Path: Orbit/LowEnergyManeuver
% Demonstrate targeting Start with an initial orbit and impulsive burn, then numerically optimize so that the location of the Moon is the final condition and the magnitude of the burn is minimized. The dynamical model is the 3 body problem, but functions exist also for the CRTBP and the full 4 body problem.
AC: ACData/ACTConstants Orbit: LowEnergyManeuver/CheckForOptimizationToolbox Orbit: LowEnergyManeuver/J20002RotPuls Orbit: LowEnergyManeuver/PlanetId Orbit: LowEnergyManeuver/PlotLET3BP Orbit: LowEnergyManeuver/Propagate3BP Orbit: LowEnergyManeuver/Targeting3BP2 SC: BasicOrbit/CP2I SC: BasicOrbit/E2Nu SC: BasicOrbit/El2RV SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: BasicOrbit/RVFromKepler SC: Ephem/CEcl2Eq SC: Ephem/InterpolateState SC: Ephem/PlanetPosJPL SC: Ephem/PlanetPositionEMBarycenter SC: SCData/bin2000 SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/SwooshWatermark Common: CommonData/xSplashSmall Common: Database/Constant Common: General/CellToMat Common: General/DeBlankLT Common: General/DeleteCell Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/Plot3D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2000 Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit
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