11

OriginsSpaceTelescope(OST)MissionConcept1

Open Issues

Face-to-Face#5June1-2,2017

Ruth.C.Carter@nasa.gov

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22

Concept1DesignStatus/Issues• Concept1massis~2,000kgoverthelaunchvehicle(VulcanAces5m

fairing)liftcapability– Massfor5instrumentsis2643kg

• Far-IRImager/Polarimeter (FIP):781kg• HighResolutionSpectrometer(HRS):935kg• MediumResolutionSurveySpectrometer(MRSS):435kg• HeterodyneInstrument(HI):383kg• Mid-IRSpectrometer/Imager/Coronagraph(MISC):108kg

• Opticalraytracesforinstrumentsarestillinprogressandsomearenearcompletion– Eliminationofanyoftheseinstrumentswillresultinreworkofraytracesand

packagingforremaininginstruments• Fairingvolumeisextremelytightanduncertain,overallpackagingis

uncertainanddeploymentisstillTBD

• CurrentConcept1istooheavytobelaunchedona5mfairing– Volumeistightanduncertain

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Solution:LargerLaunchVehicle(LV)

• NASASpaceLaunchSystem(SLS)haslargermassandvolumecapabilitiestoaccommodatecurrentOSTConcept1– FairingSizes: 8.4x19m,10mx31m

• SLSwillbeavailablein2030’swhenOSTwillbereadytolaunch– BothLUVOIRandHabEx missionconceptsincludeSLS

• SLSisadevelopmentprogramanditisyettohaveafirstlaunch– Higherriskiteminmissiondevelopment

• LargerLVcostwillbehigher,howeverlargervolumemayallowflightsystemdesigntobelesscomplex,resultinginlowermissioncostoverall

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StudyOfficePlanandRequest

• Plantoworkwithinstrumentteamstoscaledowninstrumentvolume,massandpowertofitintoa5meterfairing

• Intheeventthatthescaleddowninstrumentsresultsinexceeding5mfairingcapabilities,weneeddesignflexibilitytoassumealargerLV– InordertocompleteConcept1designby9/30/17,weneed

designflexibility

• StudyOfficerequestsSTDTpermissiontogotoalargerlaunchvehicle,ifnecessary– Needadecisionby6/15/2017,5pm

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StudyScheduleOriginsSpaceTelescopeDecadalMissionStudySchedule

Jan Feb Mar Apr May Jun Jul Aug Sept Oct Nov Dec Jan Feb Mar Apr May Jun Jul Aug Sept Oct Nov Dec Jan Feb Mar

Milestone

F2FMeetings

StudyDeliverables

NASAHQApD

Science

Technology

Med-ResolutionSurvey

Specctrogarph

(MRRS)

Far-IRImager/Polarimeter

(FIP)

High-Resolution

Sepectrograph(HRS)

HeterodyneInstrument

(HI)

Mid-IRImager

Spectrometer

(MISC)

InstrumentAccommodation

Module

(IAM)

TelescopeSystem

MissionDefintion,Design,

&Development

CY2017 CY2018 CY2019

f2f #43/21-22

f2f #56/TBD

'Strawman'Telescope design,aperturesizes

Decadal MisssionEnablingTechnology

TRLAssessmentsTRL AssessmentUpdatePrep

Definemissionrequirements,minimumsuccesscriteria,

Defineinstsrumentinterfaces, criteria,

configuration,instrumentplacmentsinIAM

Defineoptical reqrm'ts

Defineoptical reqrm'ts

Instrument def.,reqr,'ts,

HRSIDL(5/1-5)

Instrument def.,reqr,'ts, interfaces,

prepforIAMIDLMRRSI/F f2fMtg

HII/F f2fMtg

MISCI/F f2fMtg

Defineoptical reqrm'ts

Defineoptical reqrm'ts

Instrument def.,reqr,'ts,

interfaces,prepforIAMIDL

Instrument def.,reqr,'ts, interfaces,prep

forIAMIDL

TelescopeIDL#1(8/14-18)

Telescopetypedef.,reqr,'ts, interfaces, prepforTelescopeIDL

MDL#1(9/18-22)

TRL Assessment UpdateReporttoHQ(6/30)

InterimReporttoHQ(12/5)

