Path: Orbit/LowEnergyManeuver
% Keplerian Energy with respect to the Moon.
This calls InterpolateState and PlanetPositionEMBarycenter that must be
initialized prior to use. For example:
InterpolateState([],[],'bin2000.405')
PlanetPositionEMBarycenter('initialize',[0 3 10]);
EnergyWRTMoon( 0, zeros(6,1), 4.9028e+03, JD2000 );
You must call PlanetPositionEMBarycenter with [0 3 10] on initialize.
(Sun, Earth Moon)
Type EnergyWRTMoon for a demo.
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Form:
e = EnergyWRTMoon( t, y, muMoon, jDate )
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Inputs
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t (1,1) Seconds after epoch (s)
y (6,1) State vector in Earth/Moon Barycentered frame
muMoon (1,1) Gravitational Parameter of the moon
jDate (1,1) Julian date
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Outputs
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e (1,1) Keplerian energy (MJ)
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SC: Ephem/CEcl2Eq SC: Ephem/InterpolateState SC: Ephem/PlanetPosJPL SC: Ephem/PlanetPositionEMBarycenter SC: SCData/bin2000 Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2000 Math: Linear/Mag
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