基于Terminal 滑模的高超声速飞行器姿态控制

针对高超声速飞行器六自由度再入模型,考虑模型参数不确定和外界干扰对再入姿态控制的影响,基于Terminal滑模对再入过程中姿态角的跟踪控制问题进行研究.为了减少外界高频噪声对系统性能的影响,首先,利用多时间尺度技术将姿态模型划分为双环结构;然后,分别针对各环路设计Terminal滑模控制器,并通过Lyapunov理论和奇异摄动理论对系统的稳定性进行证明.仿真结果表明,对于六自由度再入模型,该控制方法能够很好地跟踪再入制导指令.

Hypersonic vehicle attitude control using Terminal sliding mode control

For the 6-DOF reentry model of hypersonic vehicles in the presence of bounded external disturbances and plant
uncertainties, the control problem of attitude tracking is investigated by using the terminal sliding mode method. In order to
reduce the effect from the external high-frequency noise in the practical application, the attitude model is divided into a two-
loop structure based on the method of the multiple time scale firstly. Then Terminal sliding mode controllers are designed for
each of loops. Stability of the system is presented based on the Lyapunov analysis. Finally, the simulation results show the
effectiveness of the proposed controller to track the guidance instruction for the 6-DOF model of hypersonic reentry vehicles.