESYSTEMS EXCEPT UNDER SPECIAL CIRCUMSTANCES. WITHTHE SHUTTLE IN THE VERTICAL POSITION AND FINALINTERFACE CHECKS COMPLETE, THE S-LTTLE IS READYFOR PRELAUNCH GPERATIONS.

.2iOzO0 CReITER PRELAUNCH OPERATIONS

.koCiOD LAUNCH PREPARATICN - TIE VEHICLE OPERATICNS AREDEVOTED PRIMARILY TC VERIFYING THE LAUNCHJMEILICAL TOWER/LAUNCH FACILITY CONNECTIONS,PERFCRMING THE FINAL INTEGRATED TESTSt SERVICINGTHE VEHICLE, LOACING ThE CREW AND PASSENGERS, AhDFINAL CLCSEOUT. FIGURE 2.2 IS A REPRESENTATIVEFLCW OF ACTIVITIES DURING THIS PERIOD. ALTHOUGHPAYLCACS NOMINALLY ARE LOADED PRIOR TO TFECRB.ITER/iOCSTER MATING, IT IS POSSIBLE TO REPLACETHE PAYLCAC ON-PAC IN CONTINGENCIES. hAZARDCLSSERVICING PROCEDURES ARE -ALSO CCNDUCTEC OUR-INGTHIS PERICD, IF THERE ARE SUCH REQUIREMENTS.ACCESS TO THE PAYLCAD WHILE CN THE PAD NORMALLYMILL BE LIMITED TC THOSE ITEMS ACCESSIBLE THROUGHTHE ORBITER CREW COMPARTMENT OR THROLGH THEPAYLCAD bAY DCCR. THE ACCESS, REMOVALt ANDLOACING CF PAYLGAC EQUIPMENT ON ThE PAD WILL BELIMITED TO NCT MCRE THAN 10 HOURS ELASPED TIMEPRIC( TC T-2 HOURS.

'..4:C PAYLCAD SERVICES - PAYLOAD SERVICES ARE FURNISHEDTHROUGH STANCARO CRBITER/PAYLOAD INTERFACES ANDTHROUGH PAYLCAD ACCESS PANELS. STANDARC GROUNDAND LAUNCH SERVICES MAY BE SUPPLEMENTED BYRECCNFIGURATION OF AN ACCESS PANEL TO ACCOMMODATEWNIgUE PAYLOAD SERVICES. HOWEVER, THERECCNFIGURATION CF ACCESS PANELS AND SUPPCRT GFUNICLE SERVICES ARE CHARGED TO THE PAYLOAD.

NORMALLY, THE CRBITER/PAYLOAC INTERFACES PROVIDEPOWER, CCMMUNICATIONS, STATLS MONITORING,ATMOSPhERE CCNTROL, VENTING, AND CERTAIN PAYLOADPROPELLANT ACCESS PRCVISIONS. THE PAYLOACSERVICES FCR CRYOGENIC PROPELLANTS INCLUDE ACCESSFOR FILL, VENT, ORAIN, AND DUMP. ATMOSPHERECGNTRCL CF THE PAYLOAD BAY IS PROVIDED THROUGH GSE

28

0co0Co

co0o r-I

0O0,0

C.

0C)

Cy-Z

)C

)

zLU

2z0--

w0 Lii

0m Ld

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0

29

DURING PRELAUNCH OPERATICNS9 PRIMARILY TO KEEP THEBAY FREE OF CONTAMINATION BY EXTERNAL SOURCES.

Z.40300 FLIGHT CPERATIONS

i..zO.ui SHUTTLE ASCENT - THE LIFT-OFF TO INSERTION PHASEWILL eE ESSENTIALLY AN AUTOMATIC GPERATICN UNDERORBITER CCNTROL. THE EARLY VERTICAL FLIGHTS WILLHAVE GRCUNC SUPPCRT FCR TRAJECTCRY AND SYSTEMSMUCH LIKE THAT EXISTING FOR APOLLO. AFTER T-ESHUTTLE OPERATIONS MATURE, THERE WILL BE LESS NEEDFCR REAL-TIME SHUTTLE SYSTEMS SUPPORT FOR LAUNCP.DURING LAUNCHo THE PAYLOAD SUPPORT WILL BE LIMITEDPRIMARILY TO MINIMUM SUBSYSTEMS SUPPCRT AhDPAYLCAC SAFETY STATUS MONITORING.

4.,;002 PAYLCAD CCNTRCL ANC DISPLAY - THE ORBITER WILLHAVE PROVISIONS FOR MONITORING ALLSAFETY-CF-FLIGHT PARAMETERS GENERATED BY TFEPAYLCAC. THESE PARAMETERS ARE DISPLAYED TO THEFLIGHT CREW AND MISSION SPECIALISTS. IN ADDITIONTO THE SAFETY-OF-FL IGHT PARAMETERS, PAYLCACPECULIAR PARAMETERS CAN BE DISPLAYED TO THEMISSICh SFECIALIST CN THE GENERAL PURPOSEDISPLAYS, OR THRCUGH PAYLCAD SUPPLIED MISSIONPECULIAR CISPLAYS TO TFE PAYLOAD SPECIALIST.

·. .3003 PAYLLCA CHECKOUT - PRICR TO PAYLOAC OPERATION ORDEPLCYMENT, FUNCTIONAL CHECKOUT CAN BEACCCOPLISHED BY USE OF PROGRAMS STORED IN THEMEMCfY CF THE COMPUTER USED FOR PAYLOAD CHECKOUT.MANUAL INSERTION OF PAYLOAD DATA/CCMMANDS INTO THECOMPLTER CAN BE MADE THROUGH THE KEYBOARD.DEDICATED PAYLOAC DISPLAYS AND CONTROLS CAN ALSC.BE USEC IN CONJUNCTICN WITH PAYLOAD CHECKOUT.VISUAL INSPECTION AND MANUAL ASSISTANCE BY THECREW CAN BE ACCCMPLISHED BY EXTRAVEHICULARACTIVITY (EVA) OR INTRAVEHICULAR ACTIVITY (IVA).WHEN THE ORBITER COCKING PORT IS SECURED TO ADOCKiNG PORT ON ANOTHER ORBITAL ELEMENT,SHIRTSLEEVE ACCESS IS AVAILABLE THROUGH THEORBITER AIRLCCK ANC DOCKING PORT TO THE ORBITALELEMENT. VERIFICATION OF DOCKING AND UNDCCKING ISDISPLAYEL TO THE CRBITER FLIGHT CREW.

,.i;O.O PAYLCAC CEPLCYMENT AND RETRIEVAL - THE ORBITERPRCVIDES A PAYLOAD CEPLOYMENT/RETRIEVAL MECHANISMTC DEPLCY PAYLOACS CLEAR OF THE ORBITER MOLD LINE.FOR RETRIEVALt THIS MECHANISM INTERFACES WIThPAYLCACS CESIGNEC FOR RETRIEVAL AND, AFTERATTACHMENT TO. THE PAYLCAC, ALIGNS THE PAYLOAD IN

30

IHE PAYLOAD eAY FCR SECURE STOWAGE OF THE PAYLOADOIN ACCITION, THIS MECHANISM IS CAPABLE CFSUPPCRTING THE PAYLOAD IN THE DEPLOYED POSITIONUNDER ATTITUDE STAeILIZATICN AND CCCKING LOADS.

DEPLCYMPET CF SFIN-STAEILIZEC PAYLOADS MAY BEACCCMPLISHED FROM A SPIN TABLE PROVIDED BY THEPAYLCAL. ANY ADDITIONAL PAYLOAD PECLLIARDEPLCYMENT, ERECTICNt RETRACTION, ET CETERA,REGUIREMENTS FOR SPECIAL MECHANICAL SYSTEMS ISPRCVIDEC BY THE PAYLOACD,

e.eU.05 MULTIPLE PAYLOAD CEPLOYMENT - THE ORBITER WILLHAVE THE CAPABILITY TO DEPLOY MLLTIPLE-PAYLOACSCN-CPBIT CURING A SINGLE MISSION9 INCLUDINGPLACEMENT CR COCKING OF PAYLOADS TO A STABILIZEDO80DY. FCR MULTIPLE-PAYLCOAD MISSICNS THE ORBITER

SUBSYSTEMS SUPPORT CAPABILITY IS SHARED BY THEPAYLCACS.

-. ).e~u DOCKING - COCKING CF THE ORBITER TC A PAYLOAD CRANCTHER CREITAL ELEMENT CAN BE ACCOMPLISHED WITH-- L .. , .....~ANIPULATOR ARMS AND COCKING PORT, CRBY DIRECT COCKING. PRIMARY COMMAND AND CONTRCLAUTHCRITY REMAINS WITH THE ORBI TER DUR ING THEDOCKING OPERATIONSo TO ACCOMMODATE DOCKING, THEORBITER CRIENTS AND APPROACHES THE ORBITAL ELEMENTWITH THE USE OF THE ORBITER RCS. WHEN THE ORBITERIS kITHIN THE REACH DISTANCE OF THE MANIPULATORARM OF THE CREITAL ELEMENT, THE MANIPULATORSENGAGE THE ORBITAL ELEMENT AND DRAW THE TWO BCDIESTOGETHER TC ACCOMPLISH CCNNECTION OF THE DOCKINGINTERFACES. FOR DIRECT DOCKING, THE OREITER ASTHE ACTIVE VEHICLE APPROACHES AND ENGAGES THEDCCKING MECHANISMS ON THE ORBITAL ELEMENT BYIMPACT ENGAGEMENT. THE OPERATIONAL DESIGNPARAMETERS FCR DOCKING ARE GIVEN IN TABLE 2-1.

