基于LMI的高超声速飞行器滑模预测控制  

Sliding mode predictive control for the hypersonic vehicle based on LMI

作　　者：高海燕[1] 蔡远利[2] 唐伟强[3] 

机构地区：[1]厦门理工学院福建省高电压技术重点实验室,福建厦门361024 [2]西安交通大学电子与信息工程学院,陕西西安710049 [3]兰州理工大学电气工程与信息工程学院,甘肃兰州730050

出　　处：《飞行力学》2016年第5期49-53,共5页Flight Dynamics

基　　金：国家自然科学基金资助(61308120;61463029);厦门理工学院高层次人才项目资助(YKJ15022R)

摘　　要：针对高超声速飞行器非线性、多约束、快时变等特点,提出了一种基于线性矩阵不等式的滑模预测控制方法。首先设计系统的滑模面,然后对滑模面进行预测并将其作为优化性能指标,通过Schur补引理将控制律的设计转化为一个优化问题。该方法避免了常规滑模控制的高频切换,有效地克服了抖振现象。此外,相对于传统的滑模预测控制方法,该方法不需要额外计算终端约束条件和终端代价函数,只需要通过选取合适的李雅普诺夫函数即可保证系统的稳定性,且其加权矩阵和控制律是同时进行优化设计的,简化了设计过程。仿真试验表明,相比于单纯的预测控制和滑模控制,所提出的方法具有更好的跟踪性能。Considering the nonlinearity,multiple constraints and fast time-varying of hypersonic vehicle,we proposed a sliding mode predictive control strategy based on the linear matrix inequalities（ LMIs）.The sliding mode surface was designed first,and then it was predicted and regarded as the performance index. By using the Schur complement lemma,the design of the control law was converted to an optimization problem. Therefore,the frequent switching on the sliding surface was avoided and the chattering was suppressed. In addition,compared with the traditional sliding mode predictive control,the method does not need to calculate terminal constraints and terminal cost function additionally,and it only needs to choose suitable Lyapunov function to guarantee the stability of the system. And the weighted matrix and the control law are optimized simultaneously,which simplifies the design process. Simulations show that compared with the pure model predictive control and the sliding mode control,the proposed method has better tracking performance.

关 键 词：线性矩阵不等式 滑模预测控制 渐近稳定 高超声速飞行器 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]