机身壁板纵向裂纹扩展分析方法研究

Study on Crack Growth Analysis of Fuselage Panel with Longitudinal Crack

在对含裂纹的机身壁板结构损伤容限分析时,核心工作是获取较为精确的几何因子。参考Swift提出的加筋壁板结构加筋系数计算方法,编制计算工具,并考虑了应力分布系数及鼓胀系数,计算获得含纵向裂纹的某机身壁板结构几何因子,与有限元法计算获得的几何因子进行比较。将几何因子输入Nasgro软件进行裂纹扩展寿命计算,与试验结果进行比较,满足飞机型号设计要求,且方法计算速度快,具有较强的工程应用价值。

Attaining the accurate geometrical factor is the core work when carrying out the damage tolerance analysis of the fuselage panel with crack,according to the analysis method of the stiffened panel structure which was put forward by Swift,the corresponding analysis tool was programmed,the stress distribution factor and the bulging factor are considered,then the geometrical factor of the fuselage panel with longitudinal crack was obtained,then the theoretical result was compared with other result which was computed by finite element analysis.At the last,the geometrical factor was input into the Nasgro software which was adopted to carry out the crack growth analysis,the life was almost identical with the test result.This method was pretty efficiency,it can help save a lot of time and have a strong engineering application value.