NASA Space Shuttle STS-116 Press Kit

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December 2006 CONTENTS i

CONTENTSSection PageSTS-116 MISSION OVERVIEW: POWER RECONFIGURATION HIGHLIGHTS

S T AT I O N AS S E M BL Y M I S S I ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1S T S -1 1 6 T I M E L INE O V E R V IE W . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 0M I S S I O N P R I O RI T I E S . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 L AU NCH AND L ANDI NG . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . 1 5

LA U N C H . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A B O R T- TO - O R B I T (A TO ). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15TR A N S A TLA N TI C A B O R T LA N D I N G (TA L) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 R E TU R N - TO - LA U N C H - S I TE (R TLS ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A B O R T O N C E A R O U N D (A O A ). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15LA N D I N G . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

M I S S I O N P R O FI LE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . 1 6 S T S -1 1 6 DI S CO V E R Y CR E W . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . 1 7M I S S I O N P E R S O NNE L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .27 R E NDE ZV OU S AND DO CK I NG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . .2 8

U N D O C K I N G , S E P A R A TI O N A N D D E P A R TU R E . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 1INTERNATIONAL SPACE STATION ELECTRIC POWER SYSTEM (EPS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

ACT I V E T HE R M AL CO NT RO L S YS T E M ( AT CS ) O V E R VI E W .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 0 S P ACE W AL K S . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . .65

E V A 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 6E V A 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 7 E V A 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 9

P AYL O AD O V E R VI E W . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .71 I N TE G R A TE D TR U S S S E G M E N T P 5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1 I N TE G R A TE D C A R G O C A R R I E R (S P A C E H A B ). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 7LO G I S TI C S S I N G LE M O D U LE (S P A C E H A B LS M ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 8


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December 2006 CONTENTS ii

Section PageE X P E R I ME NT S . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . .7 9

D E TA I LE D TE S T O B J E C TI V E S . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 9S H O R T- D U R A TI O N B I O A S TR O N A U TI C S I NV E S TI G A TI O N (S D B I ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 9S H O R T- D U R A TI O N R E S E A R C H A N D S TA TI O N E X P E R I M E N TS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 0E U R O P E A N S P A C E A G E N C Y E X P E R I M E N TS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 4

SPACE SHUTTLE MAIN ENGINE ADVANCED HEALTH MANAGEMENT SYSTEM . . . . . . . . . . . . . . . . . . . . . . . .89 S HU T T L E R E FE R E NCE DAT A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .90

ACR O NYM S AND ABBR E VI AT I O NS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . 1 0 3 M E DI A AS S I S TANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 1 8P U BL I C AFFAI R S CO NT ACT S . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 1 9


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December 2006 MISSION OVERVIEW 1

STS-116 MISSION OVERVIEW:

POWER RECONFIGURATION HIGHLIGHTS

STATION ASSEMBLY MISSION

Withitscranestillattached,theorbiterDiscoverywasmated

totheexternaltankandsolidrocketboostersonthemobile

launcherplatforminhighbay3oftheKennedySpace

CenterVehicleAssemblyBuilding.


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SpaceShuttleDiscoverylaunchesinDecember

onits33rdmissiontodeliveranothertruss

segmentoftheInternationalSpaceStationand

beginthe

intricate

process

of

reconfiguring

and

redistributingthepowergeneratedbytwo

pairsofU.S.solararrays.

Theshuttlelauncheswithsevenastronauts

sixshuttleandonelongdurationstationcrew

member. Thisisthefirstcrewmemberrotation

infouryearsinvolvingashuttleratherthana

RussianSoyuz.

TheprimaryassemblyhardwareDiscoverywill

deliverto

the

space

station

is

the

$11

million

IntegratedTrussSegmentP5,whichmeasures

11feetlongby15feetwideby14feethigh(3.3

x4.5x3.2meters). Itwillserveasaspacerand

bemated

to

the

P4

truss

that

was

attached

in

SeptemberduringtheSTS115missionof

Atlantis.

Attachmentofthe4,000pound

(1,800kilogram)P5setsthestageforthe

relocationtoitsfinalassemblypositionofthe

P6trussandthepairofsolararraysthathave

beenlocatedtemporarilyatopthestations

Unitymoduleforsixyears.

AcomputergeneratedartistsrenderingoftheInternationalSpaceStationafterflight

STS116/12A.1,followingthedeliveryandinstallationofthethirdporttrusssegment

(P5)andtheretractionoftheP6portsolararraywingandtworadiators.


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Threespacewalks(ExtravehicularActivitiesor

EVAs)spreadacrossthesevendaysofdocked

operationswillinvolveP5installationand

reconfigurationof

cables

so

that

flight

controllersinMissionControl,Houston,can

sendcommandstoswappowergenerationand

distributionfromhalfoftheP6arraystothe

newestP4pair(powerchannel2/3movesto

P42Aand1/4movestopowerchannelP44A).

InadditiontotheP5spacer,Discoverys

payloadbayalsohousesasmallpressurized

logisticsmoduleholdingsuppliesandan

integratedcarrierdeliveringspacestation

hardwareandthreesmallsatellitestobedeployedaftertheshuttlehasundockedfrom

thespacestation.

The20thshuttlemissiontotheInternational

SpaceStationrepresentsthemost

choreographedassemblyflighttodatebetween

theshuttleandstationcrewmembersandflight

controllersinMissionControl,whowillsend

allcommandstocarefullyredistributepower

andthermal

management

from

one

location

to

another. TheSTS118missioninthesummerof

2007willdeliveranidenticalshortspacer(S5)

totheoppositeendofthestationstruss.

Discoverywilllaunchwithsevencrew

members,includingCommanderMark

Polansky,PilotWilliam(Bill)Oefelein

(Commander,USN),andMissionSpecialists

NicholasPatrick,Robert (Bob) Curbeam(Captain,

USN),JoanHigginbotham,ChristerFuglesang

representingtheEuropeanSpaceAgency,andSunitaWilliams.Williamswillreplacecrew

memberThomasReiter(ESA)whowillreturn

toEarthaboardDiscoveryinherplace.

Williamswillreturnhomenextsummer

followingEndeavoursSTS118mission.

Attiredintheirtrainingversionsoftheshuttlelaunchandentrysuit,astronauts

MarkL.Polansky(left),STS116commander,andWilliamA.Oefelein,pilot,

occupythecommanderandpilotsstationduringatrainingsessioninthefixed

baseshuttlemissionsimulator(SMS)intheJakeGarnSimulationand

TrainingFacilityatJohnsonSpaceCenter.


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Thelaunchfromcomplex39BattheKennedy

SpaceCenter,Florida,istimedpreciselyto

occurwithinthesamelaunchplane(similartoa

laneon

ahighway)

as

the

space

station

to

maximizepropellantsavingsandminimize

rendezvoustime.

Becauseoftheexcellentperformanceofthe

shuttlesexternaltankinminimizingfoam

sheddingduringascent,andtheabilityto

performa100percentinspectionoftheorbiter

thermalprotectionsystemforunlikelydamage,

therestrictionfordaylightonlylauncheshas

beenlifted. ThisallowsDiscoveryslaunchto

takeplaceatnightforthefirst10daysofitswindow,whichopensnoearlierthanDec.7

andclosesonoraboutDec.26basedonasun

betaangleconstraint.

Thefirstthreedaysofthemissionnearlymirror

thoseofthepreviousthreeshuttleflightsto

inspectthethermalprotectionsystemtilesand

thewing

leading

edge

reinforced

carbon

carbon

panels,andrendezvousanddockwiththe

InternationalSpaceStation.

Patrickistheprimeshuttleremotemanipulator

system(roboticarm)operatorandwillleadthe

inspectioneffortusingtheRemoteManipulator

System(RMS)extensiontheOrbiterBoom

SensorSystem. PolanskyandOefeleinserveas

backupshuttlearmoperators.

Thehighest

priority

tasks

of

the

flight

will

be

to

transferonestationcrewmemberforanother,

installthenewP5shortspacer,reconfigurethe

electricalpowersystemandthermalcontrol

systemandtransferextraoxygentostorage

tanksontheoutsideoftheU.S.QuestAirlock.

AstronautNicholasJ.M.Patrick,STS116missionspecialist,participates

inatrainingsessioninthecrewcompartmenttrainer(CCT2)inthe

SpaceVehicleMockupFacilityatJohnsonSpaceCenter.


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IntheKennedySpaceCenterSpaceStationProcessingFacility,anoverheadcrane

movestheP5trussformissionSTS116tothepayloadcanister. Thethirdport

trusssegment,theP5willbeattachedtotheP3/P4trussontheInternational

SpaceStationduringthe11daymission.

Afterdocking,thefirstpriorityistotransfer

formfittingseatlinersintheSoyuzspacecraftmakingWilliamsanofficialmemberofthe

Expedition14crewalongwithCommander

MichaelLopezAlegriaandFlightEngineer

MikhailTyurin. Reiterthenbecomesamember

oftheshuttlecrewwithwhichhewillreturn

homeafterasixmonthstayonthestation.

Onflightday3,PatrickwillcarefullylifttheP5

spacerwiththeshuttleRMSandhandittothewaitingstationarm. Higginbothamand

Williamswillcontrolthestationarmatthe

stationsroboticworkstationintheDestiny

Laboratory. Thespacerwillremainonthe

stationsarmovernightinpreparationfor

installationthenextdayduringthefirstofthree

plannedspacewalks.


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AstronautsRobertL.Curbeam,Jr.andChristerFuglesang,STS116missionspecialists,

wearingtrainingversionsoftheExtravehicularMobilityUnit(EMU)spacesuit,

participateinanunderwatersimulationofextravehicularactivity(EVA).

CurbeamandFuglesangaredwarfedbystationtrusssegmentsinthis

overallviewofthesimulationconductedintheNeutralBuoyancy

Laboratory(NBL)neartheJohnsonSpaceCenter.

Thedayafterdocking(flightday4),CurbeamandFuglesangwillleavetheQuestAirlockona

sixhourspacewalktoassistwithinstallation

andutilityconnectionsbetweentheP5short

spacerandtheP4truss.

