着舰导引中的H_∞飞行/推力控制系统研究  

Study of Flight/Thrust Control System Using H_∞ Synthesis in Carrier Landing System

作　　者：余勇[1] 杨一栋[1] 代世俊[1] 

机构地区：[1]南京航空航天大学自动化学院,南京210016

出　　处：《南京理工大学学报》2003年第3期256-260,共5页Journal of Nanjing University of Science and Technology

基　　金：国防科技预研行业基金资助项目

摘　　要：运用基于线性矩阵不等式的H∞ 控制理论 ,提出了保持由地速构成的迎角αd 恒定的H∞ 飞行 /推力综合控制增广模型 ,使飞机接近舰尾处于雷达导引系统关闭的关键时刻 ,仍具有优良的姿态保持及抑制气流扰动性能 ,改变了传统设计由导引系统纠正气流扰动而引起的轨迹偏离 ;还从工程应用角度出发 ,提出了H∞ 控制器的降阶方法 。In this paper, the flight/thrust integrated control system (FTICS) with constant α d , actual angle of attack, using LMI based H ∞  synthesis is developed. The FTICS designed can improve the key performances of dynamic tracking and air wake disturbance restraining and keep attitude and path angle constant even during the airplane passing through the ramp where the tracking radar doesn’t work and the guidance signal is terminated. In view of engineering realization the H ∞  controller order reduction method is also proposed. The simulation results indicate the newly designed FTICS can satisfy the design specifications very well.

关 键 词：舰载飞机 飞行/推力系统 线性矩阵不等式 H∞控制 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]