超机动飞机的非线性控制与飞行员在环实时仿真

在空中格斗中，使用过失速机动可获得显著的战术优势，而飞机在大迎角和高角速率的情况下，其动力学具有强耦合性和非线性，本文讨论了应用非线性动态道进行超机动飞机飞行控制系统的设计。飞机的动力学可分成快慢两组变量，角速率是快变量，姿态角是慢变量，对快变量进行非线性逆控制器的设计，以此来稳定纵向短周期运动，并通过气动舵面与推力矢量的融合，来改善大迎角范围内的侧向响应。对慢变量进行非线性逆控制器的设计可使飞行员控制飞机慢动力学，即迎角、侧滑角和速度矢量滚转角。本文还讨论了一个飞行员在环实时仿真系统的设计，该系统采用了多台计算机的结构，可用于非线性动态逆控制律的飞行员在环分析。

Nonlinear Control for Super-Maneuvering Aircraft and Pilot-in-the-Loop Real-Time Simulation

Tactical advantages can be gained by use of post-stall maneuvering or super maneuvering in air-to-air combat situation. The aircraft dynamics exhibit significant coupling and nonlinearity when the aircraft operates at high angle of attack and with large angular rates.This paper describes the use of nonlinear dynamic inversion for the design of a flight control system for a super-maneuverable aircraft. The dynamics to be controlled were seperated into fast and slow variables. The fast variables were the angular rates and slow variables were the attitude angles. Then a nonlinear inversion controller was designed for the fast variables. This stabilized the longitudinal short-period and improved the lateral-directional responses over a wide range of angle of attack by use of a combination of aerodynamic surfaces and thrust rectoring control. Another nonlinear inversion controller was designed for the slow variables. It allows the pilot to control the slow dynamics,the angle of attack,side-slip angle and the velocity bank angle. This paper also describes the design On a real-time piloted simulation system. This system has a multi-computer structure and allows pilot-in-the-loop analysis of the nonlinear dynamic inversion control law designs.