Theconnectiontasksincluderemovaloffour

launchlockswiththetwotrusssegments

approximately612inchesapart. The

spacewalkersthenwillserveasonthescene

observersforalignmentandinstallationofP5to

P4. Theinstallationiscompletedwiththe

matingofsixutilitycables.AstronautRobertL.Curbeam,STS116

missionspecialist,attiredinatrainingversion

oftheExtravehicularMobilityUnit(EMU)

spacesuit,awaitsatrainingsessioninthe

watersoftheNeutralBuoyancyLaboratory

(NBL)nearJohnsonSpaceCenter.


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EuropeanSpaceAgency(ESA)astronautChristerFuglesang,STS116missionspecialist,

participatesinanExtravehicularMobilityUnit(EMU)spacesuitfitcheckintheSpace

StationAirlockTestArticle(SSATA)intheCrewSystemsLaboratoryattheJohnson

SpaceCenter. AstronautWilliamA.Oefelein,pilot,assistedFuglesang.

Betweenthefirstandsecondspacewalksbegins

aprocessofpowerandthermalreconfiguration

thathasneverbeenattemptedbefore. Groundcommandingremovespowerfromonehalfof

theP6solararrayfollowedbytheretractionof

itsportarray. Aminimumof40percentofthe

arraymustberetractedtoprovideenough

clearanceforactivationoftheP4solararray

trackingrotaryjointtestedduringtheprevious

shuttlemission(STS115). Thestarboardsolar

arrayofP6willberetractedduringSTS117

nextMarchbeforeinstallationoftheS3/S4setof

solararrays

on

the

integrated

truss

structure

of

thestation.

ThoughfullretractionoftheP6portarrayis

notnecessary,itisplannedinathreestep

processbudgetedforfivehours,withretraction

ofthreebaysfirst. Thentheportarraywill

continuetoberetractedtoapproximately40

percent,andfinallytoonebay.

Thenextfourhoursincludesfillingoneofthe

thermalcontrolsystemswithammoniabefore

thefinalretractionofthesolararrayintoitscanister.

Onceautomaticsuntrackingisconfirmedfor

thenewP4arrays,thestageissetforthenext

dayssecondspacewalktoreconfigurepower

totheoutboardarrays. Thisrequiresprecise

coordinationbetweenthegroundandcrewto

ensureelectricalpowerisnotflowing.

TheUnitedStatesOrbitalSegment(USOS)

electricalpowersystem(EPS)isdividedintothreemainsubsystems: primary,secondary

andsupportsystems. ThegoalwhileDiscovery

isdockedistoreconfigurethestationspower

systemfromthecurrenttemporarystatustoits

assemblycompleteconfiguration.


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TheS0trusssegmentsitsinthemiddleposition

onthetrussstructureontopoftheU.S.Destiny

Laboratory,flankedbytheS1andP1truss

elements.That

truss

and

the

S1

and

P1

trusses

containthemajorelectricalcomponentsofthe

permanentelectricalsystem. Thosearethe

MainBusSwitchingUnits(MBSUs)andlarge

transformerscalledDCtoDCconverterunits

(DDCUs)thatservetomodulatesolararray

powertotheproperlevelsrequiredtooperate

stationsystems.

S1andP1alsohousethestationstwo

independentcoolingsystems,eachofwhich

includelargeammoniatanks,anitrogengaspressurizationsystemandamassivepump

moduletoenableammoniatoflowthrough

plumbinglinestoradiatorsthatwilldissipate

heatfromtheavionicssystemsonthestation.

TherearethreesuchradiatorsonS1andthree

onP1. Tofacilitatethatheatrejection,the

radiatorsaremountedonarotatingbeamthat

canpoint

them

toward

deep

space

and

away

fromthesun.

Forthesecondtimeinthreedays,Curbeamand

FuglesangwillheadoutoftheQuestAirlockon

themissionssecondspacewalkonthesixth

dayofthemissiontoreconfigurepartofthe

powerchannel(2/3)byroutingprimarypower

throughtheMBSUs.

WilliamsjoinsCurbeamonthethirdspacewalk

onthe

eighth

day

of

the

mission

to

do

the

same

reconfigurationontheotherhalfofthepower

channel(1/4). Oefeleinwillserveasthein

cabinchoreographerforallspacewalksand

spacesuitcheckout.

AstronautsSunitaL.Williams(left),Expedition14flightengineer,and

JoanE.Higginbotham,STS116missionspecialist,usethevirtualreality

labattheJohnsonSpaceCentertotrainfortheirdutiesaboardthespace

shuttle. Thistypeofcomputerinterface,pairedwithvirtualreality

traininghardwareandsoftware,helpstopreparetheentireteam

fordealingwithspacestationelements.


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Mountedonthecentraltrusssegment(S0)

launchedinApril2002,thesefourMBSUshave

neverbeenactivated,butwerecheckedout

duringthat

mission

and

again

in

December

2002.

Whilethecrewmembersprepareforthesecond

andthirdspacewalks,alengthysetofpower

downcommandswillbeexecutedbyflight

controllerstoplaceallassociatedequipmentin

asafeconfigurationbeforeopeningtheDirect

CurrentSwitchingUnitremotebusisolators.

BecausetheMBSUsgenerateheatwhencurrent

isflowing,

they

require

cooling

via

the

ammonialoops. EstimatesshowtheMBSUs

canrunwithoutcoolingforaboutonehour,so

wellchoreographedcommandingisplannedto

activatetheammoniapumpmoduletoprovide

coolingtotheMBSUswithinthattimeframe.

Oncethepowerreconfigurationiscomplete,

thestationsnewestpairofsolararraysonthe

portsideofthetrusswillbebroughttolifeto

provideelectricalpowertothestation.

Throughoutthemission,transferofcargofrom

thepressurizedmodule(SPACEHAB)in

Discoveryspayloadbaytakesplaceto

resupplythestation.

Hardwarestowedinthemoduleincludesa

VideoBasebandSignalProcessor,aRotaryJoint

MotorControllerAssembly,anExternalTV

CameraGroup(ETVCG),OxygenGeneration

System,AdjustableGrappleBar;RemotePower

ControlModule(s),NickelRemovalAssembly

Kit,CharcoalBedAssembly,

Desiccant/Adsorbentreplacementunit,Control

MomentGyroElectricalAssemblyandan

AvionicsAirAssembly.

Aftertheoutsideworkiscompletedandbefore

Discoverydeparts,thestationsMobile

Transporterwillberelocatedtothestarboard

endofthetrussandwillundergoacheckoutin

preparationforthenextshuttlevisit,scheduled

forMarch

2007,

to

deliver

another

truss

segmentandthethirdpairofsolararraysa

mirrorimageflighttothatofAtlantisonthe

STS115missioninSeptember.

Onflightday9,(thedayafterEVA3),the

MobileTransporterwillbemovedtothe

starboardendofthetrussandundergoa

checkoutinpreparationforitssupportofthe

nextassemblymissionnextMarch.

Oncetransfers

are

complete,

the

shuttle

will

undockfromthestation,conductaflyaround

andmovetoastationkeepingdistanceofabout

40miles.

Backonitsown,Discoveryscrewwilloversee

afinalinspectionoftheorbitersthermal

protectionsystemtoensureithasnotsustained

anydamagefrommicrometeoroiddebrisbefore

theshuttleisclearedforentry. Thecrewwill

alsoremotelydeploythreesmalltechnology

demonstrationsatellitesmountedinside

canistersalonganequipmentcarrierinthe

payloadbay.

ThecarrieralsoholdstheServiceModule

DebrisPanels,15AdjustableMassPlatesand

anISSPassiveFlightReleasableAttachment

Mechanism.

Activitiesonthedaybeforelandinginclude

stowageofgearandcheckoutoforbiterentry

andlandingsystems,includingtheflight

controlsurfacesandthrusterjetsusedfor

on-orbitandentrysteering.

Discoveryisscheduledtolandthefollowing

dayattheKennedySpaceCenter,completing

the117thshuttlemission.


14/135


15/135

December 2006 TIMELINE OVERVIEW 10

STS-116 TIMELINE OVERVIEW

FLIGHT DAY 1: Launch PayloadBayDoorOpening SpacehabModuleActivation KuBandAntennaDeployment ShuttleRobotArmPowerUp ExternalTankHandheldVideo,Umbilical

WellImagery

and

Wing

Leading

Edge

SensorDataDownlinkFLIGHT DAY 2:

ShuttleRobotArmCheckout

ShuttleRobotArmGrappleofOrbiter

BoomSensorSystem(OBSS)

InspectionofShuttleThermalProtection

SystemandWingLeadingEdgeReinforced

CarbonCarbon

(RCC)

OBSSBerthing

SpacesuitCheckout

OrbiterDockingSystemOuterRing

Extension

AirlockPreparations

RendezvousToolCheckout

FLIGHT DAY 3: RendezvousOperations

TerminalInitiationEngineFiring

RendezvousPitchManeuverandISSDigital

PhotographyofDiscovery

DockingtotheInternationalSpaceStation

HatchOpening

and

Welcoming

by

Expedition14Crew

SuniWilliamsjoinsExpedition14crewwith

Soyuzseatlinertransfer;ThomasReiter

joinsshuttlecrew

ShuttlerobotarmgrappleofP5spacertruss

andhandofftostationrobotarm

CurbeamandFuglesangsleepinQuest

Airlockforspacewalkprebreathecampout

protocol

FLIGHT DAY 4:

StationrobotarminstallsP5spacertruss

installationonP4trussattachment

CurbeamandFuglesangEVA#1toconnect

P5/P4powercables,releaselaunch

restraintsandtochangeoutTVcameraon

S1truss

MobileTransporter

moves

from

Worksite

7

toWorksite3

FLIGHT DAY 5:

P6trussportarrayisretractedtoenable

SolarAlphaRotaryJointactivationand

rotationonP4truss

P4SolarAlphaRotaryJointactivationand

autotrackingofthesun

Portside

loop

of

External

Active

Thermal

ControlSystemisfilledwithammonia

CurbeamandFuglesangsleepinQuest

Airlockforspacewalkprebreathe

campoutprotocol


16/135

December 2006 TIMELINE OVERVIEW 11

FLIGHT DAY 6:

ISSpowerdownofelectricalchannels2

and3

CurbeamandFuglesangEVA#2to

reconfigureelectricalchannels2and3,

relocateCrewEquipmentTranslationAid

(CETA)carts1and2

ISSTreadmillVibrationIsolationSystem

gyroscopereplacementandmaintenance

PortsideloopoftheExternalActive

ThermalControlSystemisactivatedto

allow

ammonia

to

flow

ISSpowerupofelectricalchannels2and3

FLIGHT DAY 7:

