可变翼巡航导弹μ综合姿态控制系统设计  

Design of Attitude Control System Based onμ-Synthesis for Morphing Wing Cruise Missile

作　　者：舒营恩 郭建国[1] 周军[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《计算机仿真》2013年第1期124-127,共4页Computer Simulation

基　　金：航天科技创新基金(N11XW0001);西北工业大学基础研究基金(JC201024)

摘　　要：研究巡航导弹稳定性优化控制问题,针对面对称可变翼巡航导弹,利用μ综合方法设计了导弹的姿态控制系统。常规巡航导弹执行任务特点单一,可变翼巡航导弹可以通过改变气动外形实现多任务飞行。然而随着弹翼的变化导致导弹的动力学模型与控制特性更为复杂,为了提高可变翼巡航导弹的鲁棒性能,结合弹翼的变化策略构建可变翼导弹的多体动力学模型,综合考虑控制对象的参数不确定性和结构不确定性,采用μ综合方法设计了算例的三通道控制系统并进行了仿真。仿真结果表明,μ综合姿态控制系统不仅具有良好的动态特性,而且对参数不确定性具有良好的鲁棒稳定性。The existing cruise missiles are applied to certain specific missions. The smart morphing cruise missile can morph configuration to adapt to different missions. As morphing wings, dynamics and control characteristics of missile become complex. In order to improve robust performance of the cruise missile, the multi-body dynamic model of morpbing cruise missile based on morphing wings, parameter uncertainties and structure uncertainties can be con- sidered by using W-synthesis. The three-channel robust attitude control law for an example missile was designed. The simulation results show that the designed based on ix-synthesis controller has not only good dynamic perform- ance, but also excellent robust stability and robust performance.

关 键 词：可变翼 鲁棒控制 模型不确定性 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]