MeanAnom:

Path: Orbit/OrbitMechanics

% Computes the mean anomaly from change in time

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   Form:
   M = MeanAnom( dt, a, p, mu )
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   ------
   Inputs
   ------
   dt                   Change in time
   a                    Semi-major axis (+ for ellipse, inf for parabola
                        and - for hyperbola)
   p                    Parameter (used for parabolas)
   mu                   Gravitational parameter

   -------
   Outputs
   -------
   M                    Mean anomaly

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   References: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
               pp. 56-57.
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Children:

Common: Graphics/Plot2D

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