2MissionConcepts, mission duration, LVselections, ConOps,

prepforMDL,Developend-to-end (ETE)missionschedule

PrelimMissionDesignITR

10/18

f2f #6CANReleased:1/26

Partner

On-Board

Prepare/draft interim report forsubmittal toHQ,Develop sciencecasesforinterimreport

ScienceDefinition, Sciencerequirments, minimumscience, sciencecases

Prep missiondesignforInterimRpt

Mission Design

forInterimRpt

Sciencecases

forInterimRpt

AAS f2f #7 f2f #8

TRL Assessment UpdateReporttoHQ(6/30)

FinalReporttoHQ

OSTPresentation

toDecadal

Committee

Address ITRComments

Mission costing, PrepforMDL#2,

prep forCR

Address ITRComments

Address ITRComments

UpdateTelescopsedesigns, requirements, interfaces,PrepforTelescope IDL #2

UpdateIAMdesignconcept,ceriteria, interfaces,

IAM IDL#2(3/TBD)

TelescopeIDL#2(4/TBD)

MDL#2(5/TBD)

AddressIAM Comments,CRcomments, Finalreport draftandreview

FinalizeScienceRequirments, Scicence Cases,ScienceInstrument operation scenarios

AddressCRcomments, adjustmissioncost, preparefinalreport

MissionDesignITR,CR

Refine ETEmissionschedule andcost

Draft FinalRpt&Review

UpdateMisssionEnablingTechnologyTRLAssessments,DevelopTechnology

Roadmapfortechnology enhancementTRL Assessment Update

Prep&review

DraftTechnologyRoadmap, estimatecostfor technologyenhancement

f2f #9

InstrumentI/Ff2fMtgs(6/13)

Update instrument, requirements, design,interface definitions

Update instrument, requirements, design,interface definitions

Update instrument, requirements, design,interface definitions

Update instrument, requirements, design,interface definitions

Address ITRComments

Address ITRComments

Address ITRComments

Address ITRComments

Address ITRComments

instrument costestimatesreview,finalreviewofinstrument req.criteria,

boundarycondition, operation scenarios

instrument costestimatesreview,finalreviewofinstrument req.criteria,

boundarycondition, operation scenarios

instrument costestimatesreview,finalreviewofinstrument req.criteria,

boundarycondition, operation scenarios

instrument costestimatesreview,finalreviewofinstrument req.criteria,

boundarycondition, operation scenarios

IAMcostestimatesreview,finalreviewofinterfaces, boundary

condition, instrument postionallocations

Telescopecostestimatesreview,interfaces,

boundarycondition, deploymentschemes,

Inputto

IAM IDL#2

Inputto

Inputto

IAM IDL#2

Inputto

IAM IDL#2

Inputto

IAM IDL#2

DetermineSciCaseforCoronagraph(MISC)

IAM#1(7/17-21)

Defineoptical reqrm'ts

Update instrument, requirements, design,interface definitions

instrument costestimatesreview,finalreviewofinstrument req.criteria,

boundarycondition, operation scenarios

FIP IDL(4/17-21)

Instrument def.,reqr,'ts,

interfaces, prepforIDL

Address ITRComments, enablingtechnologies

TeamX

66

Back-Up

77

OSTConcept1DesignParameters

• 9meterdiameterprimarymirror– Segmented,Off-AxisTelescope

• 5scienceinstruments– Far-IRImager/Polarimeter (FIP)– HighResolutionSpectrometer(HRS)– MediumResolutionSurveySpectrometer(MRSS)– HeterodyneInstrument(HI)– Mid-IRSpectrometer/Imager/Coronagraph(MISC)

• InstrumentAccommodationModule(IAM)• 8cryo-coolerstocoolandmaintainTelescopeandIAMat

4Kelvin• Launchona5meterfairinglaunchvehicle

– VulcanAcesassumed• MissionOperationsOrbitisSunEarthL2

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5mFairingDesignChallenges1. Massexceedsallowable.2. StowinganddeployingSunshadeandBaffle:

- Mightbeenoughspacetodoitincurrentconfiguration– TBD.Stowedstack-uponlyallowsfor.75minheightforstowingSunshade.

- Engineer,within-depthknowledgeofJWSTSunshadedesign,isjuststartingtolookatit.

- Cableharnessesandcryo lines(volumeTBD)needtostowinsameareaasSunShade.Maynotbeenoughroomforitall.

- Howtodeploythecableharnessesandcryo linesANDtheSunshadewhentheyallstowinsamelocationmaybeunworkable.

