Research On Satellite Attitude Control Based On Backstepping

Satellite attitude stabilization control is widely concerned by scholars.Although many feedback control design methods have been proposed and applied to attitude stabilization control,there are still some problems need to be solved.For example,the nonlinear problem of spacecraft attitude kinematics and dynamics,the external disturbance rejection control of spacecraft.In addition,the problem of the uncertainty of the moment of inertia,which is caused by the motion of the payload,the rotation of the solar array and the fuel consumption,will make the attitude control more and more complicated.Actuator Constraints and faults are the practical problems in satellite attitude control.Because the backstepping control method with the complex nonlinear system is divided into several subsystems and a controller design procedure is simple and other advantages,it has strong processing ability for nonlinear systems with triangular structural characteristics.On the other hand,the two subsystems of spacecraft attitude kinematics and dynamics constitute a nonlinear attitude control system,so backstepping can be used to design satellite attitude controller.Based on backstepping theory,this paper discusses the method of satellite control.Specific research contents are as follows:(1)Firstly,the rigid body satellite with unknown bounded disturbance and uncertainty of inertia,a class of controller is designed by backstepping,The method is combined with the adaptive control theory and the Lyapunov method is used to prove the stability of the satellite attitude system.Simulation results demonstrate the effectiveness of the proposed method.(2)Secondly,on the basis of the above problems,in this section,further consideration such as actuator constraints is given to the rigid satellite.A backstepping attitude controller based on modified Rodrigo parameters is proposed.This method is simple and can realize the effective and stable control of satellite attitude.A large number of numerical simulations demonstrate the effectiveness of the proposed method.(3)A satellite attitude control method is proposed for the rigid body satellite under external disturbance and actuator constraints.Firstly,the observer is designed to realize the actuator fault estimation,and then the backstepping controller is designed by using the estimated information,and the effectiveness of the method is verified by numerical simulation.(4)A nonlinear satellite attitude control method based on backstepping is proposed for the flexible satellite with actuator constraints and unknown external disturbances.The proposed controller is sufficient to guarantee the asymptotic stability of the attitude and the angular velocity in the presence of unknown attachments,and the simulation results further demonstrate the effectiveness of the proposed scheme.