基于LMI的H_∞飞行/推力综合控制系统设计  

Design of Flight/Thrust Integrated Control System Using LMI-Based H_∞ Synthesis

作　　者：代世俊[1] 杨一栋[1] 余勇[1] 

机构地区：[1]南京航空航天大学自动化学院,南京210016

出　　处：《南京航空航天大学学报》2002年第4期386-390,共5页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国防科技预研重点基金 (编号 :3 7.2 .1)资助项目

摘　　要：在低动压下 ,着舰导引的关键技术是提高轨迹动态跟踪精度和抑制舰尾流气流扰动。为此 ,本文研究了基于线性矩阵不等式 (L MI)的 H∞ 飞行 /推力综合控制设计技术 ,提出了在动态轨迹跟踪与气流扰动下均能保持由地速构成的迎角不变的 H∞ 控制增广模型 ,设计了 H∞ 飞行 /推力综合控制器。基于工程应用 ,给出了 H∞ 控制器降阶方法 ,进行了离散化实时仿真验证。仿真表明 。A flight/thrust integrated control system with constant α d, actual angle of attack, using LMI based H ∞ synthesis of automatic carrier landing system is designed. The key technologies of landing aircraft with low aerodynamic pressure on carrier are used to improve the precision of path dynamic tracking and to restrain air wake disturbances. Firstly, a H ∞ synthesis model of flight/thrust integrated control system is established to keep α d constant under the conditions of both dynamic tracking and air wake disturbances. Secondly, the H ∞ controller is computed by the LMI tools of the Matlab software. Next, the order of the H ∞ controller is reduced by engineering realization, which translates the H ∞ controller realization from state space to transfer functions and eliminates the non dominant poles and zeros of each transfer function. Simulational results indicate that the flight/thrust integrated control system designed achieve obviously better performance of path dynamic tracking as well as restraining the air wake disturbances than previous flight control system designed by the traditional PID methodology.

关 键 词：LMI 设计 线性矩阵不等式 舰载飞机 鲁棒控制 推力控制 飞行控制 

分 类 号：V249[航空宇航科学与技术—飞行器设计] V233.7