飞机管道疲劳性能仿真分析与试验验证

Simulation Analysis and Test Verification of Aircraft PipelineFatigue Performance

为解决实际工况中飞机管道疲劳性能问题,研究飞机管道安装应力环境下的疲劳寿命分析方法,首先,建立飞机管道有限元模型;然后,利用有限元软件ANSYSWorkbench对不同轴向装配偏差情况下的管道进行模态分析以及谐响应分析;进而,提取出管道危险点应力幅值,利用材料的S-N曲线进行疲劳寿命预测。最后,设计不同安装应力情况下的管道共振疲劳试验,并对仿真结果进行验证。仿真和试验的对比结果表明:根据仿真和试验得到的管道发生断裂的位置一致,两者管道疲劳寿命循环次数契合,随着轴向装配偏差增大,管道疲劳寿命逐渐下降。

The fatigue performance of aircraft pipeline in actual working conditions is studied,the fatigue life analysis method considering the installation stress environment of aircraft pipeline is established.Firstly,the aircraft pipeline finite element model is established,and the modal analysis and harmonic response analysis of the pipeline under different axial assembly deviation are carried out using the finite element software ANSYS Workbench.Then,the stress amplitude at the critical point of the pipeline is extracted,and the fatigue life is predicted by using the S-N curve of the material.Finally,the resonant fatigue test of the pipe under different installation stresses is designed and performed,and the simulation results are verified.The results show that the fracture locations of the pipes obtained from the simulation and the test are consistent,and both results of the numbers of cycles for the fatigue of the pipes are nearly the same,the fatigue life of pipes gradually decreases with the increase of the axial assembly deviation.