M2E:

Path: Orbit/OrbitMechanics

% Computes the eccentric anomaly
 from the mean anomaly and the eccentricity.

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   Form:
   eccAnom  = M2E( e, meanAnom, tol, nMax )
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   ------
   Inputs
   ------
   e            (1,:)    Eccentricity
   meanAnom     (1,:)    Mean anomaly (rad)
   tol          (1,1)    Tolerance
   nMax         (1,1)    Maximum number of iterations

   -------
   Outputs
   -------
   eccAnom     (1,:)     Eccentric anomaly (rad)

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Children:

Orbit: OrbitMechanics/M2EEl
Orbit: OrbitMechanics/M2EHy
Common: Graphics/Plot2D
Math: Linear/DupVect

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