MarCO Mission Design & Navigation Peer Mars Cube One ... · Tomas Martin -Mur, Brian Young, Mark...
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Mission Design & Navigation Peer Review Tomas Martin-Mur, Brian Young, Mark Jesick 23 February 2015 MarCO Mars Cube One Overview John D. Baker 26 September 2017 Jet Propulsion Laboratory California Institute of Technology Copyright 2017 California Institute of Technology. Government sponsorship acknowledged.
Transcript of MarCO Mission Design & Navigation Peer Mars Cube One ... · Tomas Martin -Mur, Brian Young, Mark...
MissionDesign&NavigationPeerReview
TomasMartin-Mur,BrianYoung,MarkJesick23February2015
MarCO Mars Cube One
Overview
John D. Baker
26 September 2017Jet Propulsion LaboratoryCalifornia Institute of Technology Copyright2017CaliforniaInstituteofTechnology.Governmentsponsorshipacknowledged.
MissionDesign&NavigationPeerReview
TomasMartin-Mur,BrianYoung,MarkJesick23February2015
Deep-SpaceTelecomNeeds
2Copyright©2017CaliforniaInstituteofTechnology.GovernmentSponsorshipAcknowledged.*IMAGESNOTTOSCALE
EnvironmentHighionizingradiation
Clockstabilityovermissionduration
TrajectoryLargefree-spacepathlossSpacecraftdynamicseffects
NavigationOutsideGPSsignalrangeNoEarth’smagneticfields
Imagecredit:NASA
MissionDesign&NavigationPeerReview
TomasMartin-Mur,BrianYoung,MarkJesick23February2015
Deep-SpaceTelecomNeeds
3Copyright©2017CaliforniaInstituteofTechnology.GovernmentSponsorshipAcknowledged.*IMAGESNOTTOSCALE
TrajectoryLargefree-spacepathlossSpacecraftdynamicseffects
NavigationOutsideGPSsignalrangeNoEarth’smagneticfields
Imagecredit:NASA
RadiometricNavigationTechniques
LargeapertureantennasLowreceiversensitivity
Space-gradepartsCoherentTransponder
Anequallycapablegroundstation tosupportdeep-spaceexplorationneedsisrequired.
EnvironmentHighionizingradiation
Clockstabilityovermissionduration
Copyright©2017CaliforniaInstituteofTechnology.GovernmentSponsorshipAcknowledged.
IrisDeep-SpaceTransponder• CubeSat/SmallSat compatibledeep-spacetransponder• ~0.5Uvolume(100.5x101.0x56.0mm;transponderonly)• DSN/NEN-compatibleX-banduplink/downlink(7.2GHz/8.4GHz)• SoftwareDefinedRadiowithLeon3-FTsoftcore processor• Providesnavigationalsupport(Doppler,Ranging,DDOR)• Modularhardwaredesignforotherfrequencybands(UHF,S-
band,Ka-band)
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V1.0
V2.0
V2.1
IrisSpecification Units IrisV1.0forINSPIRE
IrisV2.0forMarCO
IrisV2.1forSLSEM-1
Mass grams 450(nochassis) 1210(w/UHF-Rx) <1000(X/X-only)
Volume U 0.46 0.77(w/UHF-Rx) 0.56
BusInputVoltage Vdc 6.4– 8.4 10.5– 12.3 9.0 – 28.0
DCPower* W 13.0 35.0 33.7
RFOutputPower* W 0.15 3.3 3.8
ReceiverNoise Figure dB 5.0 – 6.0 3.5 3.5
ReceiverSensitivity dBm -135@70HzLBW -139@70HzLBW -151@20HzLBW
UplinkDataRate† bps 1,000 62.5 & 1,000 62.5 – 8,000
DownlinkDataRate† bps 62.5 – 64,000 62.5 & 1,000&8,000 62.5 – 256,000
TelemetryEncoding Conv &ReedSolomon Turbo-1/6only Conv,Reed Solomon,Turbo1/2,1/3,1/6
RadiationTolerance krads N/A 15.0TID 23.0TID
S/CInterface 1MHzSPI 1MHz SPI 1MHzSPI
*Nominalatambient†Subjecttolinkmargin
MarCO
EM-1
INSPIRE
MissionDesign&NavigationPeerReview
TomasMartin-Mur,BrianYoung,MarkJesick23February2015
May 2018Vandenburg
Mars
Earth
November, 2018
Entry,Descent,andLanding
MarCO Objectives:- LaunchwithInsightMay2018- Demodeepspacecomm andnavcapabilityforSmallSats
- Attempt8kbpsreal-timerelayduringInsightEDL
UHF Relay
DSN 70mReception
FM1 post-Vibe FM1inCubesat Lab1December2015
ITAR CONTROLLED
ITAR CONTROLLED
MarCO JPL Pre-Ship 9 Dec. 2015
MarCO on Atlas (4-meter faring)
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x The MarCOs will be isolated from the InSight faring (4-meter)
TYVAK PROPRIETARY // ULA PROPRIETARY
MarCO location on Launch Vehicle
Mechanical Configuration: Deployed
Solar ArrayFeed Sun Sensor
Cold Gas System
Iris Stack
SSPA & LNA AssemblyCabling & Cameras
Battery Assembly
ReflectArray
C&DH, EPS, XACT stack
Mechanical Configuration: Deployed
UHF Loop Antenna
Thrusters
Tx/ Rx LGA (bottom, not shown)
Radiator
Tx/Rx MGA (co-boresighted with HGA)
Milestones-to-go
² Nov Complete assembly and test of FM2² Dec Internal JPL FRR² Dec-Jan Brief status to NASA HQ² Late Feb Ship S/C to Tyvak for Dispenser I&T² mid/end Feb KSC Reviews (MRR, Pre-integ, Pre-Install)² Mar Installation on Launch Vehicle (VAFB)² ~mid-Feb internal JPL ORR² 5 May Insight Launch period open
