飞机纵向增稳系统结构方案及控制规律设计

Control Structure and Control Law Design of Aero Longitudinal Stability Augmentation System

基于自动控制的反馈原理,将飞机俯仰角速率、迎角(或法向过载)作为反馈信号,构建飞机运动模型的俯仰阻尼回路、法向过载回路,建立包含内、外两个回路的飞机纵向增稳控制系统原理结构图,并设计其控制规律。为验证所设计的飞机纵向增稳控制系统及其控制规律的合理性,在MATLAB平台下,进行对比仿真研究。仿真结果显示,飞机纵向增稳控制系统结构合理,易于实现,在其控制规律传动比选择合理时,可增加飞机的动、静稳定性,提高飞机的飞行品质。

In order to improve aero fly quality in high altitude and velocity and increase it dynamic and static state stability,the principle structure diagram of the longitudinal stability augmentation system（SAS）and its control law were established including inside and outside feedback signals basis on auto control feedback principle. The inside and outside feedback signals were pitching angle velocity signal and attack angle signal which were constituted aero pitching damp loop and upright over loading loop. For verification rationality of designed aero SAS structure and its control law,a great deal of simulation was did under the MATLAB platform. The simulation result manifestation： the aero SAS structure was simple and reasonable,and easy to realization. At it control law ratio was choose reasonable,and the designed control system can enhance dynamic and static state stability,and improve aero fly quality