Nu2E:

Path: SC/BasicOrbit

% Converts true anomaly to eccentric or hyperbolic anomaly.
 For a demo plot use Nu2E( e ).

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   Form:
   E = Nu2E( e, nu )
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   ------
   Inputs
   ------
   e 	(1,:)  or (1,1) Eccentricity
   nu	(1,:)  True anomaly

   -------
   Outputs
   -------
   E   (1,:)  Eccentric or hyperbolic anomaly

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   References: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
   pp. 57,60.
--------------------------------------------------------------------------

Children:

Common: Graphics/Plot2D
Math: Linear/DupVect

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