ShuttletoISStransferwork

JointCrewNewsConference

Crewoffdutytime

StarboardsideloopofExternalActive

ThermalControl

System

is

filled

with

ammonia

CurbeamandWilliamssleepinQuest

Airlockforspacewalkprebreathecampout

protocol

FLIGHT DAY 8:

ISSpowerdownofelectricalchannels1

and4

Curbeamand

Williams

EVA

#3to

reconfigureelectricalchannels1and4and

transferServiceModuleDebrisPanelsto

PressurizedMatingAdapter3

StarboardsideloopoftheExternalActive

ThermalControlSystemisactivatedto

allowammoniatoflow

ISSpowerupofelectricalchannels1and4

FLIGHT DAY 9:

ShuttletoISStransferwork

MobileTransporter

moves

to

Worksite

2for

S3/S4surveyforSTS117,thenreturnsto

Worksite4

Rendezvoustoolcheckoutinpreparation

forundocking

FLIGHT DAY 10:

Finaltransferwork

FarewellsandHatchClosing

UndockingandISSflyaround

FinalseparationfromISS

MEPSIpicosatellitedeploy

ANDEpicosatellitedeploy

FLIGHT DAY 11:

FlightControlSystemCheckout

Reaction

Control

System

Hot

Fire

Test

CabinStowage

RAFTpicosatellitedeploy

DeorbitTimelineReview

RecumbentSeatSetUpforReiterin

middeck

KuBandAntennaStowage

FLIGHT DAY 12: DeorbitPreparations

PayloadBayDoorClosing

DeorbitBurn

KSCLanding


17/135

December 2006 MISSION PRIORITIES 12

MISSION PRIORITIES

1.Perform

inspection

of

space

shuttle

reinforcedcarboncarbon(RCC)and

downlinksensordataforevaluationonthe

ground.

2. Documentspaceshuttletileduring

rendezvouswithstationusingISSimagery

resourcesduringtherendezvouspitch

maneuver(RPM),followedbydocking.

3. CompleteISScrewmemberswap

(Expedition14

Flight

Engineer

Suni

WilliamsforExpedition13FlightEngineer

ThomasReiter).

InstalltheSoyuzseatliner,knownas

theIndividualEquipmentLinerKit

(IELK)

CheckouttheRussianlaunch/entrysuit,

knownastheSokolsuit

ISSsafety

briefing

Transfermandatorycrewrotationitems

(a) TransferrequiredoxygentoISS(~100

pounds).

(b) TransferandreturnElektron.

4. Transferwater.

5. InstalltheP5trusssegmentontoP4using

theshuttleandstationroboticarms.

RemoveP5inboardlaunchlocks

(requiredformatingwithP4)

Installfourtrussattachmentboltsto

structurallymateP5toP4

RemoveP5

grapple

fixture

and

relocate

toP5keel(willallowP4betagimbal

assemblytorotate)

6. DeactivateP62BloadsandreconfigureU.S.

segmentloadstoreceivepowerdistribution

fromP42AandP6EBviamainbus

switchingunits2and3. Thisincludes

establishmentofactivecoolingforchannel

2/3MBSUsandDCtoDCconverterunits

viaexternalactivethermalcontrolsystem

loopB.

RetractP64Bsolararraywingtoone

bayandinitiateP3/P4solaralpharotary

jointtracking.

RemoveP13ADCtoDCconverter

unitEthermalcovers.

7. DeactivateP64BloadsandreconfigureU.S.

segmentloadstoreceivepowerdistribution

fromP4

4A

main

buss

switching

unit

1and

4. Thisincludesestablishmentofactive

coolingforchannelMBSUs/DDCUsvia

externalactivethermalcontrolsystemloop

A. (P64Bchannelconfiguredto

dormant/parachutemode.

RemoveS14BandS04BDCtoDC

converterunitEthermalcovers.

UplinktheD1patchtoportable

computersystem

R9.

8. Transfercriticalcargoitemspertransfer

prioritylist.

9. TransferZvezdaServiceModuledebris

panelsandadaptertopressurizedmating

adapter3aftgrapplefixture.


18/135


10.RelocatebothCrewandEquipment

TranslationAid(CETA)cartsfromthe

starboardsidetotheportside.

(a) Performcontingencyspacewalkto

completeprimarymissionobjectives.

(b) PerformlateinspectionofDiscoverys

wingleadingedgeandnosecap.

11.Performminimumcrewhandover

(12hours)forrotatingcrewmembers.

(a) PerformtheOxygenRecharge

CompressorAssembly

and

Carbon

DioxideRemovalAssemblyremoval

andreplacementandreturnremoved

hardwareviashuttle.

12.Performutilizationactivitiestosupport

experiments,includingmidodrine,ALTEA,

LatentVirus,SleepShort,andPMDIS.

13.PerformdailyISSpayloadstatuschecksas

required.

14.Transferremainingcargoitemspermission

rules.

15.Performexternalwirelessinstrumentation

systempowerconnectionsbetweenP5and

P4.

16.RemoveandreplaceExternalTelevision

CameraGroup(ETVCG)atCameraPort3,

Starboard1OutboardLower.

17.Transfertheadjustablegrapplebarfrom

insidethestationtotheflexhoserotary

coupleronexternalstowageplatform2.

18.PerformP64Bfinalretractionandlatching

ofthesolararrayblanketbox.

19. InstallpowercablesforS0channels1/42/3.

20.PerformpayloadoperationstosupportSTP

H2

(ANDE,

MEPSI,

RAFT).

21.Performthefollowingtoallowreturnof

onorbithardware:

Treadmillgyroremovaland

replacement

Charcoalbedassembly

Respiratorysupportpackcheckout

22.Transfer

nitrogen

from

the

shuttle

to

the

ISS

QuestAirlockhighpressuretanks.

23.PerformU.S.andRussianpayloadresearch

operationtasks.

24.PerformanadditionalfourhoursofISS

crewhandover(16hourstotal).

25.PerformimagerysurveyoftheISSexterior

fromshuttleafterundocking.

26.Performpayloadoperationstosupport

MauiAnalysisofUpperAtmospheric

Injections(MAUI)andRamBurn

Observations(RAMBO)

27.ReboostISS(altitudeTBDbasedon

availableshuttlepropellant).

28.Thefollowingtasksfitwithintheexisting

spacewalktimelines;however,theymaybe

deferredif

the

spacewalk

is

behind

schedule. TheEVAwillnotbeextendedto

completethesetasks.

Installstationrobotarmforcemoment

sensor(FMS)insulation


19/135


Installthestarboardandportfluid

quickdisconnectbagsontheQuest

Airlock

InstallS0/UnityNodeprimarypower

cable(S0sideonly)andreconfigureZ1

patchpanelsandRussianpowerto

operatefromprimarypower(i.e.,

MBSU)

29.Performprogramapprovedspacewalkget

aheadtasks. Thefollowinggetaheadtasks

donotfitintheexistingspacewalk

timelines;however,theteamwillbetrained

andready

to

perform

any

of

these

tasks

shouldtheopportunityarise.

ConnectP5toP4umbilicals(6)

OpenP5capturelatchassembly(CLA)

andpartiallyclose(~1turn)

RemoveP5toP6trussattachment

systemlaunchlocks

Installthepumpmodulejumperbagon

theQuestAirlock

Installtheventtoolextensionbagon

Quest

30.Perform:

DevelopmentTestObjective(DTO)257

StructuralDynamicsModelValidation

FlightTestandSupplementary

ObjectivesDocument(InternalWireless

InstrumentationSystem,

known

as

IWIS,isrequired)

PerformISSStructuralLifeValidation

andExtensionfortheshuttleundocking

(IWISrequired).


20/135


21/135

December 2006 LAUNCH & LANDING 15

LAUNCH AND LANDING

LAUNCH

AswithallpreviousSpaceShuttlelaunches,

DiscoveryonSTS116willhaveseveralmodes

availablethatcouldbeusedtoaborttheascent

ifneededduetoenginefailuresorother

systemsproblems. Shuttlelaunchabort

philosophyaimstowardsaferecoveryofthe

flightcrewandintactrecoveryoftheorbiter

anditspayload. Abortmodesinclude:

ABORT-TO-ORBIT (ATO)

Partiallossofmainenginethrustlateenoughto

permitreachingaminimal105by85nautical

mileorbitwithorbitalmaneuveringsystem

engines.

TRANSATLANTIC ABORT LANDING

(TAL)

Lossofoneormoremainenginesmidway

throughpoweredflightwouldforcealandingateitherZaragoza,Spain;Moron,Spain;or

Istres,France. Forlaunchtoproceed,weather

conditionsmustbeacceptableatoneofthese

TALsites.

RETURN-TO-LAUNCH-SITE (RTLS)

Earlyshutdownofoneormoreengines,and

withoutenoughenergytoreachZaragoza,

wouldresultinapitcharoundandthrustback

towardKSCuntilwithinglidingdistanceofthe

ShuttleLandingFacility. Forlaunchto

proceed,weatherconditionsmustbeforecastto

beacceptableforapossibleRTLSlandingat

KSCabout20minutesafterliftoff.

ABORT ONCE AROUND (AOA)

AnAOAisselectedifthevehiclecannot

achieveaviableorbitorwillnothaveenough

propellanttoperformadeorbitburn,buthas

enoughenergytocircletheEarthonceandland

about9i0minutesafterliftoff.

LANDING

TheprimarylandingsiteforDiscoveryon

STS116istheKennedySpaceCentersShuttleLandingFacility. Alternatelandingsitesthat

couldbeusedifneededduetoweather

conditionsorsystemsfailuresareatEdwards

AirForceBase,California,andWhiteSands

SpaceHarbor,NewMexico.


