MoonV1:

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
   ------
   jd        (:)     Julian date
   rsc       (:)     Spacecraft vector in the ECI frame (km)

   -------
   Outputs
   -------
   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. 
--------------------------------------------------------------------------

Children:

Common: Time/DTSToDTA
Common: Time/Date2JD
Math: Linear/Mag
Math: Linear/Unit
Math: Trigonometry/CosD
Math: Trigonometry/SinD

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