Attitude Coordination Control Of Satellite Formation And Its Optimization Design

Attitude cooperative control in satellite formation flight is an important factor that affects the success of formation space mission.Whether through satellite formation to achieve target observation,navigation or guidance of imaging tasks,are needed between each satellite satellite formation in the coordinated attitude,through consistent attitude to complete the task space.Therefore,it is of important theoretical and practical significance to study the attitude cooperative control of satellite formation flying.People gradually concentrate to the problem of the optimal coordination control of satellite formation,because the orbit satellites in the implementation of space missions in the process,often need to gesture to achieve the desired attitude or to achieve stability In the process of maneuvering should also set the corresponding performance indicators to achieve the optimal extreme,such as the least loss of fuel or the minimum integration time.With the obvious advantages and broad prospects for the development of satellite formation attitude optimal coordination control technology,its implementation and improved technology are subject to the various experts in the relevant areas of widespread concern.In this paper,the optimal control theory and the integral sliding mode control theory are combined.Based on the nonlinear control model,the SDRE controller is designed for the attitude control of satellite formation.Based on the linearized model,LQR controller is also designed for the attitude control of satellite formation.The optimal sliding mode controller is designed on the basis of uncertain nonlinear model.The main contents of this paper are as follows:Firstly,the attitude control model of satellite formation is established by introducing the relative attitude difference on the basis of the single satellite model.On the basis of this nonlinear model,a pseudo-linear model of state correlation coefficient is proposed.The satellite formation attitude cooperative model is transformed into the design of SDRE controller and the design of linearized approximate model for LQR controller.Secondly,the design of the optimal controller for satellites formation attitude is presented.Then,the optimal control methods of LQR and SDRE are introduced and their stabilization has been proved.According to these two optimal control methods,design the corresponding controller.The design of the corresponding control algorithm,that is,the design of the satellite formation of the attitude of the optimal controller.Finally,with three satellite formation as an example,the design of the two controllers were simulated and analyzed.Finally,the design of the optimal sliding mode controller for satellite formation attitude is presented.The nonlinear system model is described,which consists of two parts: nominal system and uncertainty.The basic principles ?-D method and integral sliding mode method are introduced respectively.When the uncertainty term is 0,the attitude-based cooperative optimal controller is designed based on the ?-D method for the nominal system.When the uncertain term is not 0,the attitude cooperative optimal sliding mode controller based on the integral sliding mode method is designed.Finally,the controller of this chapter is simulated and analyzed.