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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。
Aircraft structural strength test, the test control parameters are mainly obtained through trial and error manual experience, may lead to load during the commissioning process of oscillation and impact on the structure of the test piece and the safety of hydraulic equipment test results. In view of this problem, taking the cantilever structure test system as the research object, the mathematical model of each component of the test system is established and the coupled analysis of the test components is carried out. By using the stability margin analysis and the system bandwidth analysis theory, the experimental system PID control parameter. At the same time, the method was verified by a cantilever structure test. Simulation and experimental results show that the new method is reasonable and effective.