Mars Reconnaissance Orbiter 1 Overview of the Mars Reconnaissance Orbiter Mission Oct ‘01 MRO This technical data is export controlled under US law and

Mars Reconnaissance Orbiter

1

Overview of the Mars Reconnaissance

Orbiter Mission

Oct ‘01

MRO

This technical data is export controlled under US law and is being transferred by JPL to ASI or its contractors pursuant to the NASA/ASI Agreement which entered into force on September 25, 2001. This technical data is transferred to ASI or its contractors for use exclusively on the NASA/ASI MRO cooperative project, may not be used for any other purpose, and shall not be re-transferred without the prior written approval of NASA


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Lockheed Martin Private DataCompetition Sensitive Material


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PROJECT OVERVIEWMars Reconnaissance Orbiter

Salient Features

• 4 Earth years in Mars orbit

– 2 years science mapping

– 2 years relay mode

• International science payload with 30 cm resolution imaging

• Navigational Aid / Relay Telecom Payload

• Launch date August 2005

Science

• Characterize Mars’ seasonal cycles and diurnal variations of water, dust, and carbon dioxide.

• Characterize Mars’ global atmospheric structure, transport and surface changes.

• Search sites for evidence of aqueous and/or hydrothermal activity.

• Map and characterize in detail the stratigraphy, geologic structure and composition of Mars surface features

• Detect on Mars the presence of liquid water and determine the distribution of ground ice in the upper surface.

• Characterize the Martian gravity and atmosphere in greater detail.

• Characterize site for future landed missions.


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Mission Overview

• Deliver a single orbiter to conduct targeted reconnaissance to further our scientific understanding of Mars and to and characterize future landing sites

• Launches in August of 2005

• Arrival in March of 2006

• Aerobrake down into the primary science orbit of 200 x 400 km by Sept of 2006

• Primary science begins in late Nov 2006 and lasts for 687 Earth days ( 1 Martian Year)


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MRO Organization

Jim GrafManager

Richard ZurekProject Scientist

Ross Jones, Project Engineer

Tom Fouser (act.), Project Software Mgr

Arden Acord, Launch Vehicle Liaison

Bredt Martin, Business Mgr

Walt Boyd, Finance& Resource Mgr

Janis Norman, Secretary

Erica Beam, Scheduler

Marty Scarbrough, Acquisition Rep.

H. EisenFlight System Mgr

R. Nybakken (act.)CTM

B. JaiMission

OperationsSystems Mgr

D. JohnstonMission

Design Mgr

J. DuxburySci/Payload Mgr

W. MateerDep. P/L Mgr

James Graf

P. Barela. Mission

AssuranceMgr

LMA- Orbiter Kevin McNeill

Orbiter Mgr

J.Graf,PMR.Zurek, PS

Project Science Group (PSG)

SHARAD Experiment Mgr

TBD, Roma

Lead Payload System

Engineer*B.Mateer, Acting

Mars ClimateSounder

JPLG.Fraschetti

Radar Team(SHARAD)

Gravity Team(Tracking Data)

Context ImagerTeam

Radio Science Team

(Occultation/USO Data)

SHARADSupport

JPLW. Johnson

HighResolution

ImagerTBD

Mars ColorImager-WAC

MSSSM.Ravine

Op Nav CameraJPLG.Fraschetti

ContextImagerMSSSM.Ravine

Inst

rum

ents

ImagingSpectrometerTBD

AtmosphericStructure

Team(Aerobraking)

Facility

Investigations

Science & Payload OfficeJ.Duxbury, MgrW.Mateer, DeputyTBD, Deputy PS

MRO Science and Payload Office Organization

*Interfaces with LMA Payload Accomodations (Tim Girard); member of JPL MRO S/C Team

** Member of MRO Mission System Design Team ***I/F with JPL Mission Design Team

Approved:__sign. on file 10/8/01__

J.Graf, Proj Manager

__sign. on file 10/8/01___

R.Zurek, Proj Scientist

Payload System Engineers

A.Dalton***D.Norris

InvestigationScientists &Ops SupportA.Jerahian**

LMA PayloadAccommodations

ManagerTim Girard

Contract NegotiatorN.Walizer

SHARADInstrument

AleniaTBD


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S/C Overview

3-m HGA

20 m^2 Solar Array (Cell Area)

4-Pi Tx/Rv LGA

MGA2x100 W(RF) TWTA

2.1 m Drag Flaps

DC Brushless Motorw/16-Bit Resolvers

MARCI

PMIRR

VNIRHRI

20 Mhz Radar (7-m Dipole Antenna)

EMPM6xMR-107N4xMR-106B8xMR-111C

Optical Bench


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Orbiter Features

• 1800 kg launch mass with JPL design principles compliant margins.

