M2EHy:

Path: Orbit/OrbitMechanics

% Eccentric anomaly for a hyperbola.
   Computed from the mean anomaly and the eccentricity. 
   This uses Kepler's method to iterate on the solution

   For a demo plot use  M2EHy( e ).

--------------------------------------------------------------------------
   Form:
   eccAnom = M2EHy( e, meanAnom, tol, nMax )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   e             (1,:)  Eccentricity
   meanAnom      (1,:)  Mean anomaly
   tol           (1,1)  Tolerance
   nMax          (1,1)  Maximum number of iterations

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

--------------------------------------------------------------------------

Children:

Common: Graphics/Plot2D

---

Back to the Orbit Module page