Parametric multi-objective design for spacecrafts attitude control system with super flexible netted antennas

This paper investigates the attitude control problem of a satellite with super-large flexible appendages. Most of existing approaches on the vibration suppression and attitude control of flexible spacecraft are developed with a singleobjective. However, in control engineering practice the performance indices such as accuracy, convergence speed, stability, vibration suppression in flexible structures and robustness are required to be considered simultaneously, which leads to a typical multi-objective design problem. In this paper, a parametric multi-objective design method based on output feedback for robust pole placement is proposed for pitch channel attitude systems with very large flexible mesh antenna satellites. Firstly, necessary and sufficient conditions for the controllability and observability of the system are derived. Then the parametric expressions of the dynamic compensator and the eigenvector matrix are given. Based on this, the multi-objective optimization of the free parameter vector is carried out, so that the control system has: 1) poles which are assigned to the desired regions; 2) lower eigenvalue sensitivity; 3) stronger ability to suppress high-order unmodeled dynamics; 4) control gain as small as possible. Finally, the controller design and simulation verification are carried out according to the satellite engineering parameters. The simulation results show that the proposed method can outperform the traditional PID controller in terms of dynamic response, high-order unmodeled dynamic suppression capability and peak control. © 2019, Editorial Department of Control Theory & Applications South China University of Technology. All right reserved.