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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Mars Reconnaissance Orbiter 1 Overview of the Mars Reconnaissance Orbiter Mission Oct ‘01 MRO This technical data is export controlled under US law and.
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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
2
Lockheed Martin Private DataCompetition Sensitive Material
Mars Reconnaissance Orbiter
3
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)
*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.