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Path: Orbit/LowEnergyManeuver
% Minimize the keplerian energy of the final state of a transfer orbit between the Earth and the Moon. Since version 9. -------------------------------------------------------------------------- Form: [elementsNew,dV1EphNew,dtNew,f,jTraj,jL2,dV2EphNew,tM2New] = MinE4BP(elements,dV1Eph,dtTarg,et,muMoon,p,dV2Eph,tM2) -------------------------------------------------------------------------- ------ Inputs ------ elements (1,6) Ecliptic orbital elements of the initial state dV1Eph (1) Magnitude of the initial maneuver dtTarg (1) Transfer time et (1) Seconds after the epoch at which the orbit begins muMoon (1) Gravitational Parameter of the moon p (1) L2 distance from the moon ------- Outputs ------- elementsNew (1) Optimized ecliptic elements dV1EphNew (1) Optimized initial maneuver magnitude dtNew (1) Optimized transfer time f (1) Final energy with resepect to the moon jTraj (1) Jacobi constant of the final state jL2 (1) Jacobi constant of the L2 point --------------------------------------------------------------------------
Common: Database/Constant Math: Linear/Mag Math: Linear/Unit Orbit: LowEnergyManeuver/CRTBPJacobiConstant Orbit: LowEnergyManeuver/CheckForOptimizationToolbox Orbit: LowEnergyManeuver/EnergyWRTMoon Orbit: OrbitCoord/J20002RotPulsPlanetMoon Orbit: OrbitCoord/Kms2CRTBP Orbit: OrbitSim/Propagate4BP SC: BasicOrbit/El2RV SC: Ephem/PlanetPositionEMBarycenter
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