某机身壁板结构环向裂纹扩展分析与试验对比

Comparison between the Crack Growth Analysis and Test Result of Fuselage Panel with Circumferential Crack

对于机身加筋壁板结构,获取较为准确的应力强度因子是进行裂纹扩展分析的基础,其核心工作是计算结构的几何因子。结合T.Swift提出的机身加筋壁板结构几何因子计算方法,编制相关分析工具,计算获得某机身壁板结构环向裂纹几何因子,将计算结果与采用有限元法计算获得的几何因子进行对比,并将几何因子输入Nasgro软件进行裂纹扩展寿命分析,与试验结果进行对比。结果表明:二者吻合较好。该方法计算效率高,可节省大量计算时间,具有较强的工程应用价值。

With regard to the fuselage stiffened panel,it is essential to attain the stress intensity factor,and the core work is to calculate the geometrical factor.According to the analysis method of the stiffened panel structure which was put forward by T.Swift,the corresponding analysis tool is programmed,by which the geometrical factor of the fuselage panel with circumferential is obtained,then the theoretical result is compared with other result which is computed by finite element analysis.finally,the geometrical factor is input into the Nasgro software which is adopted to carry out the crack growth analysis,the life is almost identical with the test result.This method is pretty efficiency,and can help save a lot of time and money and have a strong engineering application value.