22/135


23/135

December 2006 MISSION PROFILE 16

MISSION PROFILE

CREWCommander: MarkPolansky

Pilot: BillOefelein

MissionSpecialist1: NicholasPatrickMissionSpecialist2: BobCurbeamMissionSpecialist3: ChristerFuglesangMissionSpecialist4: JoanHigginbothamMissionSpecialist5: SuniWilliams/

ThomasReiterLAUNCHOrbiter: Discovery(OV103)LaunchSite: KennedySpaceCenter

LaunchPad39B

LaunchDate: NoEarlierThanDecember7,2006

LaunchTime: 9:36p.m.EST(PreferredInPlanelaunchtimefor

12/7)

LaunchWindow: 5MinutesAltitude: 123NauticalMiles(142

Miles)OrbitalInsertion;

190NM(218Miles)

Rendezvous

Inclination: 51.6DegreesDuration: 10Days18Hours40

Minutes

VEHICLE DATA

ShuttleLiftoffWeight: 4,521,350pounds

Orbiter/PayloadLiftoffWeight: 265,466pounds

Orbiter/PayloadLandingWeight: 225,350pounds

SoftwareVersion: OI30

Space Shuttle Main Engines:

SSME1: 2050SSME2: 2054SSME3: 2058ExternalTank: ET123SRBSet: BI128RSRMSet: 95SHUTTLE ABORTS

Abort Landing Sites

RTLS: KennedySpaceCenterShuttleLandingFacility

TAL: PrimaryZaragoza,Spain.AlternatesMoronandIstres,France

AOA: PrimaryKennedySpaceCenterShuttleLandingFacility;Alternate

WhiteSandsSpaceHarbor

Landing

LandingDate: NoEarlierThanDecember18,2006LandingTime: 4:16p.m.ESTPrimarylandingSite: KennedySpaceCenter

ShuttleLandingFacility

PAYLOADS

lntegratedTrussSegment(ITS)P5,SPACEHAB

SingleModule


24/135


25/135

December 2006 CREW 17

STS-116 DISCOVERY CREW

TheSTS116patchdesignsignifiesthe

continuingassemblyoftheInternationalSpace

Station. Theprimarymissionobjectiveisto

deliverandinstalltheP5trusselement. TheP5

installationwillbeconductedduringthefirstof

threeplannedspacewalks,andwillinvolveuse

ofboththeshuttleandstationroboticarms.

Theremainderofthemissionwillincludea

majorreconfigurationandactivationofthe

stationselectricalandthermalcontrolsystems,

aswellasdeliveryofZvezdaServiceModule

debrispanels,whichwillincreaseprotection

frompotentialimpactsofmicrometeoritesand

orbitaldebris. Inaddition,asingleexpedition

crewmemberwilllaunchonSTS116toremain

onboardthestation,replacinganexpedition

crewmemberThomasReiter,whowillfly

homewiththeshuttlecrew. Thecrewpatch

depictsthespaceshuttlerisingabovetheEarth

andthestation. TheUnitedStatesandSwedish

flagstrailtheorbiter,depictingthe

internationalcompositionoftheSTS116crew.

ThesevenstarsoftheconstellationUrsaMajor

areusedtoprovidedirectiontotheNorthStar,

whichissuperimposedovertheinstallation

locationoftheP5trussonthestation.


26/135


Thesesevenastronautstakeabreakfrom

trainingtoposefortheSTS116crewportrait.

ScheduledtolaunchaboardtheSpaceShuttle

Discoveryare,frontrow(fromtheleft),

astronautsWilliamA.Oefelein,pilot;JoanE.

Higginbotham,missionspecialist;andMarkL.

Polansky,commander. Onthebackrow(from

theleft)areastronautsRobertL.Curbeam,

NicholasJ.M.Patrick,SunitaL.Williamsand

theEuropeanSpaceAgencysChrister

Fuglesang,allmissionspecialists. Williamswill

joinExpedition14inprogresstoserveasa

flightengineeraboardtheInternationalSpace

Station. Thecrewmembersareattiredin

trainingversionsoftheirshuttlelaunchand

entrysuits.

Shortbiographicalsketchesofthecrewfollow

withdetailedbackgroundavailableat:

http://www.jsc.nasa.gov/Bios/


27/135


CommanderMarkPolanskyAformerAirForcetestpilot,MarkPolansky

willleadthecrewofSTS116onthe20thshuttle

missionto

the

space

station.

Polansky

served

asthepilotonSTS98in2001. Makinghis

secondspaceflight,hehasloggedmorethan

309hoursinspace. Hehasoverall

responsibilityfortheonorbitexecutionofthe

mission,orbitersystemsoperationsandflight

operationsincludinglandingtheorbiter. In

addition,Polanskywillflytheshuttleina

procedurecalledtherendezvouspitch

maneuverwhileDiscoveryis600feetbelowthe

stationbefore

docking

to

enable

the

station

crewtophotographtheorbitersheatshield.

HewillthendockDiscoverytothestation.

Polanskywillalsobeheavilyinvolvedin

shuttleroboticarmoperationsforinspecting

theorbitersheatshield,andtransferringcargo

tothestationduringthedockedphaseofthe

mission.


28/135


PilotBillOefeleinWilliamOefelein(Ohfeline),whohaslogged

morethan3,000hoursflyingmorethan50

aircraft,willmakehisfirstjourneyintospaceas

thepilot

for

the

STS

116

mission.

Selected

by

NASAinJune1998,Oefeleinreportedtothe

JohnsonSpaceCenterinHoustoninAugust

1998. HehasservedintheAstronautOffice

AdvancedVehiclesBranchandCAPCOM

(capsulecommunicator)Branch. Hewillbe

responsiblefororbitersystemsoperationsand

assistingPolanskyintherendezvousand

dockingtotheInternationalSpaceStation. He

willalsoserveasthechoreographerinside

Discoveryandthestationforthemissions

threeplanned

spacewalks,

helping

to

suit

up

anddirectthespacewalkersthroughtheir

activities. OefeleinwillundockDiscoveryfrom

thestationattheendofthedockedphaseofthe

missionandconductaflyaroundtoenablehis

crewmatestophotographthestations

configurationandassessitscondition.


29/135


MissionSpecialistNicholasPatrickAmemberofthe1998astronautclassanda

formerflightinstructor,NicholasPatrickis

assignedtoSTS116asmissionspecialist1

(MS1). HereportedtoNASAsJohnsonSpace

Centerin

Houston

for

astronaut

training

in

August1998. Hisinitialtrainingincluded

scientificandtechnicalbriefings,intensive

instructioninshuttleandInternationalSpace

Stationsystems,physiological,survivaland

classroomtraininginpreparationforT38

flight. Makinghisfirstspaceflight,Patrickwill

betheprimaryoperatoroftheshuttlesrobotic

arm,usingittounberththeorbiterboomsensor

systemtosurveyDiscoverysthermal

protectionsystemonflightday2andto

grapplethestationsP5trussforahandoffto

thestation

robotic

arm

operated

by

Mission

SpecialistJoanHigginbothamonflightday3.

Hewillberesponsiblefortheshuttlesvideo

andcomputernetworks,andwillassistwith

thetransferofcargobetweentheshuttleand

thestation. Hewillbeseatedontheflightdeck

forlaunchandonthemiddeckforlanding.


30/135


MissionSpecialistBobCurbeamAveteranoftwospaceshuttleflights,Mission

Specialist2(MS2)BobCurbeamconducted

threespacewalksbeforebeingassignedto

STS116. HeflewonSTS85inAugust1997and

onSTS98inFebruary2001. Heloggedmore

than19hoursoverthecourseofthree

spacewalksduringSTS98,completingdelivery

oftheU.S.laboratoryDestinytothespace

station. Hewillconductthreespacewalks

duringSTS116. Curbeam,asEV1,will

conductthefirsttwospacewalksofthemission

withChristerFuglesangonflightdays4and6.

Duringthefirstspacewalk,thetwowillinstall

theP5trussandattachallmechanicaland

electricalinterfacesbetweenitandtheexisting

stationtruss. TheyalsowillchangeoutaTV

cameraonthestarboard1(S1)truss. During

thesecondspacewalk,theduowillunplug

stationpowerchannels2and3fromtheP6

powertrussandconnectthemtothemaintruss

(permanent)powersystem. Theyalsowill

movetheCrewandEquipmentTranslationAid

cartsinpreparationthenextpower

reconfigurationtooccurduringthethird

spacewalkofthemission. Curbeamwill

conductthethirdplannedspacewalkofthe

missiononflightday8withSunitaWilliams.

Theywillunplugstationpowerchannels2and

3fromtheP6powertrussandconnectthemto

themaintruss(permanent)powersystem.

TheyalsowilltransferServiceModuledebris

panelsfromtheshuttletothestation. Curbeam

willbeseatedontheflightdeckforlaunchand

landing,operatingastheflightengineerto

assistCommanderMarkPolanskyandPilotBill

Oefelein.


31/135


MissionSpecialistChristerFuglesangMakinghisfirstspaceflight,EuropeanSpace

AgencyastronautChristerFuglesang

(Fyugelsang)joinsthecrewofSTS116asa

missionspecialist. Fuglesangisamemberof

ESAsEuropeanAstronautCorps,whosehome

baseistheEuropeanAstronautCentrein

Cologne,Germany. Heenteredthemission

specialistclassatNASAsJohnsonSpaceCenter

inAugust1996andqualifiedforflight

assignmentasamissionspecialistinApril1998.

MissionSpecialist3(MS3)Fuglesang,asEV2,

willconductthefirsttwoplannedspacewalks

ofthemissionwithCurbeamonflightdays4

and6. Fuglesangistheleadfordeployingthree

smallsatellitesfromthepayloadbaytoward

theendofthemission. Fuglesangwillsetup

therecumbentseatreturningExpedition14

crewmemberThomasReiterwilluseforthe

triphomeaboardtheshuttle. Fuglesangwillbe

seatedonthemiddeckforlaunchandlanding.


32/135


MissionSpecialistJoanHigginbothamMissionSpecialist4(MS4)JoanHigginbotham

willbemakingherfirstflightintospaceaboard

Discovery. Toassistwiththeconstructionof

thespacestation,Higginbothamsprimarytask

onSTS116willbetooperatethestations

roboticarm. Amongotherrobotictasks,she

willusethestationarmtoinstalltheP5truss

ontotheP4trussattachmentonflightday4.

Duringtherendezvous,dockingand

undocking,shewillmanagetherendezvous

navigationtoolsusedtoguidetheshuttles

trajectoryrelativetothestation. Shewillserve

astheleadcargotransferofficer,overseeingthe

transferofsuppliesandequipmentbetweenthe

shuttleandthestation. Shewilloversee

payloadbaydoorclosingoperations. Shewill

beseatedonthemiddeckforlaunchandthe

flightdeckforlanding.