TABLE 2-1 - CPERATICN DESIGN PARAMETERS FOR DOCKING

LATERAL MISALIGNMENT +/- 0.5 FEETANIULAR MISALIGNMENT +/- 5.0 DEGREESRULL MISALIGNMENT 7.0 DEGREESLLUSINL, VYELCCITY AT CONTACT 0.5 FPSALTIVE VEHICLE ANGULAR VELCCITY AT CONTACT 1.0 DEG/SECPASSlVt VEHICLE ANGULAR VELOCITY AT CONTACT 0.1 DEG/SEC

WHEN THE ORBITER COCKING PORT IS SECURED 10 ADOCKING PORT ON ANOTHER ORBITAL ELEMENT,SHIRTSLEEVE ACCESS IS AVAILABLE THROUGH THE

31

ORBITER AIRLCCK ANC DOCKING PORT TO THE ATTACHEDELEMENT. VERIFICATION OF DOCKING AND UNDOCKING ISDISPLAYED TO THE ORBITER FLIGHT CREW.

EVA/IVA - TO DISTINGUISH BETWEEN EXTRAVEHICULARACTIVITES (EVA) AND INTRAVEHICULAR ACTIVITIES([IVA) WITH REGARD TO A PRESSURE SUITED CREWMANrTHE FCLLCWING DEFINITION IS GIVEN.

EVA APPLIES Ta ACTIVITIES CONOUCTED OUTSIDE THESPACECRAFT PRESSURE HULL OR AN OPEN PAYLOAD BAY.IVA BY A PRESSURE-SUITED CREWMAN, IS CONFINED BYTHE VEHICLE STRUCTURE. ACTIVITIES WITPIN THEPAYLCAD BAY WITH THE DCORS CLOSED ARE CCNSIDEREDIVA. IF A SECTICO IS APPLICABLE TO EVA ONLY, IVAWILL BE EXCLUDED EY A NOTE. OTHERWISE, THE TERMEVA WILL BE USED TC INCLUDE IVA.

THE CRBITER PROVICES THE CAPABILITY TO PERFORMMULTIPLE EVA'S IN ORBIT, OR IVA'S INTO THE PAYLOADBAY. HOWEVER, THE EXPENDABLES AND EVA SLITS AREPROVIDEC AT THE EXPENSE CF PAYLOAC WEIGHT. TbCCREWMEN EVA IS CCNSIDEREC THE NORMAL EVA MODE CFOPERATICh WHERE ONE CREWMAN PERFORMS THE EVA TASK,THE SECCNO CREWMAN MAINTAINS A BACKUP STAIUS, ANDBOTH EVA CREWMEN ARE MCNITORED FROM WITHIN THECRBITER. EVA IS A METCHOD FOR THE CN-ORBIT PAYLCACACTIVITIES, AND ITS USAGE .FOR BOTH NORMAL ANCCONT INGENCY PAYLCAD CPERAT IONS MUST BE 'TRADEDAGAINST THE ADVANTAGES .ANC DISADVANTAGES GFALTERNATE METHODS. IT IS POSSIBLE THAT FOR SOMETASKS, EVA COULD BE A IIGHLY COST EFFECTIVE METHCDFCR PERFORMING PAYLOAD OPERATIONS.

COMMUNICATIONS - A COMMUNICATION SATELLITE SYSTEMIS AVAILABLE FOR RELAY OF VOICE ANC VIDEO BETWEENTHE CRBITER AND GROUND. THE ORBITER IS ALSOCAPABLE CF DIRECT COMMUNICATION WITH THE GROUND.THE CRBITER/PAYLOAC COMMUNICATION INTERFACES AREGIVEN IN TABLES 2-IIA AND 2-118. THESE INTERFACESPROVICE AVAILABLE COMMUNICATION CHANNELS FORPAYLCAC OPERATIONS DURING A MISSION.CCMMUNICATION RECUIREMENTS IN EXCESS OF THESE ARE6UPPCRTED eY THE PAYLOAD.

32

TAdLi: 2-11A - CRBITER/PAYLCAC COPMUNICATION INTERFACES

I

Si GNAL* iESCRIPTICN

I IARCWIRE PAYLOAD INTERFACE

I RBITE

* ORBITER EQUIP,4ENTI

..aII

'PAYLOAD EQUIPMENT'

*_____ - _ _ - I---_*______ I _--- -- -- - I

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INT ERCOMAU CETER

I AUCIO CENTER

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INTERLEAVED TLM' STCRED PROGRAMI FRCCESSOR

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WHlbt:ANtD ANALCG' WIOEBANC XMTR

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hICOEBANC XMTR

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TAkLE Z-IIB - CRBITER/PAYLGCAC CO'MUNICATION INTERFACES

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CREW

THE BASIC CRBITER CREW SIZE IS FOUR, TWO CF WHICHARE THE CCOMMANDER AND PILOT WHO USLALLY ACCCMPLISHTHE FLIGHT OPERATIONS OF THE ORBITER. THEFCLLCWING NOMENCLATURE IS USED TO IDENTIFY ANDDESCRIBE THE DUTIES OF THE PERSONNEL.

COMMANDER - THE CCPMANCER IS IN COMMAND OF ThEFLIGHT ANC IS RESPONSIBLE FOR OVERALL SPACEVEHICLE, PAYLCAD FLIGHT OPERATIONS, AND VEHICLESAFETY. HE IS PRCFICIENT IN ALL PHASES OF VEHICLEFLIGHT, PAYLOAD MAN IPUL AT ION, DOCKING ANDSUBSYSTEM COMMAND, CONTROL, AND MONITOR OPERATICN.HE IS ALSO KNCOWLECGEABLE OF PAYLOAD AND PAYLOADSYSTEMS AS THEY RELATE TO FLIGHT OPERATIONS,COMMLNICATION REQUIREMENTS, DATA HANDLING, ANDVEHICLE SAFETY.

2. U402 PILCT - THE PILOT IS SECONDEQUIVALENT TO THE COMMANDERKNCWLEDGE CF THE VEHICLE.

IN COMMAND AND ISIN PROFICIENCY AND

ZoU(40J MISSICN SPECIALIST - THE MISSION SPECIALIST ISRESPENSIBLE FOR INTERFACING OF PAYLOAD ANC ORBITEROPERATICNS AND THE MANAGEMENT OF PAYLOADOPERATICNS. THE SPECIALIST IS TRAINED IN VEHICLEAND PAYLCAC SUBSYSTEMS, FLIGHT OPERATICNS, ANDPAYLCAC CCOMMUNICATIONS DATA MANAGEMENT. MPRE THANONE MISSION SPECIALIST MAY BE INCLUDED IN THECREW.

2.IO40, PAYLCAC SPECIALIST - THE PAYLOAD SPECIALIST ISRESPCNSIBLE FOR THE APPLICATIONS, TECHNOLCGY, ANDSCIENCE PAYLOAD/INSTRUMENTS OPERATIONS. THISSPECIALIST HAS CETAILED KNOWLEDGE OF ThEPAYLCAC/INSTRUMENTS, OPERATIONS, REQUIREMENTS,OBJECTIVES, AND SUPPORTING EQUIPMENT. MORE THANONE PAYLOAC SPECIALIST MAY BE INCLUDED IN THECREW.

/.. .405 PASSENGER/CBSERVER - PASSENGER/OBSERVERS AREPERSChNEL WHC ARE CNBOARD, BUT HAVE NO ACTIVE PARTIN SHUTTLE OPERATIONS.

:.zOu0ob CREW PROVISICNS - VOLUME IS AVAILABLE WITHIN THECREW CCMPARTMENT FCR ACDDITIONAL PAYLOAD SPECIALISTCR PASSENGERS, HCkEVER, THEIR WEIGHT, PERSONNEL6UPPCRT SYSTEMS, EQUIPPENT, AND CONSUMABLES ARECHARGED TO THE PAYLCAC. ALSO, WITHIN 1HE CREWCOMPARTMENT ARE SLEEP PROVISIONS TO ALLOW CREWROTATICh FOR 24-HOUR OPERATIONS. PAYLOAD

4. *400u

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35

OPERATIChS MAY ELECT EITHER MULTIPLE SkIFTS CRDISCRETE WORKING HOURS TO SUPPORT MISSIChOBJECTIVES.

i.2000 PGSTFLIGHT OPERATIONS

FCLLC¼ING LANDING, THE ORBITER IS TOWED 10 THESAFIbG FACILITY WHERE THE CREW AND PASSENGERSDISEMBARK ANO THE NECESSARY POSTFLIGHT CCOLDOWNAND SAFING OPERATIONS ARE PERFORMED. NORMALLYtTHE FAYLCAC WILL REMAIN WITH THE ORBITER UNLESSTHERE ARE CRITICAL EXPERIMENTS WHICH MLST BEREMCVED AT THIS FACILITY. THIS FACILITY CAN ALSOBE USEC TO SAFE AND PURGE HAZARDOL-S PAYLOAD ITEMS.THE PAYLOAD MUST BE COMPATIBLE WITh THE AVAILABLESHLTTLE GSE, OR SUPPLY THE NECESSARY EQUIPMENT TOSUPPCRT THE OPERATICN.

