过失速机动飞机的鲁棒非线性控制律设计  

ROBUST, NONLINEAR CONTROL DESIGN FOR A POSTSTALL MANEUVER AIRCRAFT

作　　者：范子强[1] 方振平[1] 

机构地区：[1]北京航空航天大学509教研室,北京100083

出　　处：《航空学报》2002年第3期193-196,共4页Acta Aeronautica et Astronautica Sinica

基　　金：航空科学基金资助项目 (98A5 10 3 9)

摘　　要：采用非线性动态逆和结构奇异值综合方法设计了过失速飞行条件下飞控系统控制律 ,解决了飞控设计中面临的非线性和鲁棒性问题。应用非线性动态逆的目的就是对过失速机动飞行条件下高度非线性的飞机动力学进行线化 ;从而围绕线性的快逆回路应用结构奇异值综合方法设计相应的鲁棒控制器 ,以提供对驾驶员指令的鲁棒跟踪。所设计的飞控系统将达到期望的飞行品质 ,确保系统对过失速机动飞行过程中因非定常气动力效应引起的系统参数摄动鲁棒性良好。高逼真度。A flight control system is developed for an aircraft performing post-stall maneuver. The methods of nonlinear dynamic inversion and structured singular value synthesis are combined to address both the nonlinearity and robustness problems of flight at post-stall maneuver conditions. The purpose of the nonlinear dynamic inversion control is to linearize the highly nonlinear vehicle response at post-stall maneuver conditions. Structured singular value synthesis is used to design an robust controller for the linearized fast inversion loop, which provides robust tracking to pilot commands. The resulting flight control system achieves desired flying qualities and guarantees good robustness to uncertainties induced by unsteady aerodynamics effects in post-stall maneuvering. This is demonstrated by high fidelity nonlinear simulation results.

关 键 词：结构奇异值综合 非线性动态逆 飞行控制系统 鲁棒性 过失速机动 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程] V249.122