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Path: Orbit/LowEnergyManeuver
% Keplerian Energy with respect to the Moon Since version 9. -------------------------------------------------------------------------- Form: e = EnergyWRTMoon(t,y,moon,planet,muMoon); -------------------------------------------------------------------------- ------ InputsP ------ t (1) Seconds after epoch y (1) State vector in Earth/Moon Barycentered frame muMoon (1) Gravitational Parameter of the moon ------- Outputs ------- e (1) Keplerian energy --------------------------------------------------------------------------
Math: Linear/Mag SC: Ephem/PlanetPositionEMBarycenter
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