Vision and Voyages for Planetary Science in the - Solar System ...

Mars Sample Return Orbiter and Earth Entry Vehicle
MSR Orbiter an and Earth Entry Vehicle
SOURCE: NASA Mission Study (transmitted from Lisa May, NASA Planetary Science
Division)
Scientific Objectives
• Detect, rendezvous, and capture Orbiting Sample placed
in orbit by Mars Ascent Vehicle
• Transfer the Orbiting Sample to an Earth Entry Vehicle
(EEV)
• Return the EEV to Earth
• Provide a communications relay between Earth and the
Mars Sample Return Lander
• Build Sample Processing Facility
• Key science themes:
– None
Key Parameters
• Payload
– Optical Navigation Camera Assembly
– Sample Capture and Transfer System
– Earth Entry Vehicle
• One x 4.3 m Ultraflex solar array (1.25 kW @1AU
Beginning of Life) plus one unpopulated 4.3 m panel for
aerobraking
• Launch Mass: 3270 kg
• Launch Date: 2022 (on Atlas V 551)
• Orbit: 500 km circular Mars orbit (within ± 30 deg
inclination) followed by sample retrieval and Earth return
Key Challenges
• Sample Detection, Rendezvous, and Capture
– More autonomy required than Orbital Express mission
– Minimal instrumentation for rendezvous and capture
• Orbiter Instrument and Communications Package
Growth
– Growth anticipated for onboard instrumentation
– Low (10 kbps) telemetry rate unlikely to support
instrument growth
• Sample Transfer to EEV and Back Contamination
– Lack of definition for sample transfer and encapsulation
– Planetary protection methodologies to prevent back
contamination need further development
• New Earth Entry Vehicle Design
– Very high reliability required for new EEV design
– Heritage carbon phenolic manufacturing process needs
to be rediscovered
Key Cost Element Comparison
Cost Risk Analysis S‐Curve
PREPUBLICATION COPY—SUBJECT TO FURTHER EDITORIAL CORRECTION
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