Path: Interplanetary/OrbitOptimization
% Optimal 3D transfer to Mars, continuous thrust Optimize a transfer to Mars for continuous thrust, minimizing the total acceleration. This is a fixed end point optimization, run it with different durations and start dates to see how the delta-V required will vary. This routine uses JPL ephemerides for both the Earth and Mars. The optimization function requires fmincon in the Optimization toolbox. This demo uses a longer duration resulting in a power level that might be appropriate for for a solar powered electric propulsion mission. See also: Date2JD, TrajectoryBetweenTwoPlanets, SpacecraftFromAccel % -------------------------------------------------------------------------- Copyright (c) 2023 Princeton Satellite Systems, Inc. All rights reserved. Since version 2023.1 --------------------------------------------------------------------------
Orbit: Optimization/SpacecraftFromAccel Orbit: Optimization/TrajectoryBetweenTwoPlanets Common: Time/Date2JD
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