摘要
基于飞机纵向操纵系统中飞行高度和飞行速度变化对飞机舵面偏转角调节需求,研究杆系操纵系统力臂自动调节装置的电气控制原理及工作过程。首先根据不同飞行高度和速度对飞机单位过载平尾偏角固有影响规律,得出力臂自动调节规律,然后利用Multisim软件分别开展敏感电桥、差分放大、施密特触发及功率放大电路设计与仿真,得出各级控制电路电气参数传输特性变化规律,为进一步研究飞机力臂性能超差故障分析和故障预测提供借鉴。
Based on the requirement of aircraft control surface deflection angle adjustment due to the change of flight altitude and speed in the aircraft longitudinal control system,the electrical control principle and working process of the force arm automatic adjustment device of the linkage control system are studied.Firstly,according to the inherent influence law of different flight altitude and speed on the flat tail deflection angle of aircraft Unit overload,the automatic adjustment law of output arm is obtained.Then,the design and simulation of sensitive bridge,differential amplification,schmidt trigger and power amplification circuits are carried out by using Multisim software,and the variation law of electrical parameter transmission characteristics of each level of control circuit is obtained,which provides a reference for further study of aircraft force arm performance out of tolerance fault analysis and fault prediction.
作者
张元峰
孟欣
于春风
ZHANG Yuan-feng;MENG Xin;YU Chun-feng(Naval Aeronautical Engineering Academy Qingdao Branch,Qingdao 266041 China)
出处
《自动化技术与应用》
2024年第5期15-18,34,共5页
Techniques of Automation and Applications
