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对敏捷性飞机飞行控制系统的设计方法进行了研究．研究表明当飞机进行大迎角机动时，飞机可以获得敏捷性机动能力．在这种情况下，飞机的动力学特性呈现非线性的特征．此时飞行控制系统的设计是一类非线性控制系统的设计问题，设计可采用非线性动态逆的方法进行．为简化控制律和工程因素，重点研究了利用一阶动态逆作为系统的反馈线性化控制，以得到线性化的系统．在此基础上再设计跟踪控制器，以满足大迎角非线性机动时的性能要求．最后以Ｆ８飞机为例进行飞行控制系统的详细设计，所设计的系统在一个大迎角机动指令作用下进行仿真研究，结果表明系统设计的有效性．
The design method of agile aircraft flight control system is studied. Studies show that when the aircraft maneuvers at high angles of attack, the aircraft can acquire agile maneuverability. In this case, the dynamics of the aircraft exhibit a non-linear characteristic. At this time, the design of flight control system is a kind of design problem of a kind of nonlinear control system, and the design can be carried out by nonlinear dynamic inverse method. In order to simplify the control laws and engineering factors, the first-order dynamic inverse is taken as the feedback linearization control of the system to get the linearized system. On this basis, the tracking controller is designed to meet the performance requirements of nonlinear maneuvering at high angle of attack. Finally, taking the F8 aircraft as an example, the detailed design of the flight control system is carried out. The designed system is simulated under the action of a high angle of attack maneuver. The results show the effectiveness of the system design.