WHEN THE SAFING OPERATIONS ARE COMPLETED THEORBITER IS TOWED TO THE MRF WHERE THE PAYLOAD ISNORMALLY REMCVED FRCM THE ORBITER.

36

Z.300 SYSTEM/SUBSYSTEM INTERFACES

,. f1OO STRUCTURAL/MECHAhICAL INTERFACES

z.JOiOl PAYLCAC eAY ENVELOPE - THE ORBITER PAYLOAC BAY CANACCOMMCOATE A PAYLOAD, OR COMBINATIONS OFPAYLCADS, hHOSE CYNAMIC ENVELOPE IS EQUAL TO, ORLESS THAN, 60 FEET IN LENGTH AND 15 FEET INDIAMETER. THIS PAYLCAC ENVELOPE EXCLLCES THENECESSARY PAYLOAC STRUCTURAL ATTACHMENT POINTS,WHICH EXTEND OUTSIDE THE ENVELOPE TO INTERFACEWITH THE ORBITER STRUCTURAL MOUNTING POINTS.CLEARANCE ENVELOPE BETWEEN THE PAYLOAD ENVELOPEAND THE ORBITER STRUCTURE IS PROVIDED BY THEORBITER TO AVOID CRBITER CEFLECTICN AND DEPLOYMENTINTERFERENCE BETWEEN ThE ORBITER AND PAYLCAD,

'.j* 4oi2 PAYLCAD STRUCTURAL ATTACHMENT - MULTIPLESTANCARCIZED ATTACHMENT POINTS ARE LOCATED (TBD)IN THE PAYLOAC BAY TO STRUCTURALLY SUPPORT ALLPAYLCADS. THE LCCATIONS OF THESE POINTS ARE AT CROUTSIDE THE 15-FCCT DIAMETER PAYLOAD MOLD LINE ANCTRANSMIT PAYLOAD LCADS TO THE ORBITER PRIMARYSTRLCTURE. THESE ATTACHMENT POINTS INTERFACE WITHTHE PAYLOADS OR PAYLOAC ADAPTERS AND ARE CAPABLEOF SUFPCRTING THE PAYLOAD UNDER ALL mISSICNPHASES. TFE ORBITER HAS THE CAPABILITY TO LANC40,000 PCUND PAYLCACS WITH NOMINAL WIND AND LOADFACTLRS (AIREREATPING ENGINES REMOVEC) ANC LARGERPAYLCACS WITH RECUCED STRUCTURAL SAFETY FACTORS.

THE CORBITER ALSC PROVIDES THE CAPABILITY FORDETERMINING THE MECHANICAL ALIGNMENT OF THEPAYLCAC (WITH RESPECT TO THE REFERENCE FRAME CFTHE ORBITER) TO AN ACCURACY OF 0.5 DEGREE IN ALLAXES WHILE THE PAYLOAD IS ATTACHED TO THE PAYLOADSAY.

Z..~1O. REMCTE MANIPULATOR SYSTEM (RMS) - THE CRBITERPAYLCAC CEPLOYMENT AND RETRIEVAL MECHANISMCCNSISTS OF A PAIR OF REMOTE MANIPULATOR ARMSWHICH ARE STOWED OUTSIDE THE PAYLOAD VOLUME.FIGURE 2.3 IS A PRELIMINARY DESIGN OF A TYPICALSYSTEM. PAYLCAC ENGAGEMENT IS ACCOMPLISHEDTHRGUGH TERMINAL CEVICES ON THE ENC OF EACH ARM.

TO ACCCPPCDATE PAYLCAC RETRIEVAL AND STCWAGE INTHE PAYLCAC BAY, ThE PAYLOAD PROVIDES THE ORBITERCOMPATIBLE MECHANICAL, ELECTRICAL, ANC FLUIDINTERFACES.

37

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i.~30104 DOCKING MECHANISM - THE DOCKING MECHANISM ISDESIGNED TC INTERFACE W ITH STANDARDIZED DOCKINGMECHANISMS CN OTHER ORBITAL ELEMENTS AND CNANCT*ER CRBITER. THE COCKING MECHANISM CONTAINSALL THE NECESSARY HARDWARE FOR ENGAGING, LATCHING,AN[ SEALING THE INTERFACE BETWEEN THE ORBITER ANDANCThER ORBITAL ELEMENT. INCLUDED IN THE ORBITERARE APPROPRIATE DISPLAYS FOR VERIFICATION OF THEENGAGEMENT AND SEPARATION OF THE CDOCKINGINTERFACE. WITHIN THE DIAMETER OF THE DOCKINGRING ARE A CLEAR PASSAGEWAY OF L.o-METER DIAMETERAND THE NECESSARY POWER, CAUTICh AND WARNING,DATA, CCPMUNICATION, AND FLUID INTERFACECONNECTORS TC SUPPORT COCKED ORBITAL OPERATIONS.

*..0105 PAYLOAD eAY OOCR(S) - THE ORBITER I-AS TPECAPABILITY TO EXPOSE TFE ENTIRE LENGTH AND THEFULL WIDTH OF THE PAYLOAC BAY. WITH THE PAYLOADBAY DCCR(S) AND RCDIATOR(S) GPENt THEUNCBSTRUCTUED 180-DEGREES LATERAL FIELD-OF-VIEW ISAVAILABLE TO THE PAYLOAD AT THE PLANE OF THE hINGELINE, NhIC- IS LCCATED ITBD) RELATIVE 10 THELONGITUDINAL CENTERLINE OF THE PAYLOAD BAY.

*...J0Oo PAYLCAC BAY SERVICE PANELS - PAYLCAC BAY SERVICEPANELS ARE PLACED AT DISCRETE LOCATIONS IN THEORBITER STRUCTURE FOR GSE SERVICE ACCESS TO TFEPAYLCAC. THESE PANELS, LOCATED IN THE PAYLOAD BAYWALLSt NIORALLY ARE BLANKt NONSTRUCTURAL PANELSWHICH ARE CAPABLE CF BEING REPLACED WITH PAYLOADPECULIAR PANELS DESIGNED TO SERVICE A PARTICULARPAYLCAC. THE WEIGHT DIFFERENCE BETWEEN THE BLANKSERVICE PANEL AND THE PAYLOAD PECULIAR PANEL ISCHARGED AGAINST ThE PAYLOAD WEIGHT. THE LINESCONNECTING THE PAYLOAD TC THE SERVICE PANEL ALSCARE CHARGED AGAINST THE PAYLOAD WEIGHT.

:.3i020O FLUID SYSTEM INTERFACES

:..0U'OJ OMS CELTA-V KIT - CN-ORBIT MANEUVERING CELTA-V INEXCESS CF THE 1000-FPS AVAILABLE IN THE BASELINECRBITER IS AVAILABLE BY ADDITION OF OMSPRCPELLANT. THE ADDED VOLUME AND WEIGHT FORPRCPELLANT, TANKAGEt AND PLUMBING TO THE VEHICLEOHS IS CHARGED TC PAYLOAD.

2.43020d PRCPLLSIVE PAYLOAD INTERFACES - PRCPULSIVE STAGESCARRIED kITHIN TfE PAYLOAD BAY REQUIRE VARIOLSTYPES OF FLUID INTERFACES BETWEEN THE ORBITERVEHICLE AND THE PAYLCAC BAY. THESE iNTERFACEREQUIREMENTS VARY SIGNIFICANTLY WITH THE TYPES OCF

39

PRCPELLANT UTILIZED BY THE PROPULSIVE STAGE.STORABLE PROPELLANTS, SUCH AS THOSE USED BY THEAGENA9, ELTA, AND TRANSTAGE CAN BE LOADED PRIOR TCSTAGE INTEGRATICN WITH THE ORBITER. NO FILLCCNNECTICNS, THEREFCRE, ARE REQUIRED BLT DRAINCONNECTIONS CAN BE REQUIRED FOR EMERGENCY DUMP.SEVERAL CPTICNS APPEAR FEASIBLE FCR PROVIDING THEFLUID INTERFACES PREVIOUSLY MENTICNED.

