Position keeping method of electric propulsion stationary orbit satellite

The invention relates to a position keeping method of a stationary orbit satellite, particularly to a position keeping method of an electric propulsion stationary orbit satellite, and belongs to the technical field of the orbit control of a satellite. Four thrusters of an electric propulsion system are mounted at the northwest, the northeast, the southwest and the southeast of the satellite back floor. For the four thrusters, the tangential distances and the normal distances relative to a satellite centroid are the same, and the thrust directions pass through the satellite centroid. A position keeping period comprises a one-day orbit determining period and n two-day small control periods, wherein the four thrusters in one small control period are respectively started, and at the same time, the orbit inclination, the flat longitude drifting ratio and the eccentricity ratio are controlled. The position keeping method disclosed by the invention solves the problem of the position keeping of the stationary orbit satellite of the electric propulsion system.