Path: LunarMissions/LunarEphemeris
% Computes a polar lunar orbit
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Form:
x = LunarPolarOrbit( a, e, jD )
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Inputs
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a (1,1) Semi-major axis
e (1,1) Eccentricity
jD (1,1) Julian date
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Outputs
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x (6,1) [r;v] (km,km/s) ECI
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