FLUID CCNNECTION PANEL(S) ARE LOCATED TO MINIMIZEVEHICLE SCAR WEIGHT. THESE INTERFACE PANELSPROVIDE THE FLUID SERVICING PLUS THE VENTINGLOCATIONS. THE PROPULSIVE PAYLOAD PROPELLANTSREQUIRE VENTING AS WCULD, IN MOST CASES, THEPRESSURANTS. FOR THESE CASES, THE FLUIDCCNhECTICN PANELS ARE FITTED FOR THE PAYLOAD.WHEN NCT REQUIREDC THE SERVICE PANELS ARE REPLACEDBY BLANK PANELS. PROPELLANT SERVICE UMBILICALSAND DUMP PROVISIONS ARE REQUIRED FOR CRYCPAYLCACS.

TABLE 2-II INDICATES THE SERVICING APPLICABILITYFOR EACH CLASS OF PAYLOADS FLUIDS. THE 'OPENPAYLCAC BAY DOOR' IS SERVICING PAYLOADS fHEN THEBAY CCCGRS ARE OPENED. CRYO SERVICES ARE NC1INCLUDED SINCE THE ODORS ARE CLOSED PRIOR TCLAUNCH, HOWEVER, A DUMP SYSTEM IS REQUIRED.

TABLE 2-111 - LOACING AND DUMPING OPTIONS

- ' COMS · REMOVABLE ' OPEN* INTEGRATION ' SERVICE PANELS ' PAYLOAD

BAY DOOR

' UM$ KIT r X X

" LuX/LH2 X

"EAkTH STORABLE ' a X " X "_ _ _ a a,_ _ _ __ _ _ _ _ a a___ _ __ _ _ _

4.3OOU3 PAYLCAC BAY VENTS - ADEQUATE PENETRATION FCRVENTING AND PURGING THE PAYLOAD eAY ANC ACTIVEPAYLCAC EFFLUENTS ARE PROVIDED BY THE CRBITER.THIS VENT SYSTEM CCNSISTS CF NONPROPULSIVE VENTS.

40

2. oj00 ELECTRICAL POWER

ELECTRICAL POWER FOR PAYLOADS IS AVAILABLE FRCMGTHE CRBITER ELECTRICAL POWER SYSTEM. ANELECTRICAL ENERGY ALLOWANCE OF 50 KILOWATT-hOURS(KWH) IS DEDICATEC FOR PAYLOAD SUPPORT WITH ENERGYIN EXCESS OF THIS ALLOCATION BEING MISSICNDEPENDENT ANC CAPABLE OF BEING SUPPLEMENTED BYADDITICNAL CONSUMAeLES TC THE ORBITER FUEL CELLSAND/CR BY INDEPENDENT PAYLOAD SYSTEMS.

THIS POWER IS IN THE FCRP OF REGULATED REDUNDANTDC PCWER HAVING THE CHARACTERISTICS SHOWN BELOk.

VCLTAGE - 30 VCC NOMGINAL

TRANSIENT - (TBC)

LCAD - 1000-WATTS AVERAGEt 1500-WATTS PEAK (PEAK ORBITEROPERATION PERIODS)

- 3000-WATTS AVERAGE, 60C0-WATTS PEAK (Ch-ORBITCCAST PERIODS)

i53 )01 EXTENDED DURATICh MISSICh SUPPORT - FOR EXTENDEDDURATICN MISSIONS, OR FUR MISSIONS REQUIRINGINCREASED TOTAL ELECTRICAL ENERGY, ADDITIONAL FUELCELL REACTANTS ARE REQUIRED AND ARE PLUMBED INFRCM THE PAYLOAD BAY. THESE CONSUMABLESt THEIRTANKAGEt AND THE PLUMBING TO THE ORBITER INTERFACEARE CHARGEC TO THE PAYLOAD. THE EXTENDED DURATIONHISSICN RECUIRES ACCED CCNSUMABLES FOR THE PAYLOACAND FCR CPERATION CF TIE ORBITER BEYOND THE NGRMAL7-DAY CRBITER MISSION.

Z. 0eUO DISPLAYS ANC CONTRCLS

DISPLAYS AND CONTRCLS FOR PAYLOAD OPERATICNS AREPRCVIDEC AT THE CCMMANDER/PILOTt HISSIGNSPECIALIST, AND PAYLOAC VtANDLING STATIONS.

PAYLCAC DISPLAYS AND CONTROLS AT TFECGhMANDER/PILCT STATIONS ARE PRIMARILY CCNCERNEDWITH CCPMUNICATICNSe PCWER CCNTROL (MASTER CIRCUITBREAKER CCNTRCL SWITCH FOR PAYLCAC PO¼ER), AND APAYLCCA MASTER CAUTION ANC WARNING LIGHT.

41

DISPLAYS AND CONTRCLS PROVIDED AT THE MISSICNSPECIALIST STATICN INCLUCE-

A. MASTER CAUTICN ANC WARNING

B. CAUTICN ANC WARNING PANEL WITH CEDICATEDWIRING FOR GISPLAYS

C. A CATHCODE RAY TUBE ICRT) ANC KEYBCARD FCRCCNTRCL OF PAYLOAD MONITORING AND CHECKOLT INCCNJUICTION WITH THE COMPUTER USED FCRPAYLOAD MONITCRING

D. SPACE FOR DISPLAYS AND CONTROLS PRO'IDE eBYTHE PAYLOAD

F. AUCIC CCMMUNICATICNS PANEL WITH AUDIC-CHANNELSELECTOR FOR COMMUNICATIONS WITH CREWMEN,PERSCNNEL IN PAYLCAD BAY, EVA PERSONNEL,.PERSCNNEL IN A FREE FLYING PAYLOADt OR THEGRCUNC

THE PAYLCAC HANDLING STATION DISPLAYS AND CCNTROLS.ARE DESIGNED TC SUPPORT PAYLCAC DEPLCYMENT,DOCKING, RETRIEVAL, AND REMOTE OPERATIONS THROUGhTHE. USE CF THE MANIPULATOR ARMS, SPECIFICDISPLAYS AND CONTROLS CF THIS STATION INCLUDE THEFOLLCWING ITEMS-

A. MANIPULATOR CONTROL' SYSTEM AND PAYLOADRETENTICN CCNTROLS AND DISPLAYS

B. DISPLAYS FCR PAYLOAD BAY TV VIDEC, ANCCCNTRCLS FOR OPERATING AND SUPPLYING POWER TCTHE PAYLOAD EAY CAMERAS

C. AUCIO CCMMUNICATICN PANEL WITH AUDIO CHANNELSELECTOR FCR COMMUNICATIONS WITH CREWMEN,PAYLOADC BAY EVA PERSONNEL, AND GROUND

0. CAUTICN AND WARNING DISPLAYS FOR GENERALPAYLCAC OPERATIONS ITEMS

E. PAYLOAD BAY LIGHTING CONTROLS FCRILLUMINATION CF PAYLOADS, PAYLOAD BAY AREAtANC PAYLCAD INTERFACES

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i.j.Oou0 GUIDANCE AND NAVIGATION

2..tJ501 6YSTEM CAPABILITIES - THE ORBITER GUIDANCE,NAVIGATICN, AND CCNTROL (GN+C) SYSTEM IS. CAPABLECF PRCVICING GUICANCE, NAVIGATION, AND CONTROL FCRTHE CRBITER THROUGH ALL PHASES OF ORBITAL SPACEFLIGHT FRCP LAUNCH THRCUGH ENTRY, AND FOR AIRCRAFTAERCCYNAMIC FLIGHT MOLES. DURING THE CN-CRBITPHASES, THE GUIDANCE AND NAVIGATION OF THE ORBITERCAN eE INDEPENDENT OF CIRECT GROUND SUPPORT,

0. JO:O RENCEZVCUS - ThE ORBITER HAS THE ONBOARCCAPABILITY TO RENOEZVCUS WITH AN IN-PLANECOOPERATIVE TARGET UP TO 300 NAUTICAL MILESt ANCIS TIE ACTIVE VEHICLE CURING RENDEZVOUS, CCCKING,AND UNCCCKING. THE ORBITER IS ALSO CAPABLE OFMANUAL CCCKING WITH OTkER ORBITERS OR CCMPAT7BLEORBITAL ELEMENTS DURING DAYLIGHT OR DARKNESS. BvUSING GRCUND FACILITIES AND OTHER AICS, T-EORBITER IS CAPABLE CF RENDEZVOUS WITH ANCRETRIEVAL CF A PASSIVE STABLIZED ORBITING ELEMENT.

i..30503 ORBIT NAVIGATION - TABLE 2-iV PRESENTS A SUMMAR¥OF ESTIMATED NAVIGATION PERFORMANCE FOR SOME OFTHE' FCSSIBLE SYSTEMS.

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TAoLE 2-IV - TYPICAL NAVIGATION SYSTEM ACCURACIES

RMS POSITION (FT) RPS VELOCI7Y (FPS)

l I L

I A/H UK I ZON

bKUUNU i EACCIN

MUk iLuN/ BEACGh

TiuKS

LANUMARK

700

300 TO 1000

2000

SY ST EM

1000

4000

1000

1

2

1

1

1

2

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-...30O04 ORBITER/PAYLOAC DATA TRANSFER - INFORMATION FROMTHE GN+C CCMPUTER SUBSYSTEM CAN BE TRANSFERRED ICTHE PAYLCAC BAY VIA HARDOWIREo AS A MINImUM, THEINFCRM.ATICh WILL INCLUDE TIMING, STATE VECTORINITIALIZATICN AND EXTRAPOLATION 1IF DESIRED), ANDSPACECRAFT ATTITUDES AND ATTITUDE RATES.

