RToNu:

Path: Orbit/OrbitCoord

% Computes true anomaly from semi-major axis, eccentricity and radius.
 a and r must be in the same units.

 Type RToNu for a demo of an elliptic orbit.
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   Form:
   nu =  RToNu( a, e, r )
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   ------
   Inputs
   ------
   a     (1,1)  Semi-major axis
   e     (1,1)  Eccentricity
   r     (1,:)  Radius

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

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Children:

Common: Graphics/Plot2D
Math: Linear/Mag
Orbit: OrbitMechanics/RVOrbGen

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