M2EApp:

Path: SC/BasicOrbit

% Approximate root to Kepler's Equation for elliptical and hyperbolic orbits.

   Since version 1.
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   Form:
   eccAnom = M2EApp( e, meanAnom )
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   ------
   Inputs
   ------
   e             (: or 1)  Eccentricity
   meanAnom      (:)       Mean anomaly

   -------
   Outputs
   -------
   eccAnom       (:)       Eccentric anomaly

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   References: Battin, R.H. (1987). An Introduction to the
               Mathematics and Methods of Astrodynamics, AIAA Press, p. 194.
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Children:

Common: Graphics/Plot2D
Math: Linear/DupVect

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