Mean Orbital Elements for Geosynchronous Orbit - I - Semi-major, eccentricity, and longitude of perigee

Abstract

The mean orbital elements for geosynchronous satellite are developed in terms of non-singular orbital elements. The true satellite position oscillates about the position calculated from the mean elements due to short period perturbations to the satellite motion. the displacement of a geostationary satellite from this mean orbit position is less than 1800m. The mean elements of ec and es are obtained.