Path: Orbit/LowEnergyManeuver

% Minimize the keplerian energy of the final state of a transfer orbit
   between the Earth and the Moon.

   Since version 9.
   [elementsNew,dV1EphNew,dtNew,f,jTraj,jL2,dV2EphNew,tM2New] =

   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
   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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