A Calculating Method for Epicyclic Motion of Spacecraft

The analytic formulations are presented of the epicyclic motion of a spacecraft about the true anomaly and the eccentric anomaly. The eccentric anomaly as a function of time is calculated by the iterative method. And the iteration's convergence-condition is discussed. The relationship between the true anomaly and the time is gotten by the numerical integral method. The numerical simulation's results of this approach are presented.