作　　者： (蒋恒）; (管萍）; (戈新生）;

机构地区： 北京信息科技大学自动化学院

出　　处： 《北京信息科技大学学报（自然科学版）》 2017年第4期29-34,共6页

摘　　要： 针对具有高度非线性、强耦合、含较大不确定性特点的高超声速飞行器,设计了快速终端滑模控制器并应用于高超声速飞行器的姿态控制中。对飞行器姿态控制系统的慢回路设计PID控制律,快回路设计快速终端滑模控制律。快速终端滑模控制对系统参数的变化不灵敏,具有良好的鲁棒性和快速性。利用李雅普诺夫稳定性理论证明了整个闭环系统的稳定性。仿真结果表明,在气动参数大范围摄动的情况下,该控制系统对于高超声速飞行器姿态角信号指令具有良好的跟踪性能。 A fast terminal sliding mode controller is applied to the attitude control of hypersonic vehicle,which has the problem of high nonlinearity,strong coupling and large uncertainty. The PID control law is designed for the slow loop of the aircraft attitude control system,and the fast terminal sliding mode control law is designed for the fast loop. The fast terminal sliding mode control is not sensitive to the parameters of the system,and has good robustness and rapidity. The stability of the closed-loop is proved by the Lyapunov theory. The simulation results show that this control system has good tracking performance for the desired attitude angle of hypersonic vehicles,in the case of wide perturbation of aerodynamic parameters.

关 键 词： 高超声速飞行器 气动参数 不确定性 快速终端滑模控制 姿态控制