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为提高大迎角飞行状态下的战斗机等作战飞机控制系统的稳态精度,改善其控制系统的动态性能,对某型飞机俯仰方位控制系统结构进行改进设计。通过引入积分环节,将其俯仰方位控制系统由0型系统变为I型系统,提高了控制精度及抗干扰能力。通过合理配置俯仰方位控制系统控制规律传动比,对其动态性能也进行了有效改进。仿真结果显示:所设计的飞机俯仰方位控制系统结构合理,控制规律传动比配置恰当,对大迎角飞行状态下的飞机,其控制系统稳定性得到提高,其动、静态性能得到改善。
In order to improve the steady state precision of the combat aircraft control systems such as fighter planes at high angle of attack flight and improve the dynamic performance of its control system, the structure of a certain aircraft pitch azimuth control system is improved. By introducing the integral part, the control system of the pitch position is changed from type 0 system to type I system, which improves the control accuracy and anti-interference ability. Through the reasonable configuration of the pitch and azimuth control system to control the law of transmission ratio, its dynamic performance has also been effectively improved. The simulation results show that the designed pitch attitude control system of the aircraft is reasonable in structure and the transmission law of the control law is properly configured. The stability of the control system is improved and the dynamic and static performance of the aircraft is improved for the aircraft in the high-angle flight state.