GetLVLHMats:

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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 LVLH frame. They are used in the following equations:

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

   Since version 7.
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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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Children:

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