mars reconnaissance orbiter 1 overview of the mars reconnaissance orbiter mission oct ‘01 mro this...
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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
Mars Reconnaissance Orbiter
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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.
Mars Reconnaissance Orbiter
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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)
Mars Reconnaissance Orbiter
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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
Mars Reconnaissance Orbiter
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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
Mars Reconnaissance Orbiter
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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.
Mars Reconnaissance Orbiter
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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
Mars Reconnaissance Orbiter
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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
4 4
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
Mars Reconnaissance Orbiter
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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)
Mars Reconnaissance Orbiter
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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)