An electric propulsion satellites in geostationary orbit position holding method

The present invention relates to a static orbit satellite position holding method, and particularly relates to an electric propulsion stationary orbit satellite position holding method belongs to technical field of satellite orbit control. Four electric propulsion thruster system mounted in the four directions of the northwest, northeast, southwest and southeast satellite back floor, four thrusters with respect to the satellite center of mass of the tangential and normal to the same distance, and a thrust direction by the satellite center of mass. A position holding period determined by the orbital period of the day and two-day little n control cycles, a small four cycle control thrusters are turned on, while controlling orbit inclination angle, flat longitude drift rate and eccentricity. Solve the geostationary satellite position-electric propulsion system remains a problem.