• 20 m2 of solar array, providing ~2 kW of power.

• 3.0 m HGA attached directly to the bus with a 2 axis gimbal (no boom).– Design increases data rate over req’ts at maximum distance; increases data volume.

• Regulated multi-engine monoprop hydrazine system with engine out capability for MOI.

• Single set of deployments early in the mission.

• 3-axis stable for aerobraking.

• Pointing cross track and along track.

• Prominent risk management approach.

• Uses RAD750 with fast reboot capability.


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Mass Status

32.4 m^2

SubsystemStructuresMechanismsEPSAACSTelecomC&DHPropulsionHarnessThermal

Dry Orbiter Less PayloadPayload

Dry Orbiter w/ PayloadConsumables

Wet Orbiter

Orbiter ContingencyUnallocated Sys ReserveOrbiter Margin

Mass, CBE, kg

1532.3

143.2124.6

267.7 (30.1%)

517.8103.0620.8911.5

139.040.1

110.037.638.522.781.627.620.6


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Payload Description

Name Type Provider Resolution@ 200 km

Swath@ 200 km

Other Mass (kg)w/o margin

Orbital Average

Power (W)

High ResolutionImager

OpticalTargeted

AO ≤ 30 cm/pixel ≥ 3 km Panchromatic 40 < 50

Visible-Near Infrared

Spectrometer

OpticalTargeted

AO ≤ 25 m/pixel ≥ 5 km 0.4 - 3.6 µm 23 < 30

ContextImager

OpticalRegional

FacilityMSSS

≤ 4 m/pixel ≥ 20 km PanchromaticMinus Blue

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Sounding Radar(SHARAD)

RegionalFacility

ASI< 1000 m (w)

< 20 m (v)20 km (w)1 km (v)

20 MHz Center10 MHz Bandwidth

12 < 50

MARCI WA * OpticalMapping

PIMSSS

1 to10km/pixel

limb-to-limb 0.25 - 0.75 µm 1 3

MCS* AtmosphericMapping

PIJPL

≤ 5 kmvertical

-- 12 - 50 µm0.3 - 3.0 µm

6 8

OpNav OpticalTargeted

JPLMT

24 µrad/pixelPhobos/Deimos

-- 0.45 - 0.6 µm 3 3

Electra Radio JPLMT/MRO

-- -- UHF 15 40

Total 104 n/a

* MCO Investigation ReflightScience Payload

Engineering Payload


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Top Level Schedule


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Issues for Discussion

• Command and data processing– Location of SOPC

– Levels of processing and location of archiving

– Need for quick look images

• Agenda for the Radar Workshop on Dec. 3 & 4

• Organizational interface definition

• Instrument design and trade space for design options

• Accommodations-related issues (boom, etc.)

• Roles and responsibilities (off line)


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Organizational Counterparts

ASI/Alenia NASA/JPL

E. FlaminiProgram/Project (ASI)

R. Depaula/J. GrafProgram/Project (HQ/JPL)

A. CoradiniProgram Science (CNR)

J. Garvin/D. McCleeseProgram Science (HQ/JPL)

R. SeuTeam Leader (U of Rome)

R. ZurekMRO Project Scientist (JPL)

A. MasdeaExperiment Manager (U of Rome)G. BranconiProject Manager (Alenia)

J. DuxburyScience/Payload Manager (JPL)

C. ZelliInstrument Manager (Alenia)

W. JohnsonInstrument development (JPL)

TBDInst. System Eng. (Alenia)

W. Mateer (act., JPL)/ TBD Inst.Accommodation Eng. (LMA)

Documents

Mars Reconnaissance Orbiter 1 Overview of the Mars Reconnaissance Orbiter Mission Oct ‘01 MRO This technical data is export controlled under US law and