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对民用飞机含纵向裂纹机身加筋壁板在增压和轴向拉伸联合载荷作用下进行损伤容限试验和数值仿真分析。通过试验深入研究了机身壁板的裂纹扩展规律和剩余强度特性,借助Ansys有限元软件计算了不同裂纹长度下的应力强度因子,对裂纹扩展寿命进行了预测,基于线弹性断裂力学给出了剩余强度特征曲线,并进行了试验结果和计算分析的对比。研究结果表明:数值分析与试验结果吻合良好,可为机身壁板损伤容限设计及评定提供依据。
The damage tolerance test and numerical simulation of the civil aircraft stiffened stiffened panel with longitudinal crack under the combined loads of supercharging and axial tensile are carried out. By means of experiments, the crack propagation law and the residual strength characteristics of fuselage slab are studied in depth. The stress intensity factors at different crack lengths are calculated by Ansys finite element software, and the crack propagation life is predicted. Based on the linear elastic fracture mechanics, Residual strength characteristics curve, and the comparison of the test results and calculation and analysis. The results show that the numerical analysis is in good agreement with the experimental results, which can provide the basis for the design and assessment of the damage tolerance of fuselage panels.