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Mars ascent stage mass savings made available through nuclear propulsion are discussed and compared to savings made available by on-the-surface in-situ oxygen propellant production for chemical oxygen / hydrogen and oxygen / methane propulsion systems.
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This page is a summary of: Nuclear Propulsion and In-Situ Oxygen Propellant Supply for Mars Ascent Vehicles: A Performance Comparison, June 1993, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/6.1993-1949.
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