Abstract
Precise position keeping of a geostationary satellite using an electric propulsion system is investigated in this paper. Analytical mean orbital elements of the satellite which represent a long-term motion of the satellite by perturbation forces such as the gravitational effects of the earth’s oblateness, the sun, and the moon, and the solar pressure force are introduced. Then, a control law of the position keeping by using the analytical mean orbital elements is derived where four electrical thrusters are assumed and the control forces are properly distributed into the thrusters. The effectiveness of the proposed control law is demonstrated by numerical simulations.