33/135


MissionSpecialist/Expedition14FlightEngineerSuniWilliamsMakingherfirstspaceflight,MissionSpecialist

5(MS5)Sunita(Sooneetah)Williamswilljoin

Expedition14inprogressandserveasaflight

engineeraftertravelingtothestationonspace

shuttlemissionSTS116. Williams,whogoesby

thenameSuni(sunny),willjoinExpedition14

onflightday3,whenherSoyuzseatlineris

transferredfromtheshuttle3. Thetransferwill

markthebeginningofherscheduledsixmonth

stayaboardthestation. Williams,asEV3,will

joinBobCurbeamforthethirdplanned

spacewalkofthemissiononflightday8. She

willbeseatedonthemiddeckforlaunch.


34/135


ThomasReiterInternationalSpaceStationFlightEngineer

ThomasReiter(Toemahs Ryeturr)(FE2)of

theEuropeanSpaceAgency(ESA)flewtothe

spacestationaboardDiscoveryinJuly2006and

becameamemberoftheExpedition13crew.

HewillreturntoEarthaboardDiscoverywith

theSTS116crew. InSeptember2006,Expedition13CommanderPavelVinogradov

andFlightEngineerandNASAScienceOfficer

JeffWilliamsleftthestationaboardaRussian

Soyuzspacecraft. Reiterwasjoinedby

Expedition14CommanderMikeLopezAlegria

andFlightEngineerMikhailTyurin. Reiteris

thefirstcrewmembertoserveontwo

expeditions. Hespent179daysinspacein

19951996foramissiontotheRussianMir

spacestationduringwhichheconductedtwo

spacewalksandabout40Europeanscientific

experiments. ReiteristhefirstESAastronautto

liveaboardtheInternationalSpaceStationfora

longtermmission. Reiterworkedonthestationaspartofanagreementbetweenthe

RussianFederalSpaceAgencyandESA. Reiter

willbeonthemiddeckforlandingina

speciallydesignedrecumbentseattofacilitate

hisadaptationtoagravityenvironmentforthe

firsttimeinsixmonths.


35/135

December 2006 MISSION PERSONNEL 27

MISSION PERSONNEL

KEY CONSOLE POSITIONS FOR STS-116

Flt.Director CAPCOM PAOAscent SteveStich KenHam

ChrisFerguson(Wx)KellyHumphries

Orbit1(Lead) TonyCeccacci KevinFord KyleHerring(Lead)Orbit2 MattAbbott MeganMcArthur NicoleCloutierPlanning RickLaBrode ShannonLucid JohnIraPettyEntry NormKnight KenHam

ChrisFerguson(Wx)KyleHerring

ShuttleTeam4 RichardJones N/A N/AISSOrbit1 DerekHassmann TerryVirts N/AISSOrbit2(Lead) JohnCurry SteveRobinson N/AISSOrbit3 JoelMontalbano HalGetzelman N/AStationTeam4 DanaWeigel N/A N/AMissionControl,Korolev,Russia

KwatsiAlibaruho N/A N/A

JSCPAORepresentativeatKSCforLaunchKylieClemKSCLaunchCommentatorBruceBuckinghamKSCLaunchDirectorMikeLeinbachNASALaunchTestDirectorJeffSpaulding


36/135


37/135

December 2006 RENDEZVOUS & DOCKING 28

RENDEZVOUS AND DOCKING

Discoverysfinal

approach

to

the

International

SpaceStationduringtheSTS116rendezvous

anddockingprocesswillincludethe

nowstandardbackflippirouettemaneuverto

allowstationcrewmemberstotakedigital

imagesoftheshuttlesheatshield.

WithshuttleCommanderMarkPolanskyatthe

controls,theshuttlewillperformthecircular

pitcharoundfromadistanceofabout600feet

belowthestation. The9minuteflipoffers

Expedition14CommanderMikeLopezAlegriaandFlightEngineerMikhailTyurintimeto

documentthroughdigitalstillphotographythe

requiredimageryofDiscoverysthermal

protectionsystem.

Thephotosthenwillbetransmittedtoimagery

expertsintheMissionEvaluationRoomat

MissionControl,Houston,viathestations

Kubandcommunicationssystem.

Thephotographywillbeperformedoutof

windows6and8intheZvezdaServiceModule

withKodakDCS760digitalcamerasand

400mmand800mmlenses. TheRendezvous

PitchManeuver(RPM)isoneofseveral

inspectionproceduresdesignedtoverifythe

integrityoftheshuttlesprotectivetilesand

reinforcedcarboncarbonwingleadingedge

panels.

Thesequence

of

events

that

brings

Atlantis

to

itsdockingwiththestationbeginswiththe

preciselytimedlaunchoftheshuttle,placing

theorbiteronthecorrecttrajectoryandcourse

Thesequenceofeventsthatculminatewith

Discoverysdockingtothestationactually

beginswiththepreciselytimedlaunchthat

bottomside_800mm.cnv

NOTE

1. indicates

critical focuspoint.

2. Sequence is~16 shots;repeatsequence, astime allows.


NOTE

1. indicates

critical focuspoint.


placestheorbiteroncourseforitstwoday

chasetoarriveatthestation. The43hour

rendezvousincludesperiodicthrusterfirings

thatultimatelywillplaceDiscoveryabout9

statutemilesbehindthestation,thestarting

pointforfinalapproach.

About2.5hoursbeforethescheduleddocking

timeon

flight

day

3,

Discovery

will

reach

a

pointabout50,000feetbehindthestation.

Discoverysjetswillbefiredinwhatiscalled

theTerminalInitiation(TI)burntobeginthe

finalphaseoftherendezvous. Discoverywill

closethefinalmilestothestationduringthe

nextorbit.


38/135


AsDiscoverymovesclosertothestation,the

shuttlesrendezvousradarsystemand

trajectorycontrolsensor(TCS)willbegin

trackingthe

complex,

and

providing

range

and

closingrateinformationtothecrew. During

thefinalapproach,Discoverywillexecutefour

smallmidcoursecorrectionswithitssteering

jetstopositiontheshuttleabout1,000feet

directlybelowthestation. Fromthispoint,

Polanskywilltakeoverthemanualflyingofthe

shuttleupanimaginarylinedrawnbetween

thestationandtheEarthknownastheRBar

orradialvector.

HewillslowDiscoverysapproachatabout600feetand,ifrequired,waitforproperlighting

conditionstooptimizeinspectionimagery

gatheringaswellascrewvisibilityforthefinal

rendezvoustodocking.

Rendezvous Approach Profile

Space Shuttle Rendezvous ManeuversOMS-1 (Orbit insertion)-Rarely used ascentburn.OMS-2 (Orbit insertion)-Typically used tocircularize the initial orbit following ascent,completing orbital insertion. For ground-uprendezvous flights, also considered arendezvous phasing burn.NC (Rendezvous phasing)-Performed to hit arange relative to the target at a future time.NH (Rendezvous height adjust)-Performedto hit a delta-height relative to the target at afuture time.

NPC (Rendezvous plane change)- Performed

to remove planar errors relative to the target ata future time.

NCC (Rendezvous corrective combination)-First on-board targeted burn in the rendezvoussequence. Using star tracker data, it isperformed to remove phasing and height errorsrelative to the target at Ti.Ti (Rendezvous terminal intercept)- Secondon-board targeted burn in the rendezvoussequence. Using primarily rendezvous radardata, it places the orbiter on a trajectory tointercept thetarget in one orbit.MC-1, MC-2, MC-3, MC-4 (Rendezvousmidcourse burns)-These on-board targetedburns use star tracker and rendezvous radardata to correct the post-Ti trajectory inpreparation for the final, manual proximityoperations phase.


39/135



NOTE

1. indicatescritical focuspoint.


OnverbalconfirmationbyPilotBillOefeleinto

alertthestationcrew,Polanskywillcommand

Discoverytobeginanoseforward,three

quartersofadegreepersecondrotationalback

flip. AtRPMstart,thestationcrewwillbegina

seriesofpreciselytimedphotographyfor

inspection. Thesequenceofmapping

optimizesthelightingconditions.

Boththe400mmand800mmdigitalcamera

lenseswillbeusedtocaptureimageryoftherequiredsurfacesoftheorbiter. The400mm

lensprovidesupto3 inchresolutionandthe

800mmlenscanprovideupto1inch

resolutionanddetectanygapfillerprotrusions

greaterthan1/4inch. Theimageryincludesthe

uppersurfacesoftheshuttleaswellas

Discoverysunderside,nosecap,landinggear

doorsealsandtheelevoncoveareaswith

1inchanalyticalresolution. Thephotography

includesdetection

of

any

gap

filler

protrusions

whentheorbiterisat145and230degreeangles

duringtheflip. Themaneuverandlighting

typicallyoffersenoughtimefortwosetsof

pictures.

WhenDiscoverycompletesitsrotation,itwill

returntoanorientationwithitspayloadbay

facingthestation.

PolanskythenwillmoveDiscoverytoa

positionabout400feetinfrontofthestation

alongtheVBar,orthevelocityvectorthe

directionof

travel

for

both

spacecraft.

Oefelein

willprovidenavigationinformationto

Polanskyastheshuttleinchestowardthe

dockingportattheforwardendofthestations

DestinyLaboratory.

OefeleinwilljoinMissionSpecialistsNicholas

PatrickandJoanHigginbothaminplayingkey

rolesintherendezvous. Theywilloperate

laptopcomputersprocessingthenavigational

data,thelaserrangesystemsandDiscoverys

dockingmechanism.

UsingacameraviewfromcenterofDiscoverys

dockingmechanismasakeyalignmentaid,

Polanskywillpreciselymatchthedockingports

ofthetwospacecraftandflytoapoint30feet

fromthestationbeforepausingtoverifythe

alignment.

ForDiscoverysdocking,Polanskywillclose

thefinal30feetatarelativespeedofabout

onetenthofafootpersecond(whileboth

spacecraftaretraveling17,500mph),andkeep

thedockingmechanismsalignedwithina

toleranceofthreeinches.


40/135


Atcontact,preliminarylatcheswill

automaticallyattachthetwospacecraft.

ImmediatelyafterDiscoverydocks,the

shuttlessteering

jets

will

be

deactivated

to

eliminateforcesactingatthedockinginterface.

