Path: Interplanetary/LowEnergyManeuver
% Propagate the CRTBP initial state to the next perigee.
Type PropagateCRTBPToPeriapse to see a demo of a stored orbit family.
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Form:
[yF, tF] = PropagateCRTBPToPeriapse(y,t0,tF,mu)
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Inputs
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y (6,1) Current state vector [r;v] (coordinates are
centered at the secondary body)
t0 (1,1) Initial time
tF (1,1) Upper bound on final time
mu (1,1) CRTBP mass ratio
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Outputs
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yF (6,1) State at the periapse
tF (1,1) Time at the periapse
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Interplanetary: LowEnergyManeuver/PropagateCRTBP Interplanetary: LowEnergyManeuverData/f26pRef Common: Graphics/Plot2D Math: Linear/Mag
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