倾转旋翼机过渡段控制器的μ综合设计方法  

Design of Flight Control System for Tiltrotor Conversion Using μ-Synthesis

作　　者：孙杰[1] 杨军[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《飞行力学》2008年第3期41-43,共3页Flight Dynamics

摘　　要：针对倾转旋翼机过渡段模型参数摄动问题,在状态方程描述的框架下,用线性分式变换形式将模型参数摄动表示为对角块结构,采用μ综合方法设计了倾转旋翼机过渡段飞行控制器。仿真结果表明,存在模型参数摄动和外部干扰时,系统具有较好的鲁棒性和动态性能,验证了该设计方案的可行性。The parameter uncertainty in tihrotor model caused by the variation of nacelle angle was considered in controller designing for flight mode conversion of tihrotor. In order to separate the uncertainty from nominal model, the uncertainty was expressed as a diagonal structure in the form of LFT, which avoided the unnecessary conservation. Then the flight controller was designed by μ-synthesis theories. Simulation shows that the controller provides good robust stability and performance.

关 键 词：倾转旋翼机 飞行控制 鲁棒性能 Μ综合 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]