MoonV2:

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 moderate precision model. 
   See also MoonV1.

   Since version 1.
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   Form:
   [u, r] = MoonV2( 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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Children:

Common: Time/Date2JD
Math: Linear/Mag
Math: Linear/Unit

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