I.30bO0 STABILIZATION AND CCNTROL

2.300.1 PAYLCAC POINTING ACCURACY - THE DOMINANT ERRORSINVOLVED IN POINTING A PAYLOAD WITH THE SPACECRAFTSYSTEMS ARE CONTRIBUTED BY THE STRLCTURALMISALIGNPENTS AND THERMAL DISTORTIONS. THEGUIDANCE AND NAVIGATION (G+N) SUBSYSTEM ERRORS,INCLLDING AN EQUIVALENT ANGULAR ERROR CUE ICNAVIGATION UNCERTAINTY ARE LESS AT 0.2 DEGREE 11SIGMA). CCNTROL SYSTEM ERRORS, I.E., ATTITUDEDEADBANC EXCURSIONS, MLST ALSO BE ADDED TO THESTATED ERRCR SOURCES.

THE CRBITER IS CAPABLE CF POINTING THE PAYLOADCCNTINUCUSLY FOR ONE ORBIT EVERY CThER ORBIT FCRONE 24-HCUR PERICC PER MISSION AT ANY GROUND,CELESTIAL, CR CRBITAL OBJECT WITHIN +/-0.5DEGREES. PAYLOAD REQUIREMENTS IN EXCESS OF THISCAPABILITY SHOULD eE PROVIDED BY THE PAYLCAD OREXPERIMENT SYSTEMSo

:.0J~b02 REACTICN CCNTROL SYSTEM FIGURE 2.4 SHOWSTHRUSTER LOCATICNS IN THE WING TIP/NOSECONFIGURATION. CURRENT THRUSTER SIZING YIELD THESTABILITY RATES INCICATED IN TABLE 2-V.

TABLE 2-V - VINIMUM ANGULAR STABILITY RATES

* AXIS I STABILITY RATES '

' FITCH ' ITBC)

' YAW ' (TBC)

' ROLL * (TBC)I I a

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Z.J070 PAYLCAC CHECKOUT

PAYLCAD CHECKOUT PROVISIONS ARE COMPRISED GFMISSION SPECIALIST STATION CRT AND KEYBOARD,COMPUTER FOR PAYLCAC MCNITORING, STORED PROGRAMPROCESSCR, PAYLOAD PROVIDEO REGIONAL ACCUISITIONUNITS (RAU'S), RECCRDERS, DISPLAYS AND CCNTROLS,AND PAYLOAD COMMAND DECODER SUBUNITS. FIGURES 2.5AND 2.6 SHOW THESE INTERFACES. THE COMPUTERPROVIDES FCR SOFTWARE, DATA PROCESSING, COMMANDAND CCNTROL, DATA ACQU IS IT ION, AND OISPLAYCAPABILITIES REQUIRED FOR PAYLCAD FUNCTIONALEND-TC-ENC CHECKOUT, AND STATUS MONITORING WHILEINSTALLED IN THE PAYLOAD BAY.

DETAILEC ACCEPTANCE TESTING OF EACH PAYLOAD ITEMIS PERFCRMED PRIOR TO INSTALLATION. CHECKOUT OFTHE FAYLOAC FOR PRELAUNCH OPERATIONS MAKES USE OFTHE GRCUND CHECKOUT EQUIPMENT AND THE ONBOARDCHECKOUT COMMAND CECCODER FOR HARDWIREC UPLINKCOMMANDS. A HARDWIRED PCM DCWNLINK TO THE GROUNDCHECKCUT ECUIPMENT IS ALSO PROVIDED FOR C:ECKOLTDATA, WHICH IS INTERLEAVED WITH ORBITER SUBSYSTEMDATA.

THE PHYSICAL INTERFACES TC THE PAYLCAD FORINFLIGHT USE ARE THE RAUIS AND THE PAYLOAD COMMANDDECCCER SUBUNITS PROVIDED BY THE PAYLOAC. THISALLOWS FCR THE PAYLOAD TC BE COMMANDED FRCM ThEGRCUSGC VIA THE RF LINK OR THE ONBOARD PAYLOADi4GNITCR STATION THROUGH THE COMMAND CECODER9UBUNIT. A KEYBOARD PERMITS THE MISSIONSPECIALIST TC COMMUNICATE WITH THE COMPUTERe AND ACRT PERMITS THE DISPLAY OF PAYLOAD CHECKOLT DATA.

CHECKOUT DATA ARE COLLECTED FROM THE PAYLOAD BYTHE PAYLOAD RAU'S AND SENT TO THE STORED PROGRAMPROCESSOR ISPP)} IT CAN THEN BE INTERLEAVED WITHORBITER OCUNLINK PCM, AND EITHER SENT TO THEGROUND VIA THE RF LINK OR RECORDED UNDER CERTAINCIRCUMSTANCE CN A RECORDER.

2.:3071l PAYLCAC REIGCNAL ACQUISITION UNIT (RAU) - THEPAYLCAC RAU INTERFACES THE PAYLOAD WITH TFE STOREDPROGRAM PROCESSOR [SPP). IT WILL SAMPLE THEPAYLOAD DATA OUTPUTS ON COMMAND FROM THE SPP. THECESIGN REQUIREMENTS FOR THE RAU ARE AS FOLLOWS-

A. THE RAU INTERFACE WITH THE STORED PROGRAMPROCESSOR UTILIZES PARTY LINE TECHNIQUES 10MINiMIZE TIE AMOUNT OF INTERFACE WIRINGRECUIRED.

47

Mission Specialist Station

*Payload supplied

Mission Specialist Station Interfaces

FIGURE -2.5

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Crtkeyboard

IRF uplink--

Ground checkouthardwire downlink

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Checkoutcommanddecoder

Ground checkoutuplink hardwire

Serial data or commands

Payload narrowbandcheckout data

Serial digital checkout commands and data

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ORBITER/PAYLOAD CHECKOUT OF INTERFACE

FIGURE - 2.6

computer

Stored programprocessor

I

49

B. ThE RAU ACCEPTS ANALOG AND DIGITAL SIGNALS INTHE QUANTITIESt AND MIXTURES BASED ON PAYLOADMEASUREMENT REQUIREMENTS.

C. ThE RAU SAMPLES AND DIGITIZES PAYLOAD ANALOGSIGNALS TO THE ACCURACY REQUIRED BY THECCPPUTER AND OTHER CATA USERS.

D. THE RAU SAMPLES PAYLOAD CHECKOUT DATA ATSAIPLING RATES COMPATIBLE WITH THE COMPUTERAND OTHER USER RECUIREMENTS.

E. THE RAU IS PACKAGED TO OPERATE DURING ALLMISSION PHASES IN ThE SAME ENVIRONMENT AS THEVEHICLE SUBSYSTEMS WITH WHICH IT INTERFACES.

4.B70iL PAYLCAC CCPMAND CECCODER SUBUNIT (PCDS) - A SERIALDIGITAL LIAE IS PROVIDED FROM THE COMPUTER THROUGHTHE PCCS. THIS ALLOWS THE PAYLOAD TO BE COMMANDECFROM THE GPCUND CR FRCM THE MISSICON SPECIALISTiSTATICN KEYBOARD. THE PCDS PROVIDES STIMULI ANDCOPPANCS TO THE PAYLOADS FOR OPERATION ORCHECKCUT. THE DESIGN REGUIREMENTS ARE AS FOLLOWS-

A. ACCEPT SERIAL DIGITAL COMMANDS AND PROVIDEVERIFICATION CF CORRECT DIGITALCCMIANDS/SECUENCES FROM THE COMPUTER

8. BE CAPABLE CF SIMULTANEOUS COMMANC/STIMLLIGENERATION, I.E., EMPLOY MULTIPLE PRCGRAMABLEFUNCTION GENERATORS

C. PROVIDING AUTOMATICt BUILTIN CALIBRATIChMEANS UPCN CCMMANOD VIA SERIAL DIGITAL DATAFROM THE COMPUTER

0. BE ENVIRONMENTALLY PACKAGED FOR THE PAYLOADEtV IRCNMENT

-. 30703. HARC[IRE INTERFACES - COAXIAL CABLES AND kIRES ARE:PROVIDEC BETWEEN .THE 'PAYLOAC INTERFACE AND ThEMISSICN SPECIALIST STATION (MSS). THESE CAN BEUSED FCR INTERFACING PAYLOAD PROVIDED CISPLAYStRECORDERS, CCNTRCLS, ET CETERA, INSTALLED IN THECONSOLE AT THE MSS WITH PAYLOADS. STANDARDIZEDINTERFACE CONNECTORS ARE PROVIDED ON THESE WIRES.TI'ME CCODES AND SYNCHRONIZATION FREQUENCIES CAN BEMADE AVAILABLE FROM TfE ORBITER CENTRAL TIMINGUNIT, AND TRANSMITTED TO THE PAYLOAD BY THESEINTERFACES.

