南京航空航天大学学报(英文版)
南京航空航天大學學報(英文版)
남경항공항천대학학보(영문판)
TRANSACTIONS OF NANJING UNIVERSITY OF AERONARUTICS AND ASTRONAUTICS
2002年
1期
31-36
,共6页
飞行/推力综合控制%H∞综合%线性矩阵不等式%飞行控制系统%舰载飞机
飛行/推力綜閤控製%H∞綜閤%線性矩陣不等式%飛行控製繫統%艦載飛機
비행/추력종합공제%H∞종합%선성구진불등식%비행공제계통%함재비궤
flight/thrust integrated control%H∞ synthesis%linear matrix inequality%flight control system%carrier-based aircraft
以提高低动压着舰时动态跟踪及抑制舰尾气流扰动的性能为期望,基于线性矩阵不等式(LMI)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结构.使飞机在接近舰尾处于雷达导引系统关闭的关键时刻,该系统仍有姿态保持及抑制气流扰动的优良性能,从而改变了传统设计需由导引系统纠正气流扰动而引起的轨迹偏离.基于工程应用,文中提出了H∞控制器的降阶方法,进行了离散化实时仿真验证.仿真表明,本文开发的系统能够很好地满足设计要求.
以提高低動壓著艦時動態跟蹤及抑製艦尾氣流擾動的性能為期望,基于線性矩陣不等式(LMI)的H∞控製理論,提齣瞭保持由地速構成的迎角αd恆定的H∞飛行/推力綜閤控製增廣模型結構.使飛機在接近艦尾處于雷達導引繫統關閉的關鍵時刻,該繫統仍有姿態保持及抑製氣流擾動的優良性能,從而改變瞭傳統設計需由導引繫統糾正氣流擾動而引起的軌跡偏離.基于工程應用,文中提齣瞭H∞控製器的降階方法,進行瞭離散化實時倣真驗證.倣真錶明,本文開髮的繫統能夠很好地滿足設計要求.
이제고저동압착함시동태근종급억제함미기류우동적성능위기망,기우선성구진불등식(LMI)적H∞공제이론,제출료보지유지속구성적영각αd항정적H∞비행/추력종합공제증엄모형결구.사비궤재접근함미처우뢰체도인계통관폐적관건시각,해계통잉유자태보지급억제기류우동적우량성능,종이개변료전통설계수유도인계통규정기류우동이인기적궤적편리.기우공정응용,문중제출료H∞공제기적강계방법,진행료리산화실시방진험증.방진표명,본문개발적계통능구흔호지만족설계요구.
The landing task of an aircraft under low aerodyna-mic pressure on carrier requires precise airplane control. A flight/thrust integrated control system (FTICS) with constant αd, actual angle of attack, is developed using LMI-based H∞ synthesis. The typical single input/output specifications are translated into the weighting functions of an H∞ output-feedback synthesis problem. The motivation of the work is to improve the key performance of dynamic tracking and air disturbance attenuation. The FTICS can keep the attitude angle and the path angle unchangeable as the airplane is passing through the ramp at which the tracking radar doesnot work and the guidance signal is terminated. For engineering application, an order-reduction method of the H∞ controller is also proposed. Simulational results indicate that the system satisfies the design requirements quite well.
