Path: SC/Ephem
% Generate the moon vector in an earth or spacecraft centered frame.
The earth-centered inertial frame is default or, if a spacecraft vector is
input, the vector is in the spacecraft centered frame.
This is the low precision model.
See also MoonV2.
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Form:
[u, r] = MoonV1( jd, rSc )
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Inputs
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jd (:) Julian date
rsc (:) Spacecraft vector in the ECI frame (km)
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Outputs
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u (3,:) Unit moon vector
r (:) Distance from origin to moon (km)
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References: The 1993 Astronomical Almanac, U.S. Government Printing
Office, p. D46.
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Common: Time/DTSToDTA Common: Time/Date2JD Math: Linear/Mag Math: Linear/Unit Math: Trigonometry/CosD Math: Trigonometry/SinD
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