摘要
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.
作者
赵正大
寸文渊
钱进
赵旭升
舒阳
陈果
ZHAO Zhengda;CUN Wenyuan;QIAN Jin;ZHAO Xusheng;SHU Yang;CHEN Guo(Chengdu Aircraft Industrial(Group)Company Ltd.,Chengdu 610092,China;College of Civil Aviation,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;College of General Aviation and Flight,Nanjing University of Aeronautics and Astronautics,Liyang 213300,Jiangsu China)
出处
《噪声与振动控制》
CSCD
北大核心
2023年第5期239-244,279,共7页
Noise and Vibration Control
基金
国家科技重大资助专项(2017-Ⅳ-0008-0045)
国家自然科学基金资助项目(51675263)。
关键词
振动与波
飞机管道
装配应力
疲劳性能
疲劳试验
有限元
vibration and wave
aircraft pipeline
assembly stress
fatigue performance
fatigue test
finite element