Orbital Inclination of Satellite

Abstract

Equations are derived which govern the rate of change of the inclination of a satellite orbit to the equator of an planet. It is shown that if the motion of the satellite’s ascending node on the equator plane has a period which is short as compared to with the planet precession period then the satellite’s orbit will maintain a constant inclination to plane’s equator. This criterion is satisfied by many satellite orbit in the soldar system. These include all satellite whose orbit planes lie in the planet’s equator planes.