RVToMEq:

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   Transforms elements r and v to  modified equinoctial. 
   The modified equinoctial elements are

   p = a(1 + e^2)
   f = ecos(w + W);
   g = esin(w + W);
   h = tan(i/2)cosW
   k = tan(i/2)sinW
   L = W + w + nu

   W is right ascension of the ascending node
   w is argument of perigee

   Since version 7.
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   Form:
   x = RVToMEq( r, v, mu )
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   ------
   Inputs
   ------
   r              (3,1)  Position vector
   v              (3,1)  Velocity vector
   mu             (1,1)  Gravitational parameter

   -------
   Outputs
   -------
   x              (6,1)  Elements

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Children:

SC: BasicOrbit/RV2El
Sail: Coordinates/ElToMEq