摘要
根据飞机结构静力/疲劳试验中操纵系统试验的需求,对控制模式转换技术进行研究,在协调加载控制系统中应用手动与自动两种方式进行飞机操纵系统模式转换试验。通过切换当前输入信号,将控制回路的当前输入信号无扰动转换为目标输入信号,控制模式相应改变。试验后对试验数据进行分析,试验结果表明,能够平稳快速地将当前控制模式转换,加载点误差以及跟随性均能满足试验要求。随着研究的深入,模式转换技术可逐步推广到相应的静力或疲劳试验中。
According to the demands of aircraft control system in aircraft structure static/fatigue test,the control mode switching technology is studied. Manual and automatic modes are used in the coordinated loading control system. By switching the current input signal,the current input signal of the control loop is converted to the target input signal without disturbance,and the control mode is changed accordingly. The test data are analyzed after the test. The test results show that the current control mode can be switched smoothly and quickly,and the loading point error and the following performance can meet the test requirements. With the deepening of research,mode switching technology can be gradually extended to the corresponding static or fatigue tests.
引文
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