基于H_∞/H_2方法的弹性飞行器颤振抑制系统设计  

Flutter suppression system design for elastic aircraft based on H_∞/H_2 method

作　　者：宋科璞 罗健晖[2] 张翔伦 SONG Ke-pu;LUO Jian-hui;ZHANG Xiang-lun(School of Automation, Northwestern Polytechnical University, Xi＇an 710072, China;National Key Laboratory of Science and Technology on Flight Control Integration, Xi＇an Flight Automatic Control Research Institute, Xi＇an 710065, China)

机构地区：[1]西北工业大学自动化学院,陕西西安710072 [2]西安飞行自动控制研究所飞行器控制一体化技术国防科技重点实验室,陕西西安710065

出　　处：《飞行力学》2017年第6期39-43,共5页Flight Dynamics

基　　金：中航工业产学研专项基金资助(CXY2014XGD09)

摘　　要：在考虑机翼弹性的情况下,研究大展弦比高空长航时飞行器的主动控制技术,以达到颤振抑制的效果。为了解决飞行器模型阶数过高难以进行控制律设计的问题,采用改进的平衡截断方法对模型进行降阶处理。同时针对机翼弹性所带来的严重气动弹性问题,基于静态输出反馈H_∞/H_2控制方法对降阶后的模型设计了颤振抑制控制律。仿真结果表明,飞行器在海平面高度下的颤振临界马赫数提高了128%,说明H_∞/H_2控制器起到了很好的主动控制效果。The active control technology for high-altitude long-endurance aircraft with high aspect ratio was studied in order to achieve the effect of flutter suppression. To solve the problem of designing control law for high order aircraft model,model reduction was realized by using an improved balanced truncate method. As for the serious aeroelastic problem caused by elasticity of wing,active control law for flutter suppression was designed based on static-output feedback H_∞/H_2 method. The simulation results showed that flutter Mach number at sea-level increased by 128%. In conclusion,the H_∞/H_2 controller has played a significant roll on active control.

关 键 词：弹性飞行器 主动控制 颤振抑制 H∞/H2控制 静态输出反馈 

分 类 号：V249.12[航空宇航科学与技术—飞行器设计]