Mars Sample Return mission utilizing in-situ propellant production

Details Mars Sample Return mission utilizing in-situ propellant production Mars Sample Return mission utilizing in-situ propellant production

Mar 1995

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1995lock.rept.....z&link_type=abstract

Final Report Lockheed Martin Corp., Denver, CO.

Computer Science

Atmospheric Composition, Carbon Dioxide, Liquid Rocket Propellants, Mars Atmosphere, Mars Sample Return Missions, Methane, Oxygen, Propellant Additives, Propellant Chemistry, Cost Reduction, Electrolysis, Hydrogen, Low Cost, Mixing Ratios, Specific Impulse, Weight Reduction

Scientific paper

This report presents the results of a study examining the potential of in-situ propellant production (ISPP) on Mars to aid in achieving a low cost Mars Sample Return (MSR) mission. Two versions of such a mission were examined: a baseline version employing a dual string spacecraft, and a light weight version employing single string architecture with selective redundancy. Both systems employed light weight avionics currently being developed by Lockheed Martin, Jet Propulsion Lab and elsewhere in the aerospace community, both used a new concept for a simple, light weight parachuteless sample return capsule, both used a slightly modified version of the Mars Surveyor lander currently under development at Lockheed Martin for flight in 1998, and both used a combination of the Sabatier-electrolysis and reverse water gas shift ISPP systems to produce methane/oxygen propellant on Mars by combining a small quantity of imported hydrogen with the Martian CO2 atmosphere. It was found that the baseline mission could be launched on a Delta 7925 and return a 0.5 kg sample with 82 percent mission launch margin;over and beyond subsystem allocated contingency masses . The lightweight version could be launched on a Mid-Lite vehicle and return a 0.25 kg sample with 11 percent launch margin, over and above subsystem contingency mass allocations.

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