悬臂梁结构试验系统PID参数整定方法

Study of PID Tuning Method for Testing System of Cantilever Beam

飞机结构强度试验中,试验控制参数主要是通过人工经验试凑获得,可能导致调试过程中载荷出现振荡和冲击,对试验件结构和试验液压设备的安全性造成危害。针对此问题,以悬臂梁结构试验系统为研究对象,建立了试验系统各组件的数学模型并对试验组件进行耦合分析,利用稳定裕度分析和系统频宽分析理论,仿真得到了试验系统PID控制参数。同时利用了一个悬臂梁结构试验对该方法进行了验证。仿真和试验结果表明,新方法是合理有效的。

PID parameters are obtained using engineering experience in aircraft structural strength test, so there is severe oscillation phenomenon in the test system. The oscillation factor is harmful to the test article and the equipment. To solve the problem, the coupled mathematical model of components for the testing system is introduced to confirm PID parameters based on stability margin analysis for the open-loop system and frequency bandwidth analysis for the closed-loop system. In order to validate the method in this paper, a testing system for the cantilever structure is designed. Finally, a cantilever structure experiment is implemented. The experiment and simulation results show that the method presented in this paper is effective and reasonable to improve the control accuracy of the aircraft structure test, and could be widely used in relative test article.