Path: SC/Ephem
% Computes the moon orbital elements with respect to the earth inertial frame.
These elements are only valid for short term use. Use PlanetPosJPL
for more accurate positions and velocities.
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Form:
el = MoonEl( jD )
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Inputs
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jD (1,1) Julian Date
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Outputs
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el (1,6) Keplerian elements [a,i,L,w,e,M] (km,rad)
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Reference: Montenbruck, O., T. Fleger, "Astronomy on the Personal
Computer", Springer-Verlag, p 155.
http://ssd.jpl.nasa.gov/?sat_elem
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Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2T
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