Shockabsorberlikespringsinthedocking

mechanismwilldampenanyrelativemotion

betweentheshuttleandthestation.

Oncemotionbetweenthetwospacecrafthas

beenstopped,MissionSpecialistsBobCurbeam

andChristerFuglesangwillsecurethedocking

mechanism,sendingcommandsforDiscoverys

dockingringtoretractandtocloseafinalsetof

latchesbetweenthetwovehicles.

UNDOCKING, SEPARATION AND

DEPARTURE

WithadditionalinspectionsofDiscoverysheat

shieldexpectedtobescheduledafter

undocking,theorbiterwilldepartthestation

withtheshuttleroboticarmandOrbiterBoom

SensorSystem(OBBS)intheirstowed

configuration.

The

OBSS

will

be

unstowed

to

accommodatetheinspections.

OnceDiscoveryisreadytoundock,Fuglesang

willsendacommandtoreleasethedocking

mechanism. Atinitialseparationofthe

spacecraft,springsinthedockingmechanism

willpushtheshuttleawayfromthestation.

Discoveryssteeringjetswillbeshutoffto

avoidanyinadvertentfiringsduringtheinitial

separation.

OnceDiscoveryisabouttwofeetfromthe

station,withthedockingdevicesclearofone

another,Oefeleinwillactivatethesteeringjets

tovery

slowly

move

away.

From

the

aft

flight

deck,OefeleinmanuallywillcontrolDiscoverywithinatightcorridorasitseparatesfromthe

stationessentiallythereverseofthetask

performedbyPolanskyduringrendezvous.

Discoverywillcontinueawaytoadistanceof

about450feet,whereOefeleinwillguidethe

shuttleinacircularflyaroundofthestation.

OnceDiscoverycompletes1.5revolutionsof

thecomplex,OefeleinwillfireDiscoverysjets

todepartthestationsvicinityforthefinaltime.

Discoverywillseparatetoadistanceofabout

40nauticalmilesandremaintheretoprotectfor

areturntothecomplexintheunlikelyevent

thelateinspectionrevealsanydamagetothe

shuttlesthermalheatshield.


41/135

December 2006 ELECTRIC POWER SYSTEM 32

INTERNATIONAL SPACE STATION

ELECTRIC POWER SYSTEM (EPS)

TheInternationalSpaceStation(ISS)electrical

powersystemconsistsofpowergeneration,

energystorage,powermanagement,and

distribution(PMAD)equipment. Electricityis

generatedinasystemofsolararrays. Besides

thesolararraysontheRussianelement,the

stationcurrentlyhastwophotovoltaicmodules,

atermthatreferstoasetofsolararrays,

batteriesandtheassociatedelectronics,on

orbit,withtwomorescheduledfordelivery.

TheElectricPowerSystem(EPS)providesall

userloadsandhousekeepingelectricalpower

andiscapableofexpansionasthestationis

assembledandgrows. Eightindependent

powerchannelsforhighoverallreliability

supplytheelectricpower.

Aphotovoltaic(PV)electricpowergeneration

subsystemwasselectedforthespacestation. A

PVsystemusessolararraysforpower

generationandchemicalenergystorage

(Nickelhydrogen)batteriestostoreexcesssolar

arrayenergyduringperiodsofsunlightand

providepowerduringperiodswhenthestation

isinEarthsshadow(eclipse). Thestation

orbitstheearthevery90minutesandforabout

35minutes,thestationmustrunonbatteries

whilethestationisineclipse.

Flexible,deployable

solar

array

wings

that

are

coveredwithsolarcellsprovidepowerforthe

ISS. EachPVmodulecontainstwowings,and

eachwingconsistsoftwoblanketassemblies.

Thesolararraywingsaretightlyfoldedinsidea

blanketforlaunch. Theyaredeployedinorbit

andsupportedbyanextendablemast.

Analogybetween

municipal

utility

andthestationsEPS

Nominalelectricaloutputofeachpower

channelisabout11kilowatts(kW),or20.9kW

perPVmodule. FourPVmoduleswillsupply

approximately83.6kW.

TheprimarypurposeoftheEnergyStorage

Subsystem(ESS)istoprovideelectricalpower

duringperiodswhenpowerfromthesolar

arraysisnotenoughtosupportchannelloads.

TheESSstoresenergyduringperiodswhen

solararrayscangeneratemorepowerthan

necessarytosupportloads. Thesystemconsists

ofthreenickelhydrogen(NiH2)batteriesper

powerchannelandeachbatteryconsistsoftwo

batteryOrbitalReplacementUnits(ORUs).

Eachbatteryalsohasacharge/dischargeunit

(BCDU). TheNi/H2batterydesignwaschosen

becauseofitshighenergydensitylightweight

andprovenheritageinspaceapplicationssincethelate1970stoearly1980s.

TheentireEPSmaybedividedintotwopower

subsystems. Theprimarypowersubsystem

operatesatavoltagerangeof137to173volts

directcurrent(Vdc)andconsistsofpower

generation,storageandprimarypower


42/135


distribution. Thesecondarypowersubsystem

operatesatavoltagerangeof123to126Vdc

andisusedtosupplypowertouserloads.

DirectCurrent

to

Direct

Current

Converter

Units(DDCUs)areusedtoconvertprimary

powertosecondarypower.

TheU.S.powersystemisalsointegratedwith

Russianpowersources,sothatpowerfromthe

Americanpowerbuscanbetransferredtothe

Russianpowerbusandviceversa. TheRussian

powersystemoperatesatanominalvoltageof

28Vdc. AmericantoRussianConverterUnits

(ARCUs)andRussiantoAmericanConverter

Units(RACUs)areusedtoconvertpowerfromtheAmericansecondarypowerbustothe

Russianpowerbusandviceversa.

SOLAR POWER

Themostpowerfulsolararraysevertoorbit

Earthcapturesolarenergytoconvertitinto

electricpowerfortheISS.

Eightsolararraywingssupplypoweratan

unprecedentedvoltagelevelof137to173Vdcthatisconvertedtoanominal124Vdcto

operateequipmentontheISS. TheSpace

Shuttleandmostotherspacecraftoperateat

nominal28Vdc,asdoestheRussianISS

segment.

ThehighervoltagemeetsthehigheroverallISS

powerrequirementswhilepermittinguseof

lighterweightpowerlines. Thehighervoltage

reducesohmic

power

losses

through

the

wires.

Someeightmilesofwiredistributepower

throughoutthestation.

EachPVmodulecontainstwosolararray

wings. Anindividualwingis110feetlongby

38feetwide. Eachwingconsistsoftwoarray

blanketsthatarecoveredwithsolarcells. The

blanketscanbeextendedorretractedbya

telescopicmastwhichislocatedbetweenthe

twoblankets. Eachsolararraywingis

connectedtotheISSs310footlongtrussandextendoutwardatrightanglestoit(P4andP6

arecurrentlyonorbit). Aseriesof400solar

cells,calledastring,generateselectricityathigh

primaryvoltagelevelswhile82stringsare

connectedinparalleltogenerateadequate

powertomeetthepowerrequirementforeach

powerchannel. Thereareatotalof32,800cells

perpowerchannelor65,600solarcellsoneach

PVmodule.

Asolarcellassemblyisaboutthreeinches

square. Thecellsaremadeofsiliconandhavea

nominal14.5percentefficiencyforsunlightto

electricityconversion. Cellsareweldedontoa

flexibleprintedcircuitlaminatethatconnects

cellselectrically. Thesunfacingsurfaceofthe

cellisprotectedbyathincoverglass. Each

groupofeightcells,connectedinseries,is

protectedbyabypassdiodetominimize

performanceimpactoffracturedoropencells

onastring. Solararraysaredesignedforan

operatinglifeof15years.

Twomutuallyperpendicularaxesofrotation

areusedtopointsolararraystowardstheSun.

EachsolararraywingisconnectedtooneBeta

GimbalAssembly(BGA),locatedoneachPV

module,thatisusedtorotatethatsolararray


43/135


wing. Anotherrotaryjoint,calledSolarAlpha

RotaryJoint(SARJ),ismountedonthetruss

androtatesthefoursolararraywingstogether.

Whenthe

station

is

complete,

there

will

be

eightBGAsandtwoSARJs. Theserotaryjoints

arecomputercontrolledandensurefullsun

trackingcapabilityastheISSgoesaroundthe

earthunderawiderangeoforbitsandISS

orientations.

ELECTRIC POWER SYSTEM OVERVIEW

Likeacityscentralpowerplant,thePV

modulesgenerateprimarypoweratvoltage

levelstoohighforconsumeruse,rangingfrom137to173Vdc. Theprimarypowerisroutedto

BCDUsforchargingbatteriesandtoswitching

unitsthatrouteittolocaldistributionnetworks.

TheDCDCConverterUnits,DDCUs,

stepdown theprimarypowertoamore

tightlyregulatedsecondarypowervoltage,

nominally124.5Vdcthatisregulatedplusor

minus1.5Vdc,anddistributeittoISSloads.

OnMainStreet,USA,theuserswouldbeshops

andhomes. OntheISS,theyarelaboratories,

livingquartersandothermodules.

EventhoughtheStationspendsaboutonethird

ofeveryorbitinEarthsshadow,theelectrical

powersystemcontinuouslyprovidesusable

power(about84kWatassemblycomplete)to

ISSsystemsandusers.WhentheISSisin

eclipse,thebatteriesthatstoredenergyfrom

solararraysduringthesunlitportionofthe

orbitsupply

power.

Thepowersystemiscooledbyathermal

systemthroughwhichexcessheatisremoved

byliquidammoniacoolantintubesthat

ultimatelyloop

through

radiator

panels

that

radiatetheheattospace.

RussiassegmentoftheISSprovidesitsown

powersources,supplying28voltdctothe

Russianmodules. Powerissharedbetweenthe

twosegmentswhenrequiredtosupport

assemblyandoperationsforallISSpartners.

RussiantoAmericanConverterUnits(RACUs)

andAmericantoRussianConverterUnits

(ARCUs)stepupandstepdownconverters,

respectively,dealwiththedifferencebetweenU.S.andRussianbusvoltagelevels. AsISS

assemblycontinues,Russiansolararrays

(a72footpaironControlModuleZaryaanda

97footpairontheRussianServiceModule)

willreceivemoreshadow,whichwilldiminish

theirpowergenerationcapability.