50

2.' 000 COMU4N ICAT IONS

FIGURE 2.7 IS A SCIEMATIC DIAGRAM OF THECOFM4NICATICNS PRCVISICNS.

,.i0801 VOICE - THE ORBITER AUDIO COMMUNICATIONS SYSTEMPROVIDES VOICE COMMUNICATIONS FOR PAYLOADOPERATICNS AS FOLLOWS-

A. TWO-WAY' VOICE CCMPUNICATIONS BETWEEN THEPAYLCCD BAY AND GRCUNO

B. . TWC-WAY VOICE CCMMUNICATIONS BETWEEN CREWSTATICNS AND THE PAYLOAD BAY STATIONS

C. RACIO FREQUENCY IRF) VOICE COMMUNICA.TIONSBETWEEN RELEASED PAYLOADS AND THE ORBITER

6. EVA VCICE CCF"UNICATIONS USED ONBCARD THEORBITER OR RELAYED TO THE GROUND. TkO UNIQUEEVA Ct-ANNELS ARE PROVIOED, WITH CONFERENCECAPABILITY TC (TBC) ADDITIONAL EVA'S.

.j10802 WIDEBAND DATA - A HARDWIREC INTERFACE IS PROVIDEDIN ThE PAYLOAD BAY FOR TRANSMISSIGN OF REALTIME ORDELAYEC WICEBAND PAYLOAD DATA TO THE GROUNC. THISLINK ACCCM'OCATES UP TC 256,000 BITS PER SECCNC4BPS) CF DIGITAL DATA CR PROVIDES WIDEBANDC ANALCGDATA. IN EITHER CASE, THE PAYLOAD PROVIDES THENECESSARY EQUIPMENT TO INSURE THAT THE PAYLOADDATA ARE CCMPATIBLE WITH THE ORBITER TRANSMITTER.

Z.3Cu03 OIGITAL DATA - PAYLOAD PCM DATA FRCM RAU'S IN THEPAYLEAD BAY CAN BE TRANSMITTED TO THE GROUNDTHROUGH THE STCRED PROGRAM PROCESSOR ANC S-BANDTRANSMITTER. UP TC 25,COC BPS OF PAYLOAD CATA CANBE TRANSMITTED TO THE GRCUNO BY THIS METHOD. DATAFRCP RELEASED PAYLOADS UP TC 2,0CO BPS CAN BERECEIVED BY THE ORBITER SYSTEM FOR RELAY 10 THEGROUhD, CR FCR TRANSMISSION TO THE COMPUTER USEDFOR PAYLCAD MONITORING.

-. L30)4 TELEVISICN (TV) - TWC COAXIAL INTERFACES AREPROVIDED IN THE PAYLOAD BAY FOR TRANSMISSION CFPAYLCAD TV VIDEO SIGNALS TO THE GROUND, OR 10 THEVIDEC DISPLAYS AT THE PAYLOAD HANDLER STATION.

,.,0d805 UPLINK CCMMANCSICATA - INFLIGHT UPLINK INFORMATIGNFOR ATTACHED PAYLCADS IS ROUTED TO THE COMPUTERFROM THE S-BAND UPLINK COMMAND DECODER. THISINFCRMATICh IS RELAYED TO THE PAYLOAD VIA A SERIALDIGITAL INTERFACE TO THE PCDS. IN ADDITION, THIS

51 I

Receiver

Free flying payload

o0- x ~Shuttle data

Attached payload

Payload TV, widebaneanalog or recorderplayback

ORBITER/PAYLOAD COMMUNICATIONSINTERFACE

FIGURE - 2.7

Xmtr

52

INFCRPMATICN CAN EE RELAYED TO RELEASE PAYLOADS ILPTO A RANGE OF TBC MILES) VIA RF, UP TO 200C0 BPS,COMPANDS ORIGINATEC IN ThE CRBITER CAN ALSO BETRANSMITTED TG THE RELEASED PAYLOADS BY THE SAMEMEAhS. THIS LINK INCLUDES A COMMAND 'CONFIRMATIONCAPABILITY.

2.* j0900 CREW SYSTEMS

2i.*O90L SUPPCRTS AND RESTRAINTS - MOBILITY AIDS AREPRGVIDED IN THE PAYLOAD BAY AND ORBITER STRLUCURE.THESE OCBILITY AIOS INCLUDE STRATEGICALLY LOCATEDHANC-CLDS, TETHER-ATTACHMENT POINTS, AND FOCTRESTRAINTS AT WORK AREAS. SIMILAR- MOBILITY AIDSSHCULD BE PROVIDED ON PAYLOADS WHICH REQUIRE CREWOPERATIONS SUCH AS MAINTENANCE, INSPECTICN,DEPLCYMENT, OR HAeITATION.

.JO0902 EVA SUPPORT EQUIPMENT - THE EVA CAPABILITY FCR AMINIMUM CF TWO CREWMEN IS PROVIDED BY THE ORBITER.TO SLPPCRT EVAt THE ORBITER hAS AN AIRL'CCK, EVAEQUIPMENT STCRAGE AND CONNING AREA, EXTRAVEIICULARLIFE SUPPORT SYSTEM IEVLSS) RECHARGING STATICN,CREW MBCILITY AIDS, AND THE NECESSARYCOMiUNICATION CIRCUITS AND MCNITORING SYSTEMS FCRCN-CFBIT CPERATIONS. THE EVA EQUIPMENT ANDEXPENCABLES ARE AVAILABLE, AND ARE CHARGEABLE TCTHE PAYLOAD. THIS EVA EQUIPMENT INCLUDES - 11)PRESSURE GARMENT ASSEMBLIES IPGA'S) 12) EVLSS9 SJ3) MAhEUVERING SYSTEMS, 14) TOOL KITS, 15)RESTRAINTS, AND 16) PORTABLE LIGHTS. STANDARDTOCOLS AND A TORQUING DEVICE ARE INCLUDED IN THETOCL KIT. SPECIALIZED TOOLS ANO TOOL ADAPTERS AREPROVIDED BY THE PAYLOAD.

4.iuO90 EVA CESIGN CCNSIDERATICNS - THE FOLLOWING ITEMSMUST BE CONSIDEREC IN PAYLOAD DESIGN TO ENSURECOMPATIBILITY WITH ThE EVA CREWMAN TC OBTAINMAXIMUM UTILITY FROM TIME SPENT IN EVA.

A, . HANCHCLDS OR GUIDERAILS ARE PROVIDED ALCNGTHE EVA TRAVERSE WHEREVER POSSIBLE.

B. FCCT RESTRAINTS AND TETHER-HOCK ATTACP POINTSARE PROVIDED AT WORK STATIONS OR WHEREVERPULLING, PUSHING, CR TORQUING ACTIONS AREREQUIRED.

C. MAXIMUM FORCE AND TORQUE CAPABILITIES FOR TIERESTRAINED EVA CREWMEN ARE-

53

TCRCUE - (TBDI FT-LBSFCRCE PULL - (TBO) LBSFORCE PUSH - (TeC) LBS

D. REACH MOBILITY AND VISIBILITY ARE CCNSIDEREDIN WORK STATION DESIGN. TOOLS AND CONTROLSMUST eE COMPATIBLE WITH THE GLOVED HAND.

E. MIXIMUM ENVELOPE CIFENSICNS OF THE PGA/PLSSARE SHOWN IN FIGURE 2.8.

F. LIGHTING LEVELS ARE COMPATIBLE WITH THE TASKSTG BE PERFORMED.

G. SHARP OR DANGEROUS OBJECTS ARE ELIMINATEDFRCM THE EVA ROUTE.

PAYLCAD WEIGHT WHICH CAN BE TRANSFERRED eY THECREWMAN IS DEPENDENT UPON THE PHYSICALCONFIGURATION OF THE PAYLOAD AND THE METHOD OFTRANSFER. PAYLOAD TRANSFERS FROM THE PAYLOAD BAYTO AN EVA WORK STATION CAN BE ACCOMPLISHED BY THECREWMAN CARRYING THE PAYLOAD TO THE WORK STATION,OR BY USING A TRANSFER DEVICE SUCH AS CLCTHESLINETYPE CCNVEYOR. TC CARRY THE PAYLOAD TO ThE WORKSTATICh, TtE CREWMAN GRASPS THE PAYLOAD BY MEANSOF hANChOLCS, OR ATTACHES THE PAYLOAD TO THE PGAOR CThER EVA ECUIPMENT BY MEANS OF RESTRAINTDEVICES.

·.J90'4 EVA AIRLOCK - AN AIRLOCK(S) IS PROVIDED BY THEORBITER WHICH ALLCWS DUAL EVA FROM THE ORBITER.THE AIRLOCK(S) PRCVIDE IVA ACCESS TO THE PAYLOADBAY WITH PAYLOAD COORS CLCSE0, AS WELL AS EXTERMAL-TC THE CRBITER. THE EVA CAPABILITY EXISTS WITH CRWITHCUT AN ORBITAL ELEMENT ATTACHED TO THE DOCKINGPORT.

