AERToNu:

Path: Orbit/OrbitCoord

% Converts semi-major axis, eccentricy and r to true anomaly.
 r and a must be in the same units. This only works for elliptical
 orbits.

 Type AERToNu for a demo.
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   Form:
   nu = AERToNu( a, e, r )
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   ------
   Inputs
   ------
   a   (1,1) Semi-major axis
   e   (1,1) Eccentricity
   r   (1,:) Position

   -------
   Outputs
   -------
   nu	(1,:) True anomaly (rad)

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Children:

Common: Graphics/Plot2D

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