Maneuver Planning of Geostationary Satellites Using Mean Orbital Elements

On the one hand, the satellite will deviate from its current orbit gradually, on the other hand, it will cause the satellite's motion to oscillate periodically. Generally speaking, the orbit maneuver of satellite is to adjust the average trend of its space motion to make its space position meet the requirements of load application at least for a period of time. The oscillation of satellite orbit elements changes in real time. Therefore, in order to realize precise maneuver planning, the amplitude of orbital elements oscillation before and after maneuver must be considered. The calculation of this amplitude is not simple and accurate. There are usually two methods, numerical method and analytical method. The cost of numerical method is very high, especially in the planning of complex maneuvering process, large-scale optimization solution requires multiple calculation of amplitude. Aiming at geostationary satellite (one of the most widely used satellite types), this paper uses an analytical method to calculate the amplitude of the satellite to realize the high-precision planning of the average motion of the satellite. The complex satellite maneuver planning problem is transformed into the boundary constraint optimization problem, and then solved by a simple and universal method. The simulation results verify the feasibility and accuracy of the proposed method for geostationary satellite maneuver planning.