Multi-satellite Distributed Attitude And Orbit Integrated Coodinated Control

With the continuous development of spacecraft technology,a single spacecraft cannot meet the needs of complex missions.Therefore,space mission carriers have gradually developed to multiple spacecraft,and a distributed formation system has emerged.At the same time,in order to ensure high-precision synchronized attitude tracking and formation maneuvers in specific formation missions,overall attitude and orbital motion must be modeled and controlled.This thesis studies the distributed multi-satellite attitude and orbit integrated coordinated control problem,mainly including the following content.First,the relative kinematics and dynamics model of multi-satellite attitude and orbit coupling is established based on the dual quaternion theory.Combining the theory of consensus cooperative control with dual quaternion,and based on the multi-satellite relative motion model,a distributed multi-satellite synchronous cooperative control method is proposed,which brings the desired state and expands to the multi-satellite tracking cooperative control.When all the slave spacecraft exchange information with the master spacecraft,it will bring a great burden to the communication system.Therefore,assuming that only some spacecraft can obtain the desired state,a fixed-time sliding mode observer is designed to estimate the desired state.Furthermore,a sliding mode controller is designed to carry out attitude-orbit coupling and coordinated control of the satellite formation.Based on Lyapunov,it is proved that the estimator can make the estimation error converge to zero at a fixed time,and the stability of the controller is proved.Aiming at the problem that the finite time control convergence time is affected by the initial state,a multi-satellite attitude orbit coupled fixed-time cooperative controller is proposed.This controller is established based on the directional communication topology.Furthermore,an adaptive control rate is designed when the upper bound of external interference is unknown.The Lyapunov function is used to testify the stability of the controller.Finally,through numerical simulation,the feasibility of the above estimator and controller is verified.