RAEToM:

Path: Orbit/OrbitMechanics

% Computes m, nu and E from r, a and e.

   Type RAEToM for a demo

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   Form:
   [m, nu, E] = RAEToM( r, a, e )
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   ------
   Inputs
   ------
   r          (1,1) Orbit radius
   a          (1,1) Orbit semi-major axis
   e          (1,1) Orbit eccentricity

   -------
   Outputs
   -------
   m          (1,1) Mean anomaly (rad)
   nu         (1,1) True anomaly (rad)
   E          (1,1) Eccentrci anomaly (rad);

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Children:

Orbit: OrbitMechanics/Nu2M

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