Abstract

A method of stationkeeping for a three-axis stabilized satellite having four thrusters mounted in a generally rectangular configuration on an anti-nadir face of the satellite, each of the four thrusters having a line of thrust which passes through the center of mass of the satellite, the four thrusters including a northwest thruster, a northeast thruster, a southwest thruster, and a southeast thruster. The method includes the step of rotating the satellite about a pitch axis that is perpendicular to a normal to the anti-nadir face of the satellite. The northwest thruster and the northeast thruster are canted away from the anti-nadir face in a north direction with respect to a north-south axis which passes through the center of mass of the satellite. The southwest thruster and the southeast thruster are canted away from the anti-nadir face in a south direction with respect to the north-south axis. The northeast thruster and the southeast thruster are slewed in an east direction about the north-south axis and the northwest thruster and the southwest thruster are slewed in an west direction about the north-south axis. Next, the northeast thruster and the northwest thruster are fired near an orbit ascending node and the southeast thruster and the southwest thruster are fired near an orbit descending node, wherein each of the four thrusters is fired in accordance with the amount that the satellite is rotated about the pitch axis.

Other References

• Anzel, Bernard M., "Controlling a Stationary Orbit Using Electric Propulsion," DGLR/AIAA/JSASS 20th International Electric Propulsion Conference, W. Germany, Oct. 3-6, 1988, pp. 1-