Methods for numerical integration of equations of motion of stationary satellites.

A three step method of numerical integration for computing the orbital parameters of a stationary satellite is presented: (1) a coordinate system is established whose origin is at the satellite point, thereby eliminating gravity and centrifugal force on the satellite from the equations, (2) perturbation on the satellite caused by tesseral harmonics of the earth potential are computed, and (3) the equations are numerically integrated using a series which eliminates terms of order 3 through 11. Attention is given to the simplification of computer programming steps.