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SUPPORT SITE |
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SUPPORT SITE |
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Path: Orbit/LowEnergyManeuver
% Transfer a CRTBP LET to the restricted 3 body, non-planar problem.
Since version 9.
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Form:
[elementsNew,dV1EphNew] = Targeting3BP2(elements,dV1Eph,dt,et,muMoon);
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Inputs
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elements (1,6) Ecliptic orbital elements of the initial
state
dV1Eph (1) Magnitude of the initial burn
dt (1) Transfer time
et (1) Seconds after the Epoch at which the transfer
is initiated
muMoon (1) Gravitational parameter of the Moon
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Outputs
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elementsNew (1,6) Converged ecliptic orbital elements
dV1EphNew (1) Converged maneuver magnitude
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Common: Database/Constant Math: Linear/Mag Math: Linear/Unit Orbit: LowEnergyManeuver/CheckForOptimizationToolbox Orbit: OrbitCoord/J20002RotPuls Orbit: OrbitSim/Propagate3BP SC: BasicOrbit/El2RV SC: Ephem/PlanetPositionEMBarycenter
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