E2Nu:

Path: SC/BasicOrbit

% Computes the true anomaly from the eccentric or hyperbolic anomaly.

   Since version 1.
--------------------------------------------------------------------------
   Form:
   nu = E2Nu( e, E )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   e             (1,:)   Eccentricity
   E             (1,:)   Eccentric or Hyperbolic anomaly

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

--------------------------------------------------------------------------
   References:   Bate, R. R., Fundamentals of Astrodynamics. pp. 20-40.
--------------------------------------------------------------------------

Children:

Common: Graphics/Plot2D
Math: Linear/DupVect

Back to the SC Module page