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Switched control system for satellite formation configuration

In this paper formation configuration control of distributed satellites is studied based on continuous micro-thrust. The nonlinear model for the Leader/Follower relative position case is derived. A sliding mode relative position controller is designed based on the dynamic equations, which is proved to be able to eliminate the influence of J2-perturbation. As it is difficult to develop a globe control law for all the missions during the formation, a switching-mechanism is adopted according to the hierarchical architecture of the system. A supervisor in the upper layer controls the transition between the modes. Dwell time and safe mode are applied to ensure the stabilization of the switched system. Simulation results show that the switched system proposed in this paper can control configuration of the formation to desired patterns effectively and can still work even if the Leader satellite is malfunctioning.