某型飞机俯仰方位控制系统设计与仿真

Design and Simulation for Aero Pitching Azimut Control System

摘要:

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。

Abstract:

In order to increase steady state accuracy and improve dynamic state performence of the pitching azi. muth control system of the battleplan under especial fly state with big attack angle, improved structure of the pitching azimuth control system was designed. By means of introduceing integrator, it was changed from“0” type to“I”type control system of the pitching azimuth control system. The system’s control accuracy was en. hanced, and anti-interference ability was improved. By means of allocationed reasonable transmission ratio of control system, the dynamic performence also was improvement. Simulation results showed that designed control structure of pitching azimuth control system was reasonable, and collocated transmission ratio of the control laws was accurate. For the airplane under especial fly state with big attack angle, aero stability was enhanced and performance of dynamic and static state of control system were improved.