2.309o0 CREW COMPARTMENT/PAYLOAD BAY ACCESS - AN INTERNALACCESS BETWEEN ThE CREW COMPARTMENT AND THEPAYLCAD BAY IS CESIGNED IN THE ORBITER. THISACCESS ALLOWS SHIRTSLEEVE IVA TRANSFER CFPERSCNNEL AND CARGO THROUGH A HATCH LOCATED IN THEAFT SECTION OF THE CABIN TO A HAEITABLE PAYLOADMCDULE IN THE PAYLOAD BAY. LOCATED WITHIN THEPRESSURIZEC VOLUME OF THIS INTERFACE ARE REDUNDANTPOWEP, C+W, DATA, CCMMUNICATIONS, ANC FLUIDINTERFACE CCNNECTCRS TO SUPPORT HABITABLE PAYLOADSdN THE PAYLOAC BAY.

Z..09CUb ILLUPINATICN - THE ORBITER HAS LIGHTING SYSTEMS TCSUPFCRT ORBITER/PAYLOAC OPERATIONS EXTERNAL TO THEORBITER, INSIDE ThE PAYLOAD BAY, AND INSIDE THE

54

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55

CRE# CCMPARTMENT. THE EXTERNAL LIGHTING SYSTEMPROVIDES ILLUMINATION FOR PAYLOAD DEPLOYMENT,DCCKING, AND RETRIEVAL GPERATIONS. PAYLCAD BAYILLUPINATICN IS AVAILABLE FOR PAYLOAD INSPECTICN,ATTACHED PAYLOAD CPERATIONS. PAYLOAD LATCkING, ANDPAYLCAD RELEASE. THE LIGHTING SYSTEM WITHIN THECABIN ILLUMINATES THE PAYLOAD DISPLAY AND CONTROLSTATICN AT LEVELS WHICH ARE CONSISTENT WITH THECREW CCWPARTMENT ILLUMINATION REQUIREMENTS.

g.3LIUOU ENVIRONMENTAL CONTRCL/LIFE SUPPORT SYSTEM

-. 3'.OU SYSTEM CAPABILITIES - THE ORBITER ENVIRONMENTALCONTRCL/LIFE SUPPORT SYSTEM (ECLSS) BASELINE ISDESIC-NEC TC ACCOMMCCODATE A CREW OF FOUR FOR AMISSICN DURATION OF 7 CAYS. THIS SYSTEM HAS THECAPABILITY TO ACCCMMCCATE UP TO 42 MAN-DAYSWITHCUT SYSTEM CHANGES. WITH MINOR CHANGES, SIXADDITICNAL PEOPLE CAN EE ACCOMMODATED WITI SLIGHTINCREASES IN ATMOSPHERIC DRY BULB TEMPERATURE,HUMICITY, ANC CARBCN DIOXIDE CONTENT.

Z. jiUOZ ATMHCSPERE SUPPLY AND PRESSURE CONTROL - THISSYSTEM IS DESIGNED TO CONTROL AND MAINTAINAUTCPATICALLY A TWO-GAS, SEA LEVEL ECLIVALENTATMCSPHERE (14.7 PSIA, 80-PERCENT NITROGEN,20-PERCENT OXYGEN) WITHIN THE ORBITER CABIN ANDHABITABLE PAYLOAD MODULES.

THE WEIGHT OF ACCITICNAL ATMC SPHERE STORAGEEQIFPMENT AND EXPENDABLES TO SUPPORT MISSIONSBEYCND 28 MAN-DAYS ARE CHARGED TC THE PAYLOAC.THE FAYLCAC SHOULD NOT INTRODUCE ADDITIONAL OXYGENOR NITRCGEN INTO THE HABITABLE ATMOSPHERE.

..3IU0 ACTIVE THERPAL CCNTRGL - THE ORBITER ACTIVETHERMAL CONTROL SUBSYSTEM PROVIDES INTERFACE HEATEXCHANGERS TC REJECT PAYLOAD WASTE HEAT 0O THEORBITER HEAT REJECTION ECUIPMENT. THIS SUBSYSTEM4S CAPABLE OF TRANSFERRING PAYLOAD WASTE HEAT LPTO 5200 BTU/HR DURING PEAK ORBITER OPERATIONSt AND{TBO) BTU/HR DURING ON-ORBIT COAST PERIODS.SUFPLEMENTARY ON-ORBIT HEAT REJECTION IS PROVIDEDBY CRBITER WATER EVAPORATION OR BY PAYLOADSUPPLIEC HEAT REJECTION SYSTEMS. THE PAYLOAD ISALSO RESPONSIBLE FCR PROVIDING THE PAYLOAD HEATTRANSPORT THERMAL CONTROL SYSTEM AND HARCIARE ICINTERFACE WITH THE CRBITER ACTIVE THERMAL CONTRCLSUBSYSTEM INTERFACE HEAT EXCHANGER.

56

-.3LO004 WASTE PANAGEYENT - ALL SOLID AND LIQUID hASTEPRCDUCTS ARE STORED ONBOARD FOR RETURN TO EARTHtHONEVER, AN OVERBCARC LIQUID CLMP SYSTEM ISPROVIDED AS A CONTINGENCY MEASURE. WASTE hATERFRCM PAYLCAC EXPERIMENTS OR OPERAT'IONS ISPROCESSEC ANCD/OR STOREC BY TFE PAYLOAD.

,.iiOO PAYLCAC BAY ENVIRCNPENT

.11.iO1 lACOUSTIC - THE OREITER PAYLOAD BAY INTERICR SOUNDPRESSURE LEVEL WILL NOT EXCEED 145 De.

,'iIOZ YIeRATICh - VIERATICN ENVIRONMENT WITFIN THEPAYLCAL BAY WILL NOT EXCEED CURRENT LAUNCH VEHICLEPAYLEAD ENVIRCNNENTS.

Z.3ii..3 SHCCK - ORBITER/BOOSTER SEPARATICN AND ORBITERLANDING ARE EXPECTED TO INDUCE SHORT DURATI CSHOCK TC THE PAYLCADS.

i. i104 FLIGHT ACCELERATICN LOADS - THE SHUTTLE FLIGHTACCELERATICN LOACS ARE GIVEN IN TABLE 2-VI FOR THEV.ARICUS FLIGHT PHASES. THESE LOAD FACTORS INCLUCETHE CYN^AMIC INDUCED LOADS, AND CARRY THE SIGNS CFEXTERNALLY APPLIED LOACS.

57

TAbLE 2-VI - PRELIPINARY LIMIT LCAD FACTORS FOR PAYLOAD

'LUUIT1 lON* NX (G) * NY (GI NZ (GI a

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1.0 '+/-1.0 ' - '+/- - '+/-- .25'5I 3 I I I

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1.5 '+/-1.0 '+/-0.25'+/-0.5 '+/-0.25"+/-0.5 'I I

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3. 0 '+/-0.25'+/-0.2

1.0 ' +/-1.5 '+/-0.2I I

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58

i.31105 PAYLCaP BAY ATMOSPHERE - THE ORBITER PAYLCOAD BAYCAN BE ATMCSPHERIC CONTROLLED INDEPENDENT CF OTHERPARTS CF TIE ORBITER STRUCTURE WHILE ON THE LAUNCHPAC. THIS PRCVISION ALLOWS THE CONTROL OF THETEMPERATURE. HUMICITY, ATMOSPHERE COMPOSITION, ANDPARTICLE CGNTAMINATION OF THE PAYLOAD BAY BY THEUSE CF' LAUNCH SITE GSE.

THE CRBITER PAYLCAG EAY IS VENTED DURING THELAlUNC AND ENTRY PHASES, AND OPERATESUNPRESSURIZEC DURING THE ORBITAL PHASE Of THEMISSICN. THE PRESSURE ENVIRONMENT CURVES FOR THELAUNCH AND ENTRY PHASES ARE SHOWN IN FIGLRE 2.S.

'.3.iOo CCNTAMINATICN - CCNTAMINATION OF THE PAYLOAD ISMINIMIZED THROUGH CONTROLLED VENTING, MATERIALCCNTRCL, ANC PRELAUNCh ATMOSPHERIC CONTROL.ATTITUDE CCNTROL SYSTEM THRUSTERS ARE DESIGNED ICPREVENT PLUME IMPINGEMENT ON THE PAYLCAD CRPAVLCAC BAY.

2.3110 7 THEPRIAL ENVIRONMENT AND CCNTROL - THEDETERMINATION OF PAYLOAD TEMPERATURE ANCTEMPERATURE ENVIRCNMENTS WHICH THE PAYLOAD WILLACTUALLY EXPERIENCE IN THE PAYLOAD BAY REQUIRESKNCNLECCE OF THE SPECIFIC MISSION ENVIRONMENT FROMBOGST THROUGH ENTRY. THE TYPE OF THERMAL CONTROLPRCVIDEC BY THE SHUTTLE VEHICLE ANC THE PAYLOAC.AND THE PAYLOAD BAY AND PAYLOAD THERMALCHARACTERISTICS. TO OBTAIN THIS INFORMATICNRECLIRES DETAILED KNOWLEDGE CF THE ACTUAL SHUTTLEAND PAYLOAD CESIGN, AS WELL AS THE SPECIFICINFLIGHT ORIENTATICNS WHICH PROBABLY WILL VARY FGREACH DIFFERENT MISSICN OBJECTIVE. AS SHUTTLEPAYLCAC BAY AND PAYLOAC THERMAL DESIGN CRITERIA ISCURRENTLY ENVISICNEU, THE FOLLOWING DESIGNREQUIREMENTS HAVE BEEN IMPCSED ON THE SHUTTLEVEHICLE THERMAL DESIGN.

