CORRECTING METHOD FOR ARGUMENT OF PERIGEE WITH LONGITUDE CONTROL FOR SATELLITE ORBITING IN INCLINED ELLIPTIC GEOSYNCHRONOUS ORBIT

摘要

PROBLEM TO BE SOLVED: To provide a method for controlling an inclined elliptic orbit of a geostationary satellite, by maintaining a perigee position while simultaneously preventing a reference point on an orbit from being excessively away from a reference position over the Earth. SOLUTION: Execution of an orbit control changes a semimajor axis of the orbit, and causes drift velocity with respect to the Earth when purturbed away from a geosynchronous orbit value. A multiple maneuvers have to be executed to correct an argument of perigee and control the drift velocity so as to maintain a prescribed tolerance on a ground track position. A relationship between the maximum allowable velocity change and time between the maneuvers is determined by the correction needed for the argument of the perigee and an allowable movement of the reference point.