Path: Interplanetary/LowEnergyManeuver
% Transfer a LET from the restricted 3BP to the Sun/Planet/Moon 4BP
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Form:
[elementsNew,dV1EphNew,dtNew,exitflag] = Targeting4BP(elements,dV1Eph,
dtTarg,et,p,jDate,muPlanet)
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Inputs
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elements (1,6) Ecliptic orbital elements of the initial state
dV1Eph (1,1) Magnitude of the initial burn
dtTarg (1,1) Transfer time
et (1,1) Seconds after the Epoch at which the transfer
is initiated
p (1,1) Distance from the moon to L2
jDate (1,1) Julian date
muMoonMultiplier (1,1) 0 to 1, parameter to ease between 3BP and 4BP
muPlanet (1,1) Gravitational parameter of the planet
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Outputs
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elementsNew (1,6) Converged ecliptic orbital elements
dV1EphNew (1,1) Converged maneuver magnitude
dtNew (1,1) Converged transfer time
exitflag (1,1) 1 if successful
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Interplanetary: Ephemeris/PlanetPositionEMBarycenter Interplanetary: LowEnergyManeuver/CheckForOptimizationToolbox Interplanetary: LowEnergyManeuver/PlotLET Interplanetary: LowEnergyManeuver/Propagate4BP SC: BasicOrbit/El2RV Common: Database/Constant Math: Linear/Mag Math: Linear/Unit
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