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SUPPORT SITE |
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SUPPORT SITE |
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Path: Orbit/LowEnergyManeuver
% Obtain a refined maneuver magnitude for transferring an orbit from the
3BP to the Sun/Planet/Moon 4BP
Since version 9.
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Form:
[elementsNew,dV1EphNew,dtNew,exitflag] = Targeting4BPB(elements,dV1Eph,dtTarg,et,p,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
dtTarg (1) Transfer time
et (1) Seconds after the Epoch at which the transfer
is initiated
p (1) Distance from the moon to L2
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
dtNew (1) Converged transfer time
exitflag (1) 1 if successful
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Common: Database/Constant Math: Linear/Mag Math: Linear/Unit Orbit: LowEnergyManeuver/CheckForOptimizationToolbox Orbit: OrbitSim/Propagate4BP SC: BasicOrbit/El2RV SC: Ephem/PlanetPositionEMBarycenter
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