El2RV:

Path: SC/BasicOrbit

% Converts orbital elements to r and v for an elliptic orbit.

   Type El2RV for a demo.
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   Form:
   [r, v] = El2RV( el, tol, mu )
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   ------
   Inputs
   ------
   el    (6,:)  Elements vector [a;i;W;w;e;M]           (angles in radians)
   tol   (1,1)* Tolerance for Kepler's equation solver. (default = 1e-14)
   mu    (1,1)* Gravitational constant.                 (default = 3.9860044e5)

   -------
   Outputs
   -------
   r     (3,:)  position vector
   v     (3,:)  velocity vector

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   References:	Battin, R.H., An Introduction to the Mathematics and 
              	Methods of Astrodynamics, p 128.
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Children:

Common: General/DispWithTitle
OrbitMiniToolbox: Support/CP2I
OrbitMiniToolbox: Support/M2Nu

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