Modification of Three Order Methods For Solving Satellite Orbital Equation in Elliptical Motion


In the present study, a modification for iterative methods of three order is presented by means of mean anomaly to calculate the values of E and e (true anomaly and eccentricity) respectively, for a planet in an elliptical orbit around the sun. We find that the improved methods converge to the true anomaly value E, solution with less iteration. The efficiency of the modified third order algorithms are examined on many cases of the values of M and e. It is observed that methods are more efficient than third order methods presented by Weerakoon [1], Homerier [2] and Ababneh [3] and classical Newton's method.