GEO satellite collision avoidance maneuver strategy against inclined GSO satellite

Abstract

Orbit maneuver strategy for Geostationary Earth orbit (GEO) satellite is investigated to keep away from inclined geosynchronous orbit (GSO) satellite. Characteristics of inclined GSO with various combinations of eccentricity and argument of perigee are examined first. Then the close approach of inclined GSO SL-12 rocket body to GEO COMS satellite is inspected to develop a maneuver strategy for collision avoidance. Several sizes of delta-velocities are applied to the GEO satellite to check the effect of the maneuvers on separation. It is found that radial separation between the two satellites is the most important factor and the greatest separation can be achieved when the collision avoidance maneuver is executed at 12 hours before the time of closest approach. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.