基于Terminal滑模的高超声速飞行器姿态控制  

Hypersonic vehicle attitude control using Terminal sliding mode control

作　　者：韩钊[1] 宗群[1] 田柏苓[1] 吉月辉[1] 

机构地区：[1]天津大学电气与自动化工程学院,天津300072

出　　处：《控制与决策》2013年第2期259-263,268,共6页Control and Decision

基　　金：国家自然科学基金项目(91016018);教育部科学技术研究重大项目(311012);天津市基础研究重点项目(11JCZDJC25100)

摘　　要：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.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 twoloop 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.

关 键 词：高超声速飞行器 再入模型 TERMINAL滑模控制 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]