首页> 中文期刊>西北工业大学学报 >一种先进的飞机吊挂结构疲劳寿命仿真分析方法

一种先进的飞机吊挂结构疲劳寿命仿真分析方法

     

摘要

常规的有限元疲劳寿命仿真分析采用连续函数作为形状函数,在处理位移不连续问题时,需将裂尖附近网格进行高密处理和重新剖分来进行裂纹扩展模拟,导致求解规模大,计算效率低.采用扩展有限元法和虚拟裂纹闭合技术,以吊挂结构为研究对象,通过建立局部模型,对疲劳裂纹扩展寿命进行分析计算,使得计算效率提高,且计算结果与试验结果相比,误差仅为8.2%,从而证明了该方法的有效性.%The conventional finite element simulation of the fatigue life analysis using continuous function as shape function , In dealing with the problem of displacement discontinuity , It is necessary to carry out crack propagation simulation by high density meshing and re-segmentation in the vicinity of the crack tip , which leads to large scale and low computational efficiency .In this paper ,based on the hanging structure , through the establishment of local model, the extended finite element method and the virtual crack closure technique are used to simulate the fatigue crack propagation life , improving computational efficiency , the calculation results compared with the experimental results, error was only 8.2%, proving the effectiveness of the proposed method .

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