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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.
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Form:
LETTrans = LowEnergyEarthToMoonTransfer(jD,r0)
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Inputs
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jD (1) Julian Date of transfer
r0 (1) Initial circular orbit radius (km)
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Outputs
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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
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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.
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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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