- Maynotbeenoughroominbustostoreeverything.ManydeploymentboomsareneededforSunshade.Largeproptanktakesupalotofroom,aswell.LayoutofBusisTBD.

3. CurrentlyHRSinstrumentinterfereswithlowercornerofstowedPrimaryMirror• PackagingofHRSmightnotallowforremovalofinterference– TBD.• RemovingonehexsegmentofPMrequiredifHRSinterferenceremains.

4. CGifstowedassemblywillberatherhigh.HighCGandhighmassmayprecludeusingthislaunchvehicle.

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Layoutshownisabitobsolete,butthe.75mspaceisaccurate,givencurrentlaunchvehiclefairinglimitation.

1010

142”

57”Areaofredtriangle=1/2[(142-57)/2]^2=903in^2

AreaofDTA=PixD^2/4=Pix40in^2/4=1256in^2

AreaofbustopshapewithoutDTAarea=142^2– 4(903”)– 1256=20,164in^2– 3,612in^2– 1256in^2=15,296in^2(9.8m^2)

Volumeavailableforsunshadestowageandcableharnessesandcryo lines=9.8m^2x.75m=7.35m^3Areaofsunshade=TBD

BusVolume

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Concept1MassEstimatespreliminaryandimmature

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PotentialLaunchVehicles

LaunchVehicle ManufacturerCountry

ofOrigin

CostperlaunchFairingSizeDia.byLength

PayloadtoGTO(kg)

PayloadtoL2(3)

Status LaunchSites

Falcon9FullThrust(FT)(1)

SpaceX U.S.A. $62Million 5.2mx13.1m 8,300 3,370(4) FT:Active CapeCanaveralSLC-40KennedySpaceCenterLC-39AVandenbergSLC-4E

DeltaIVHeavy ULA U.S.A $375Million(2014) 5mx19.1m 14,220 10,695 Active SLC-37B,CapeCanaveralSLC-6VandenbergAFB

AtlasV500Series ULA U.S.A NotAvailable 5.4mx20.7m5.4mx23.5m

4,750–8,900 2125-6,165 Active CapeCanaveralSLC-41VandenbergAFBSLC-3E

FalconHeavy SpaceX U.S.A $90Millionforupto8,000kgtoGTO

5.2mx13.1m (27˚)22,200 NotAvailable Indevelopment KennedyLC-39AVandenbergAFBSLC-4E

SpaceLaunchSystem

Boeing,ULA,OrbitalATK,AerojectRocketdyne

U.S.A $500Million 5mx19m8.4mx19m10mx31m

Notavailable NotAvailable Indevelopment LC-39B,KennedySpaceCenter

Ariane5 AirbusDefenseandSpace Europe $165-$220Million(20ESAmemberstates)

5.4mx17m (27˚)ECA(2):10,500 NotAvailable Active GuianaSpaceCentreELA-3,FrenchGuiana

H-llB MitsubishiHeavyIndustries

Japan NotAvailable 5.1mx15m 8,000 NotAvailable Active TanegashimaSpaceCenter,Japan

U.S.A./In

de

velopm

ent

Foreign/

Activ

eU.S.A./Active

Notes:1) FT – Full Thrust is the latest version of the Falcon 9; versions v1.1 and v1.0 are retired from service.2) ECA - The Ariane 5 ECA (Evolution Cryotechnique type A), first successfully flown in 2005, uses an improved Vulcain 2 first-stage engine with alonger, more efficient nozzle with a more efficient flow cycle and denser propellant ratio. The Ariane 5 ECA has a GTO launch capacity of 9,100 kg(20,100 lb.) for dual payloads or 9,600 kg (21,200 lb.) for a single payload. ES - the Ariane 5 ES (Evolution Storable) has an estimated LEO launchcapacity of 21,000 kg (46,000 lb.). Ariane versions A5 G, A5 G+, and A5 GS are retired from service.3) L2 - Lagrange point 2 named after Joseph Lagrange, an 18th century mathematician, who found the solution to the “three-body problem”. Inastrodynamics, the characteristic energy (C3) is a measure of the excess specific energy over that required to just barely escape from a massive body.The units are length2/time2, i.e., energy per mass. In this case an initial C3 estimate of -0.5 km2/sec2 to L2 was assumed.4) Assumes the Drone recovery option for the Falcon 9 FT 1st Stage and launch from SLC-41 at CCAFS.