TheoveralldesignandarchitectureoftheISS

EPSwasmanagedbyNASAsGlennResearch

Center

in

the

early

1990s.

Boeings

Rocketdyne

PropulsionandPowerdivision(nowPratt&

WhitneyRPP)builtmostofthehardwarefor

theelectricalpowersystem. LockheedMartin

builtthesolararraysandtheSolarAlpha

RotaryJointforRocketdyne. Boeing,along

withPratt&WhitneyRPP,asasubcontractor,

continuestoprovideEPSsustaining

engineeringtoNASA.MostEPScomponents

andcargoassembliesundergofinalacceptance

testingatKennedySpaceCenterbeforeflightto

ISS.


44/135


ElectricalPowerDistributionOverview

EPS BLOCK DIAGRAM OVERVIEW

Thisblockdiagramgivesanoverviewofhow

thestationselectricalsystemfunctionswhen

assembly

is

complete.

The

Solar

Array

Wing

(SAW)cangeneratepoweratawiderangeof

voltage,however,theSequentialShuntUnits

(SSU),locatedclosetotheSAWinthe

IntegratedEquipmentAssembly(IEA),regulate

thevoltagethatcomesoutofthesolararraysat

anestablishedsetpointofabout160Vdc.When

asolararraycanproducesufficientpower,then

thesurpluspowerisroutedtotheBattery

Charge/DischargeUnits(BCDU),whichcharge

thebatteries.Whenasolararraycannot

producesufficientpowertosatisfyISSloads

thenthebusvoltagestartstodropbelowthe

SSUsetpoint,andwhenitdropsbelowthe

BCDUsetpoint,thentheBCDUsstartto

dischargebatteriestosupportISSloads. The

primarybusvoltagevariesbetweentheSSU

andBCDUvoltagesetpointsplusasmall

voltageregulationband.

TheprimarypowerisprovidedtotheMainBus

SwitchingUnits(MBSU)forsubsequent

distributiontoISSelectricalloads. FourMBSUs

arelocatedontheS0trussthatisfedbyeight

independentpower

channels

and

the

MBSU

outputssupplyallISSloads. Undernormal

operations,eachpowerchannelsuppliespower

toaspecificsetofloads.However,ifthat

channelfails,theMBSUenablesfeedingpower

tothoseloadsfromanotherchannel. This

greatlyenhancesthefailuretoleranceofthe

EPS.

AllEPSoperationsarecomputercontrolledand

controlscanbeexercisedbytheonorbitcrew

orbyoperatorsonground. Operatorsonthegroundtofreeupcrewtimeformoreimportant

onorbitoperationsperformmostofthese

functions. Allcontrolsetpointsarestoredon

onorbitcomputersandcanbechangedwhen

needed.


45/135


TheMBSUsroutepowertotheDCtoDC

ConverterUnits(DDCUs). TheDDCUsconvert

primarypowertosecondarypowerat123to

126Vdc.

Several

DDCUs

are

located

inside

pressurizedcompartments,suchasUSLab,

whileseveralarelocatedexternallyontrusses.

DDCUssupplyregulatedsecondarypowerto

RemotePowerControllerModules(RPCMs).

RPCMsareboxeswithmultipleswitcheswith

severaldifferentloadratingstoroutepowerto

userloads. TheRPCMsprovideremote

switchingofloadsandovercurrentprotection.

AnRPCMcanalsofeedotherRPCMsandcan

feedRussianpowerconverters,outletpanels,

etc. Therewillbethousandsofindividual

switchesinapproximately184RPCMsonthe

stationatassemblycomplete. Thereareabout

119RPCMsonthestationcurrently.

TheEuropeanandJapaneselaboratory

moduleshavetheirowninternalpower

distributionsystem. Thosemoduleswilldraw

powerfromDDCUs,fromNode2. Their

uniquetransformersandpowercontrol

modulesequivalent

to

U.S.

RPCMs

will

handle

power. NASAandBoeinghaveresponsibility

fordistributingpowertothoseelements,but

theindividualinternationalpartnerswillbe

responsibleforpowerwithintheirrespective

elements.

PRIMARY POWER DISTRIBUTION

OVERVIEW

PrimaryPowerDistributionprovidesa

commandableinterfacebetweengeneratedor

storedpowertoloadsthatarelocateddown

stream. Powerdistributionwithinapower

channelisperformedbyaDCSwitchingUnit

(DCSU)andthepowerdistributiontoloadsis

performedbytheMBSU. AtISSassembly

complete,therewillbeeightDCSUsandfour

MBSUsinvolvedinprimarypower

distribution. TheDCSUsandMBSUsusea

networkofhighpowerswitchescalledRemote

BusIsolators(RBIs)todirectthepowerflow.

TheRBIs

do

not

physically

control

the

direction

ofthecurrentflowingthroughthembutthey

doprovideameansofisolatingacurrentpath

intheeventofamalfunctionorifarepairis

neededontheprimarypowersystem. The

RBIsinboththeDCSUandMBSUarefully

commandablebyonboardcomputers.

EachpowerchannelcontainsoneDCSUto

performpowerdistributionontheIntegrated

EquipmentAssembly(IEA). Duringinsolation,

theDCSUroutespowerfromthearraystoanMBSUdistributionbus,aswellastotheBCDUs

forbatterycharging. Duringeclipse,theDCSU

routesbatterypowertothesameMBSU

distributionbustosatisfypowerdemands,and

italsosendsasmallamountofpowerbackto

theSSUtokeeptheSSUfirmwarefunctioning

inpreparationforthenextinsolationcycle. In

additiontoprimarypowerdistribution,the

DCSUhastheadditionalresponsibilitiesof

routingsecondary

power

to

components

on

the

PVmodules(i.e.,theElectronicsControlUnit

andothersupportcomponents). This

secondarypowerisprovidedbytheDDCU

locatedontheIEA. TheDDCUreceives

primarypowerfromtheDCSU,convertsitinto

secondarypower,andsendsittoRemote

PowerControllerModules(RPCMs)for

distribution. ThePVmoduleRPCMsare

housedwithintheDCSU.

TheMBSUsactasthedistributionhubforthe

EPSsystem. ThefourMBSUsonboardtheISS

arealllocatedontheStarboardZero(S0)truss.

EachofMBSUreceivesprimarypowerfrom

twopowerchannelsanddistributesit

downstreamtotheDDCUsandotherusers

includingServiceModule(SM)Americanto

RussianConverterUnits(ARCUs). Inaddition,


46/135


theMBSUscanbeusedtocrosstiepower

channels(i.e.,feedonepowerchannelloads

withadifferentpowerchannelsource)toassist

infailure

recovery

and

assembly

tasks.

TheBGAsandSARJsontheISSalsoplayarole

inprimarypowerdistribution. TheBGA

providesforthetransmissionofprimarypower

fromthesolararraywingstotheIEAandthe

SARJprovidesfortransmissionofprimary

powerfromtheDCSUstotheMBSUs. The

BGAsandSARJsincorporatearollringdesign

toprovideconduitsforpower(anddata),while

allowingacontinuous360rotation.

SECONDARY POWER DISTRIBUTION

Theworkhorseofthesecondarypower

distributionsystemistheRPCM,anOrbital

ReplacementUnit(ORU),whichcontainssolid

stateorelectromechanicalswitches,knownas

RemotePowerControllers(RPCs). RPCscanbe

remotelycommanded,byonboardcomputers,

tocontroltheflowofpowerthroughthe

distributionnetworkandtotheusers. There

aredifferenttypesofRPCMs,containing

varyingnumbersofRPCsandvaryingpower

ratings. Asshownabove,secondarypower

flowsfromaDDCUandisthendistributed

throughanetworkofORUscalledSecondary

PowerDistributionAssemblies(SPDA)or

RemotePowerDistributionAssemblies

(RPDA).Essentially,

SPDAs

and

RPDAs

are

housingsthatcontainoneormoreRPCMs. The

onlydistinctionbetweenSPDAsandRPDAsis

thelocationdownstreamofaDDCU. RPDAs

arealwaysfedfromotherRPCMsinside

SPDAs. NotethatRPCMshaveonlyonepower

input;thus,ifpowerislostatanylevelofthe

SecondaryPowerSystem,alldownstreamuser

loadswillbewithoutpower.

ThereisnoredundancyintheSecondaryPower

System;rather,redundancyisafunctionoftheusersloads. Forexample,acriticaluserload

maybeabletoselectbetweentwoinputpower

sourcesthatusedifferentpowerchannelsand

thusdifferentsecondarypowerpaths.

AswithDDCUs,SPDAsandRPDAsmaybe

locatedinsidepressurizedcompartmentsor

outside. Dependingontheirspecificlocation,

SPDAsorRPDAsmayinterfacewiththeLab

Internal

Thermal

Control

System

(ITCS)

or

use

heatpipestodissipateheat. RPCMsarealso

locatedwithintheDCSUontheIEAsto

providesecondarypowertopowerchannel

components,asrequired.


47/135


REDUNDANCY

Eachofthepowerchannelsispreconfiguredto

supplypower

for

particular

ISS

loads;

however,

toprovideabackupsourceofpowerforcritical

equipment,theassemblycompletedesign

providesforrerouting(i.e.,crosstying)

primarypowerbetweenvariouspower

channels,asnecessary. Atassemblycomplete,

theISSwillhavefourPVmodulescontaining

eightpowerchannelswithfullcrossstrapping

capability. However,itisimportanttonote

thatonlyprimarypowercanbecrossstrapped.

Oncepowerisconvertedintosecondarypower,

powerflowthroughthedistributionnetwork

cannotbererouted.

Asaresult,ifthereisafailurewithinthe

SecondaryPowerSystem,thereisno

redundancy,andtheentiredownstreampath

fromthefailureisunpowered. Instead,user

loadsgenerallydetermineredundancy. There

arethreetypesofuserredundancyschemesas

listedbelow:

Componentsmaybewiredwithmultiple

powerinputsources,providingthe

capabilityofswappingamongthem.

Twoormorecomponentsthatperformthe

samefunctioncanbefedbydifferentpower

sources;thus,theresponsibilitiesofone

componentcanbeassumedbyanother.

Multiplecomponentscanworktogetherto

performafunction;withthelossofasingle

component,operationalcapabilitiesare

degradednotlost.

