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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