利用姿态机动的绳系卫星编队系统轨道协同控制

In order to solve the tether libation problem of the tethered satellite formation system during orbit maneuvering, a control algorithm is proposed to realize orbit tracking of the formation system by adjusting the thrust direction of the leader satellite. Due to the coupling between the thrust direction angle and state variables, and the number of control inputs is less than the degree of freedom of the system, orbit cooperative control is a typically non-affine underactuated control problem. Firstly, the angular velocity is used as the virtual control input by the step-up method; then, the high-level sliding surface and the equivalent control input law are obtained by designing the sub-sliding surface after weighting for each subsystem, and an observer is designed to estimate the nonlinear term of the system. Secondly, switching control law of the higher-level sliding mode surface is obtained by model predictive control algorithm. Finally, the effectiveness of the proposed control algorithm is verified by MATLAB/Simulink.