Path: Interplanetary/LowEnergyManeuver
% Transfer a CRTBP LET to the restricted 3 body, non-planar problem.
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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 (1,1) Magnitude of the initial burn
dt (1,1) Transfer time
et (1,1) Seconds after the Epoch at which the transfer
is initiated
muMoon (1,1) Gravitational parameter of the Moon
jDate (1,1) Julian date
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Outputs
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elementsNew (1,6) Converged ecliptic orbital elements
dV1EphNew (1,1) Converged maneuver magnitude
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