MarsOptimalTransfer:

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
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Children:

Orbit: Optimization/SpacecraftFromAccel
Orbit: Optimization/TrajectoryBetweenTwoPlanets
Common: Time/Date2JD

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