Water Electrolysis for Propulsion of a Crewed Mars

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Water Electrolysis for Propulsion of a Crewed Mars ( water-electrolysis-propulsion-crewed-mars )

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Table II-1: SLS Water Propellant Depot Delivery Capacities Payload Mass, t of: LEO GTO HEO LL2 Mars Water 126 67 47.5 48.5 36.5 Tank 1.61 1.06 0.84 0.85 0.71 RCS 0.6 0.4 0.4 0* 1 Solar Panels, Avionics 0.6 0.6 0.6 0* 0.9 Total Mass 128.81 69.06 49.34 49.35 39.11 Available Mass 130 70 50 50 40 Margin 1.19 0.94 0.66 0.64 0.89 Propellant Fraction 97.8% 97.0% 96.2% 98.3% 93.3% Table II-2: FH Water Propellant Depot Delivery Capacities Payload Mass, t of: LEO GTO HEO LL2 Mars Water 61.5 25 18 19 14.4 Tank 1 0.55 0.44 0.46 0.38 RCS 0.4 0.3 0.3 0* 0.6 Solar Panels, Avionics 0.4 0.4 0.4 0* 0.6 Total Mass 63.3 26.25 19.14 19.46 16.08 Available Mass 63.8 26.7 20 20 16.8 Margin 0.5 0.45 0.86 0.54 0.72 Propellant Fraction 97.2% 95.2% 94.0% 97.6% 90.2% Table II-3: SLS Water Propulsion Module Delivery Capacities Payload Mass, t of: LEO GTO HEO LL2 Water 121 61.5 41.5 42.5 Tank 1.57 1 0.77 0.78 Engine 6 6 6 6 RCS 0.6 0.4 0.4 0* Solar Panels, Avionics 0.6 0.6 0.6 0* Total Mass 129.77 69.54 49.27 49.28 Available Mass 130 70 50 50 Margin 0.23 0.4 0.73 0.72 Propellant Fraction 93.2% 88.4% 84.2% 86.2% Table II-4: FH Water Propulsion Module Delivery Capacities Payload Mass, t of: LEO GTO HEO LL2 Water 55 19 12 13 Tank 0.93 0.46 0.34 0.35 Engine 6 6 6 6 RCS 0.4 0.3 0.3 0* Solar Panels, Avionics 0.4 0.4 0.4 0* Total Mass 62.73 26.16 19.04 19.35 Available Mass 63.8 26.7 20 20 Margin 1.07 0.54 0.96 0.65 Propellant Fraction 87.7% 72.6% 63.0% 67.1% *Dependent on the Deep Space Gateway for stationkeeping. 5 American Institute of Aeronautics and Astronautics Downloaded by NASA LANGLEY RESEARCH CENTRE on January 30, 2018 | http://arc.aiaa.org | DOI: 10.2514/6.2018-1537

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