Path: Interplanetary/LowEnergyManeuver
% Compute a ballistic lunar capture trajectory from a circular Earth orbit
From circular trajectory about Earth with a radius of r0 to a weakly captured
lunar orbit.
Requires the Optimization Toolbox.
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Form:
[LETTrans,debugData] = 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
debugData
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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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See also: LowEnergyTransferInCRTBP, LETPhasing, Targeting3BP2
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Interplanetary: Ephemeris/PlanetPositionEMBarycenter Interplanetary: LowEnergyManeuver/CRTBP2kms Interplanetary: LowEnergyManeuver/CheckForOptimizationToolbox Interplanetary: LowEnergyManeuver/J20002RotPuls Interplanetary: LowEnergyManeuver/LETPhasing Interplanetary: LowEnergyManeuver/LowEnergyTransferInCRTBP Interplanetary: LowEnergyManeuver/MinE4BP Interplanetary: LowEnergyManeuver/PlotLET Interplanetary: LowEnergyManeuver/PlotLET3BP Interplanetary: LowEnergyManeuver/RotPuls2J2000 Interplanetary: LowEnergyManeuver/Targeting3BP2 Interplanetary: LowEnergyManeuver/Targeting4BP SC: BasicOrbit/El2RV SC: BasicOrbit/RV2El SC: Ephem/LagrangePointsL1ToL5 Common: Database/Constant Common: Time/JD2000 Math: Linear/Mag
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