THE INTERNAL WALL TEMPERATURE LIMITS FOR THEPAYLCAC BAY, NOT CCNSIDERING PAYLOAD HEAT ADDITICNOR REMOVAL SHALL REMAIN WITHIN THE RANGES NOTED INTHE FCLLCWING TAELE-

59

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60

CONDITICN MINIMUM ( F) MAXIMUM ( F)

PI:LAUNLH 440 +120

LAUNCH +40 +150

LUN-URkIT (DOGR-CLCSEC) -100 +150

:NTRY AND POST LANCING -100 +200

AS AN CN-OtBIT THERMAL CONTROL POINT-DESIGN FORSIZING THE NCOMINAL PAYLOAD PASSIVE THERMAL CONTRCLPRCVIDEC BY THE CRBITER, THE PAYLOAD BAY ISDESIGNEO TC LIMIT THE NET HEAT LEAK INTO OR OUT OFA 100-CEGREE FAhRENHEIT CONSTANT TEMPERATLREPAYLCAD TO 3 BTU/HR/SQUARE FOOT, WITH THE PAYLCACDOORS CLOSED UNDER WORST-CASE CRBITALORIENTATIONS.

PROVISICNS ARE INCORPORATEC IN THE PAYLOADBAY-WALL DESIGN FCR ATTACHMENT AND REMOVAL OFPASSIVE THERMAL CONTROL IN MODULAR FORM TC MEETVARIABLE PAYLOAD THERMAL CONTROL REQUIREMENTS.

THE TEMPERATURE LIPITS SPECIFIED FBR TkEPRELAUNCH, LAUNCh, ANC ENTRY PHASES PROVIDE ADESIGN ENVIRCNMENT INTERFACE BETWEEN THE PAYLOADAND FAYLCAC BAY, WHICH REPRESENTS CONSERVATIVEPAYLCAC BAY-WALL ENVIRCNMENT TEMPERATURES FOR APASSIVE PAYLOAD. BECAUSE OF THE VARIABLE NATUREOF THE ON-ORBIT PAYLOAD BAY THERMAL CONTRCLREQUIREMENTS, CAUSEC BY VARIATIONS IN TPE ORBITTHERPAL ENVIRONhMENT AND PAYLOAD THERMALREQLIREPENTS, FLEXIBILITY IN MEETING THESENARIATICNS IS PRCVIDED BY REMOVAL AND PLACEMENT CFDIFFERENT PASSIVE INSULATION SYSTEMS AS REQUIREC.AN CN-CRBIT POINT CESICN REQUIREMENT PROVIDES FCRNOMINAL PAYLOAD EAY PASSIVE THERMAL CONTROL IN THEPAYLCAD BAY DESIGN.

IF THE PAYLOAD BAY CANNOT BE PASSIVELY CONTROLLED,PRCVISICNS FOR LIMITED ACTIVE THERMAL CONTROL CFTHE PAYLCAC IS AVAILABLE FROM THE SHUTTLE ORBITER,ACTIVE PAYLOAD THERMAL CCNTROL IS SUPPLIED BY -THEORBITER ACTIVE FLUID LOOP SYSTEM THROUGH -A HEATEXCHANGER IN THE ORBITER TO SUPPORT THE PAYLOAD INTHE PAYLCAD BAY. THE. HEAT TRANSFER CAPACITY FCRPAYLOADS EQUIPMENT IS-

61

A. PEAK CAPACITY OF 5200 BTU/HR DURING PEAKCRBITER CPERATIONS

B. PEAK CAPACITY OF (TBD) BTU/HR DURING CN-ORBITCCAST PERIOCS

SINCE A MINIMUH ENERGY ALLOUANCE OF 50 KWH ISPRCVIDEC BY THE ORBITER ELECTRICAL POWER SYSTEMFOR PAYLCAC SUPPCRT. A PCRTICN OF THIS POWER CAN8E UTILIZEC FOR ACTIVE HEATER THERMAL CONTROL,DEPENDING UPON OTHER PAYLOAD ELECTRICAL POWERREQU IREPENTS

Z.iALOo RADIATICh - RADIOACTIVE SOURCES CN THE OReITER ARECCN'TPRLLEC TO RECUCE STRAY SIGNAL SOLRCES ICEXPERIMENTS OR PAYLCADS CARRIED BY THE CRBITER.PAYLCAD SUPPLIEO RACIOACTIVE SOURCES ARE APPROVEDTHRCLGI- THE ORBITER INTEGRATION CENTER (MSC) TCMEET ALL FLIGHT AND SAFETY REQUIREMENTS.

62

qi.400 SAFETY, RELIABILITY, AND QUALITY ASSURANCE

Z.4U010 SHUTTLE CAPABILITIES

2.40101 ABORTS - TIE SHUTTLE IS DESIGNED TO PROVIDE SAFEMISSION TERMINATICN CAPABILITY FOR ALL FLIGHTREGIMES. SAFE MISSION TERMINATION INCLIOES THEINTACT RETURN OF PAYLOADS TO EARTH.

.4'01u CREW AND PASSENGER EGRESS - EMERGENCY EGRESSCAPAEILITY FOR TIE CREW ANC PASSENGERS IS PROVIDEDFOR PRELAUNCH AND POSTLANDING OPERATIONS.

o.4 10: CAUTICN ANC WARNING - THE SHUTTLE PRCVIDES ACAU-TIEN ANDC WARNING SYSTEM FOR PROCESSING ANDDISPLAYING CRITICAL PAYLOAD DATA. SEE SECTION2.30400 FOR A CESCRIPTION OF THE CAUTICN AONWARNING SYSTEM.

i.40104 PAYLCAD CONTROL - THE SHUTTLE PROVIDES A LIMITEDHARDWARE AND RF CONTROL CAPABILITY TO PROVIDECORRECTIVE MEANS TO CIRCUMVENT CATASTROPHIC EVENTSFRCM- OCCURRING, ANC FOR ACTIVATION ANDDEACTIVATICN OF PAYLOAD SYSTEMS. SEE SECTIONS2.30700 ANC 2.30800 FOR MORE DETAILS.

,.4U105 DUPFS AND VENTS - THE CAPABILITY TGO DUMP LIQUIDSAND VENT GASES IS PROVIDED. INTERCONNECTS TO THEDUMP ANC VENTING SYSTEMS ARE AVAILABLE TC SAFELYREMOVE LIQUIDS AhC GASES FROM THE PAYLOAD BAY, IFREQUIRED.

,.4iU06 PURGE - A NITROGEN PURGE CAPABILITY IS PROVIDECFOR INERTING THE PAYLOAD BAY PRIOR TO LAUNCH.

.4 OOO PAYLOAD

,i.40,iI PURPCSE AND SCOPE - THE FIRST INTENT OF THISSECTION IS TC DEFINE MINIMUM SAFETY, RELIABILI t7,AND CUALITY ASSURANCE REQUIREMENTS TO BE INVOKED'ON PAYLCOAD SUPPLIERS. THESE REQLIREMENTSCONSIDER PRIMARILY THE SAFETY, RELIABILITY, ANDQUALITY ASSURANCE CF PAYLCAD HAZARCDS ThE NORMALOPERATICh CR FAILURE OF WHICH COULD CAUSE HAZARCSTO PERSONNELt OR CAMAGE TO THE SHUTTLE SYSTEMtRELATED FACILITIES, OR OTHER PAYLOAD ELEMENTS.SECCNC, THE COMPATIBILITY OF THE PAYLOAD WITH THESHUTTLE INTERFACES IS ALSO A CONCERN.

63

i,4OiOZ GENERAL REQUIREMENTS - THE PAYLCAD SUPPLIER IcRESPCNSIBLE FOR THE FOLLOWING SAFETY, RELIABILITY,AND CUALITY ASSURANCE ACTIVITIES-.

A. THE DETERMINATION OF THE HAZARiOUS ASPECTS CFHIS PAYLOA£ AND THE IMPLEMENTATION GFRECUIREC CORRECTIVE MEASURES.

B. ASSURANCE OF THE COMPATIBILITY OF HIS PAYLOADWITH THE SHUTTLE INTERFACES.

C. IOENTIFICATICN TC NASA OF THE UNRESCLVEDRESIOUAL HAZARCS AND INTERFACEINCCPFATIBILITIES PRIOR TO NASA APPROVAL CFHIS PAYLCAD.

0. THE ON-ORBIT FUNCTICNAL RELIABILITY. QUALITY,AND SAFETY OF HIS PAYLOAD.

* U.S. GOVERNMENT PRINTING OFFICE: 1972-779-467/145