Setofavailablejumpersthatcanbeusedto

temporarilyregainpowertoaloaduntilthe

secondarysystemcanbefixed.

SYSTEM PROTECTION

TheEPSisdesignedtoprotectequipmentfrom

powersurges

and

overheating

at

several

points

alongthepowerpathfromthesourcetothe

users. Current,voltage,andtemperature

sensorsarelocatedinnearlyalltheEPS

equipment(ORUs)andaremonitoredby

firmwarelocatedonthehardwareoronboard

computers,orboth. Ifavoltage,current,or

temperatureisoutofrange,anappropriate

safingactionwillbeinitiatedeitherbythe

firmwareorbycomputersoftware. Thesafing

actionisdesignedtolimittheamountoftime

thattheboxisexposedtohighpowerorhigh

temperature. Incaseofpowersurges,itisalso

designedtolimittheimpactofthatsurgeon

otherequipmentalongthepowerpath.

Thesystemprotectionfunctionincludesthe

architecturesabilitytodetectthatafault

conditionhasoccurred,confinethefaultto

preventdamagingconnectingcomponents,and

executeanappropriaterecoveryprocessto

restorefunctionality,

if

possible.

This

process

is

usuallyreferredtoasFaultDetection,Isolation,

andRecovery(FDIR). Forexample,upon

detectionofafault,componentscanbeisolated,

therebypreventingpropagationoffaults. In

responsetoovercurrentconditions,the

architectureisdesignedsuchthateach

downstreamcircuitprotectiondeviceissettoa

lowercurrentratingandrespondsmore

quicklythantheprotectiondevicedirectly

upstream. Thisensuresthatelectricalfaultsor

shortsinthesystemdonotpropagatetoward

thepowersource. Anotherfunctionofthe

architecturessystemprotectionshutsdownthe

productionofpowerwhenarrayoutputvoltage

dropsbelowaspecifiedlowerlimitthreshold.

ThispreventsthePVcellsfromcontinuingto

feedadownstreamfault. Insummary,allthe


48/135


variousimplementationsofsystemprotection

worktogethertoisolatefaultsorshortsatthe

lowestlevel. Thisapproachminimizesimpacts

tothe

users

of

the

EPS

and

protects

the

EPS

fromdamagebylowlevelfaults.

KEY EPS COMPONENTS

SOLAR ARRAY WING (SAW)

TheprinciplefunctionoftheSAWistoproduce

electricalpowerfromsolarenergy. TheSAW

contains32,800solarcells,16,400perblanket,

whichcanproduceapproximately31kilowatts

(kW)ofelectricalpoweratBeginningofLife

(BOL),andabout26kWafter15years,attheir

designedEndofLife(EOL). However,itisimportanttonotethatpoweravailabilityis

influencedbyISSattitude,operationalmode

(e.g.,proximityoperations),Sunalphaandbeta

angle,shadowing,etc.

BETA GIMBAL ASSEMBLY (BGA)

ThefunctionoftheBGAistoprovideminor

arraypointingcorrectionalongtheBetaAngle.

Thebetaangleistheanglebetweentheorbit

planeandthesolardirection(changes

~4/day))tocompensateforapparentsolar

motioninducedbyseasonalvariations. There

isoneBGAassociatedwitheachSAW. The

BGAprovidesoneaxisofrotationforasolar

arraywing. TheBGAiscapableofafull

360degreesofrotationormaybecommanded

toaspecificlocationviacomputercommand.

Electricpowergeneratedbythesolararray

wingistransferredthroughtheBGAoverthe

entirerange

of

BGA

axis

rotation.

The

transfer

ofpowerisaccomplishedbyarotarycoupling,

therollringsubassembly,whichismounted

coaxiallywiththeaxisbearingandtorque

motor.

TheBGAmaybecommandedtothefollowing

modesofoperation:

AngleCommandMode. BGAaxisof

rotationalignedtoacommandedangle

position.

LatchMode. TheBGAaxisofrotationis

lockedatspecifiedlocationandprevented

fromfurtherrotation.

ManualOperatingMode. Allnonessential

functionsaredisabledandthedrivemotor

isdisabled. BGAaxismayberotatedby

manualactionfromtheIEAside.

Rate

Mode.

BGA

may

be

commanded

to

rotateataspecifiedrate.

ELECTRONICS CONTROL UNIT (ECU)

TheECUislocatedontheBGA. Itisthe

commandandcontrollinkforthesolararray

wingandBGA. TheECUprovidespowerand

controlforextensionandretractionofthesolar

arraymast,latchingandunlatchingofthe

blanketboxes,BGArotation,andBGAlatching.

SOLAR ALPHA ROTARY JOINT

ThepurposeoftheSARJistorotatethePVMs

toprovidealphaanglearraypointing

capability. TheportSARJandstarboardSARJ

arelocatedattheoutboardendoftheP3andS3

trusssegmentsandprovide360continuous

rotationalcapabilitytothesegmentsoutboard


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ofP3andS3. TheSARJwillnormallycomplete

onecomplete360degreerevolutionperorbit.

TheSARJtransferelectricalpowerthrougha

setof

roll

rings,

which

provide

acontinuous

rollingelectricalconnectionwhilerotating.

INTEGRATED EQUIPMENT ASSEMBLY

(IEA) EachIEA,locatedonP4,S4,P6andS6,has

manycomponents:12BatterySubassembly

orbitalreplacementunits(ORUs),sixBattery

Charge/DischargeUnits(BCDU)ORUs,two

DirectCurrentSwitchingUnits(DCSUs),two

DirectCurrenttoDirectCurrentConverterUnits(DDCUs),twoPhotovoltaicController

Units(PVCUs),andintegratestheThermal

ControlSubsystemwhichconsistsofone

PhotovoltaicRadiator(PVR)ORUandtwo

PumpFlowControlSubassembly(PFCS)ORUs

usedtotransferanddissipateheatgeneratedby

theIEAORUboxes. Inaddition,theIEA

providesaccommodationforammonia

servicingoftheoutboardPVmodulesaswell

aspass

through

of

power,

data

to

and

from

the

outboardtrusselements. Thestructural

transitionbetweentheP3andP4 (andS3and

S4whenlaunchednextyear)segmentsis

providedbytheAlphaJointInterfaceStructure.

TheIEAmeasures16feet(4.9meters)by16feet

(4.9meters)by16feet((4.9meters),weighs

nearly17,000poundsa(7,711.1kilograms)and

isdesigned

to

condition

and

store

the

electrical

powercollectedbythephotovoltaicarraysfor

useonboardtheStation.

TheIEAintegratestheenergystorage

subsystem,theelectricaldistribution

equipment,thethermalcontrolsystem,and

structuralframework. TheIEAconsistsofthree

majorelements:

1. Thepowersystemelectronicsconsistingof

theDCSU

used

for

primary

power

distribution;theDDCUusedtoproduce

regulatedsecondarypower;theBCDUused

tocontrolthecharginganddischargingof

thestoragebatteries;andthebatteriesused

tostorepower.

2. ThePhotovoltaicThermalControlSystem

(PVTCS)consistingof: thecoldplate

subassemblyusedtotransferheatfroman

electronicboxtothecoolant;thePump

FlowControlSubassembly(PFCS)usedto

pumpandcontroltheflowofammonia

coolant;andthePhotovoltaicRadiator

(PVR)usedtodissipatetheheatintodeep

space.

3. ThecomputersusedtocontroltheP4

moduleORUsconsistoftwoPhotovoltaic

ControllerUnit(PVCU)

Multiplexer/Demultiplexers(MDMs).

TheIEApowersystemisdividedintotwo

independentandidenticalchannels. Each

channeliscapableofcontrol(fineregulation),

storageanddistributionofpowertotheISS.

Thetwopowermodulesareattachedoutboard

oftheAJIS.


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ThebatteryORUscanbechangedout

roboticallyusingaspecialpurposemanipulator

ontheendofthestationsroboticarm. Each

batterymeasures

41

inches

(104.1

cm)

by

37inches(94cm)by19inches(48.3cm)and

weighs372pounds(168.7kilograms).

BATTERY CHARGE/DISCHARGE UNIT

(BCDU)

TheBCDUservesadualfunctionofcharging

thebatteriesduringisolationandproviding

conditionedbatterypowertotheprimary

powerbussesduringeclipse.

TheControlPowerRemoteBusIsolator

(CPRBI)controlstheflowofpowertotheDC

controlpoweroutputbusandalsofunctionsas

acircuitbreaker,limitingtheloadcurrent

duringfaults. TheFaultIsolator(FI)limitsthe

batterydischargecurrent,intheeventofafault,

to85to127amps. TheBCDUalsoincludes

provisionsforbatterystatusmonitoringand

protectionfrompowercircuitfaults.

EachBCDUmeasures28inches(71.1cm)by

40inches(101.6cm)by12inches(30.5cm)and

weights235pounds(106.6kilograms). The

BCDUhasan8.4kWbatterychargecapability

witha6.6kWdischargecapability. Itprovides

70to120voltsdccontrolpoweroutputandcan

regulatepowerbetween130to180voltsdc.

ThepowerstoragesystemconsistsofaBCDU

andtwoBatterySubassemblyORUs.

MAIN BUS SWITCHING UNIT (MBSU)

Locatedon

the

S0

truss,

the

four

MBSUs

distributeprimarypowerfromthepower

channels,downstreamtotheDDCUs,andother

loads. Theyalsoprovidethecapabilitytocross

tiePrimaryPowerChannelstofeedthose

DDCUloadsintheeventofaPrimaryPower

Failure.

Command,communication,healthmonitoring,

andRBIdrivefunctionsareprovidedbythe

SwitchgearControllerAssembly(SCA). The

MBSUshaveadesignlifeofapproximatelyfifteenyears. ThereisaspareMBSUlocatedon

orbit.

Thesystemsdesigncanaccommodatetheloss

ofPVmodulesandotherproblemsbyremotely

accessingtheMBSUs,byeitherthegroundor

onstation,andinternallyredirectingpowerto

bypassfaultsorfailuresintheEPS. Thefour

MBSUsthemselvesarenotredundant. All

MBSUsarerequiredtopowerallstationloads.

However,MBSUsprovideredundancyfor

powermodulesupstream. TheMBSUoutput

voltagerangeisfrom133to177Vdc.

8/14/2019 NASA Space Shuttle STS-116 Press