Path: Interplanetary/PlanarOptimization
% Pluto planar orbit optimization Calculate the optimal thrust to achieve a planar trajectory to the desired final orbit, assuming a certain specific impulse (exhaust velocity) and specific power for the engine. The fuel structural mass fraction is 0.02. The demo delivers 1000 kg to Pluto in 3 years. EXAMPLES: Pluto mission in 5.2 years, with 1000 kg payload and 10800 kg total dry mass, 36,700 kg fuel, with 1 MW fission reactor. This corresponds to a specific power of about 134 W/kg with a payload of 2646. Total efficiency to thrust is 15.8% and uE is 40 km/s. Total thrust is 8 N. Assumed distance to Pluto is 30.5 AU. "Standard" mission: 1000 kg payload, 1000 W/kg specific mass, efficiency of 0.4, uE of 100 km/s
Interplanetary: Optimization/PlanarHelioOptimal Interplanetary: Optimization/SimulatePlanarHelioTrajectory StraightLine: ConstantThrust/StraightLineReport Common: Database/Constant
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