Research On Design And Station Keeping Method Of Non-Kepler Geostationary Orbit Based On Continuous Low Thrust

Because of its wide coverage,strong maneuverability and long orbital life,the geostationary orbit plays an important role in communications,navigation and meteorology.Since the number of satellites that can be placed in the geostationary orbit is limited,as the geostationary satellites continue to launch,the geostationary orbit will gradually become congested.In order to solve the problem of the gradual congestion of the geostationary orbit,this paper designs a displaced geostationary orbit.By using a continuous low thrust to the geostationary satellite,make the satellite move out of the original geostationary orbit and form a new geostationary orbit.In this paper,the displaced geostationary orbit is taken as the main research object,and the continuous low thrust is used as the propulsion system of the satellite to design the orbit.The performance and orbital life of the displaced geostationary orbit using the continuous low thrust are studied.In addition,the perturbation factors of displaced geostationary satellite using continuous low thrust are analyzed,and the corresponding orbit keeping strategy is designed to eliminate the influence of perturbation factors on the satellite.Firstly,this paper introduces the main frame and dynamic orbit model that are used in the case of measuring orbit and building models.Then the basic concepts and related models of displaced geostationary orbit are researched in order to provide theoretical support for the follow-up work.Secondly,in order to show the advantages of continuous low thrust propulsion in designing the displaced geostationary orbit,the design methods of the displaced geostationary orbit using traditional chemical propulsion and electric propulsion are studied.Simultaneously,using simulations to verify whether the performance and the orbital life of the displaced geostationary orbit using these two propulsion strategies can meet the design requirements or not.Furthermore,the displaced geostationary orbit is designed by using the hybrid propulsion strategy of solar sail and electric propulsion.The basic principles of solar sail propulsion and hybrid propulsion are introduced in detail,and the design method of displaced geostationary orbit using hybrid propulsion is studied.Through simulation analysis,analyzing and comparing the performance of orbital life and quality of displaced geostationary orbit in order to verity the feasibility and superiority of hybrid propulsion strategy.At the same time,the perturbation factors of displaced geostationary satellite are researched,and corresponding orbit keeping strategies are designed to eliminate the influence of perturbation factors according to the characteristics of hybrid propulsion strategy.Finally,in order to reduce the propellant loss of the satellite and improve the life of the satellite,a spring-autumn seasonal transfer orbit is designed.Using optimal control theory to analyze the most fuel-saving problems in the seasonal transfer orbit,and verifing the actual effect of the seasonal transfer orbit by simulation.