El2RV:

Path: Orbit/OrbitCoord

% Converts orbital elements to r and v for an elliptic orbit.
 Type El2RV for a demo. The Keplerian elements are defined as:

 * a is semi-major axis (km)
 * i is inclination (rad)
 * W is right ascension of the ascending node (rad) 
 * w is argument of perigee (rad)
 * e is argument of perigee
 * M is mean anomaly

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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 = 3.98600436e5)

   -------
   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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 See also: RV2El, RVFromKepler
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Children:

Orbit: OrbitCoord/CP2I
Orbit: OrbitMechanics/M2Nu
Common: General/DispWithTitle

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