GetLVLHMats:

Path: FormationFlying/Coord

% Generate LVLH transformation matrices
 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 LVLH frame.
 They are used in the following equations:

   rL = A*(r1-r0);
   vL = A*(v1-v0) + Adot*(r1-r0);

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   Form:
   [A, Adot] = GetLVLHMats( ro, vo )
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   Inputs
   ------
   ro              (3,1) r, ECI frame
   vo              (3,1) v, ECI frame

   -------
   Outputs
   -------
   A               (3,3) Rotation matrix (position)
   Adot            (3,3) Rotation matrix (velocity)
                           Equal to -cross( orbrate(mag(ro), A )

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