GetHillsMats:

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   This function takes the position and velocity of a satellite in the ECI 
   frame, and returns the A and Adot matrices used for transformation to 
   the Hills frame. They are used in the following equations:

   rH = A*(r1-r0);
   vH = A*(v1-v0) + Adot*(r1-r0);

   Since version 7.
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   Form:
   [A, Adot] = GetHillsMats( r0, v0 )
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   ------
   Inputs
   ------
   r0      (3,1)   Position ECI frame
   v0      (3,1)   Velocity ECI frame

   -------
   Outputs
   -------
   A       (3,3)   Rotation matrix (position)
   Adot	(3,3)   Rotation matrix (velocity)
                   Equal to -Cross( OrbRate(Mag(r0), A )

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Children:

Math: Linear/Cross
Math: Linear/Mag
SC: BasicOrbit/RV2El