Path: Orbit/LowEnergyManeuver

% Compute a ballistic lunar capture trajectory from a circular orbit
 about Earth with a radius of r0 to a weakly captured lunar orbit.

 Requires the Optimization Toolbox.
   LETTrans = LowEnergyEarthToMoonTransfer(jD,r0)

   jD             (1)  Julian Date of transfer
   r0             (1)  Initial circular orbit radius (km)
   LETTrans       (.)  Data structure with information about the orbit
                  .elements            ecliptic orbital elements of the
                                       initial state
                  .initialStateJ2000   Initial state vector
                  .maneuver            Magnitude of the initial maneuver
                  .timeOfFlight        Period of the transfer
                  .finalEnergy         Final energy level
                  .family              CRTBP orbit family
                  .muMoon              Gravitational Parameter of the moon
                  .muPlanet            Gravitational Parameter of the planet
                  .cTraj               Jacobi constant of the final state
                  .cL2                 Jacobi constant of the L2 point
                  .burns               number of burn maneuvers performed

   Reference: Griesemer, P. R., Ocampo, C. A., and Cooley, D. S., "Targeting
   Ballistic Lunar Capture Trajectories Using Periodic Orbits in the Sun-Earth
   CRTBP", accepted for publication by the AIAA Journal of Guidance, Control,
   and Dynamics, Feb, 2010.


Common: Database/Constant
Common: Time/JD2000
Math: Linear/Mag
Orbit: LowEnergyManeuver/CheckForOptimizationToolbox
Orbit: LowEnergyManeuver/LETPhasing
Orbit: LowEnergyManeuver/LowEnergyTransferInCRTBP
Orbit: LowEnergyManeuver/MinE4BP
Orbit: LowEnergyManeuver/PlotLET
Orbit: LowEnergyManeuver/PlotLET3BP
Orbit: LowEnergyManeuver/Targeting3BP2
Orbit: LowEnergyManeuver/Targeting4BP
Orbit: LowEnergyManeuver/Targeting4BPB
Orbit: OrbitCoord/CRTBP2kms
Orbit: OrbitCoord/J20002RotPuls
Orbit: OrbitCoord/RotPuls2J2000
SC: BasicOrbit/El2RV
SC: BasicOrbit/RV2El
SC: Ephem/LagrangePointsL1ToL5
SC: Ephem/PlanetPositionEMBarycenter

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