Path: Interplanetary/Optimization
% Optimal 3D trajectory between two planets, fixed time (fmincon)
Uses the JPL ephemerides. planet2 can be a number from 1-9 or a data
structure. This stops at the target. The objective, which is minimized,
is the total acceleration required. Generates a trajectory plot.
Type TrajectoryBetweenTwoPlanets for two demos: Earth to Mars using both
JPL ephemerides, and Earth to Pluto using a data structure for planet2.
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Form:
s = TrajectoryBetweenTwoPlanets( jD0, planet1, planet2, years, n, opts, nRSim )
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Inputs
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jD0 (1,1) Start Julian Date
planet1 (1,1) Id of departure planet (1-9)
planet2 (1,1) Id of arrival planet (1-9) or data structure
.name (1,:) Name
.el (1,6) Orbital elements - epoch must be jD0
years (1,1) Mission duration (years)
n (1,1) Number of steps in solution
opts (.) Data structure for fmincon
nRSim (1,1) Ratio of sim points to optimization points
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Outputs
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s (.) Output structure
.x (6,:) States
.a (3,:) Acceleration vector (km/s^2)
.jD0 (1,:) Julian date
.t (1,:) Elapsed time (s)
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See also: FindDepartureDate
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Interplanetary: Ephemeris/PlanetPosJPL Interplanetary: Optimization/FindDepartureDate Interplanetary: Visualization/PlanetTrajectoryPlot Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/RV2El Common: Database/Constant Common: General/DispWithTitle Common: Graphics/Plot2D Common: Graphics/TimeLabl Common: Time/Date2JD Math: Integration/RK4 Math: Linear/Mag Math: Linear/Unit
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