CAJ | 학술논문

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.
침대고초성속비행기륙자유도재입모형,고필모형삼수불학정화외계간우대재입자태공제적영향,기우Terminal활모대재입과정중자태각적근종공제문제진행연구.위료감소외계고빈조성대계통성능적영향,수선,이용다시간척도기술장자태모형화분위쌍배결구;연후,분별침대각배로설계Terminal활모공제기,병통과Lyapunov이론화기이섭동이론대계통적은정성진행증명.방진결과표명,대우륙자유도재입모형,해공제방법능구흔호지근종재입제도지령.
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.