THE “SolarClipper” SCENARIO (1 of 4) SYSTEM CHARACTERISTICS • An SSP-based concept, derived from the SunTower SPS system concept - Vehicle Specific Mass = 5 kg/kW (Power =1 kg/kW, Propulsion/Vehicle = 4 kg/kW) - Specific Impulse = 5000-6000 seconds - Standard Power Unit = 250 kW @ 1 AU (Concentrator Diameter = 26 m) • Version I: CT-MTV - Cargo transport Mars Transfer Vehicle and Mars orbit infrastructure (power, comm., operations staging) - 6 MW (12 pairs of identical power units; 12 identical propulsion units) - Specific Impulse = 6000 seconds - Payload = 140 MT; IMLEO = 240 MT; Propellant = 70 MT; Drymass = 30 MT • Version II: HE-MTV - Reusable vehicle (planned for multiple transits to/from Mars) - Human expedition Mars Transfer Vehicle - 12 MW (24 pairs of identical power units; 24 identical propulsion units) - Specific Impulse = 5200 seconds - Payload = 80 MT (includes 40 MT return propellant); IMLEO = 240 MT; Propellant (Earth-to-Mars) = 100 MT; Drymass = 60 MT THE “SolarClipper” SCENARIO (2 of 4) FIRST MISSION SYSTEM SKETCH • The “SolarClipper” Scenario - A sketch of a notional SPS-Derived Mars Mission for illustrative purpose - Comparable to the adjusted Design Reference Mission - Total IMLEO = 960 MT; Total Payload to Mars Orbit = 500 MT ♦ CT-MTV: 3 Vehicles per expedition - 1-Way; vehicles remain in Mars orbit as Mars-based SPS - 3x6 MW @ 1 AU (72 (36 pairs) identical power units; 36 identical propulsion units) - Specific Impulse = 6000 seconds - Payload = 3x140 MT = 420 MT (including 50-100 MT (TBD) of propellant for Earth return); IMLEO = 3x240 MT; Propellant = 3x70 MT; Drymass =3x30 MT - Transit Times = 320 d (Heliocentric) + 30 d (Mars Capture) + 150 d (Earth Escape) - Launch Scenario = 3x(1 Shuttle-Derived Vehicles + 8 RLVs)... or other options • HE-MTV: 1 Vehicle per expedition - 12 MW @ 1 AU (48 (24 pairs) identical power units; 24 identical propulsion units) - Specific Impulse = 5200 seconds - Payload = 80 MT; IMLEO = 240 MT; Propellant = 100 MT; Drymass = 60 MT - Transit Times = 210 d (Heliocentric) + 9 d (Mars Capture) + 70 d (Earth Escape) - Launch Scenario = 1 Shuttle-Derived Vehicle + 10 RLVs (or other options)
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