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)

4

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)

2

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