大型飞机迎角保护控制律设计及试飞技术研究

Research on design and flight test technologies of large aircraft angle of attack protection control law

针对大型飞机迎角保护控制律设计及试飞问题,通过杆位移-过载梯度的实时精确调整及取大值逻辑指令切换,设计了迎角保护控制律,实现拉杆到底飞机迎角达到且不超过限制迎角的目的。根据迎角保护控制律的功能及试飞目的,将整个试飞过程分为三个阶段,研究了各个阶段的试飞技术。仿真结果表明,所设计的控制律能够实现迎角保护功能,具有良好的控制效果。

Aiming at the design and flight test of large aircraft angle of attack protection control law, the angle of attack protection control law is designed through real-time precise adjustment of the rod displacement-overload gradient and the command switching of large value logic, thus reaching purpose that the aircraft’s AOA reaches but not exceed the limit value when full back stick is applied. According to the function of the angle of attack protection control law and the purpose of flight test, the whole flight test process was divided into three stages, and the flight test technologies at each stage were studied. The simulation results show that the designed control law can achieve the angle of attack protection function and has good control effect.