CAJ | 학술논문

　　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。
　　위제고대영각비행상태하적전두궤등작전비궤공제계통적은태정도，개선기공제계통적동태성능，대모형비궤부앙방위공제계통결구진행개진설계。통과인입적분배절，장기부앙방위공제계통유0형계통변위I형계통，제고료공제정도급항간우능력。통과합리배치부앙방위공제계통공제규률전동비，대기동태성능야진행료유효개진。방진결과현시：소설계적비궤부앙방위공제계통결구합리，공제규률전동비배치흡당，대대영각비행상태하적비궤，기공제계통은정성득도제고，기동、정태성능득도개선。
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.