含多裂纹铝板的剩余强度评估

Residual Strength Prediction of Thin Aluminum Alloy Panels with Multiple Site Cracks

提出了一种计算飞机多裂纹平板结构剩余强度的方法。该方法采用多裂纹结构中主裂纹旁的小裂纹的张开位移来预测剩余强度。裂尖张开位移和剩余强度通过应用弹塑性有限元获得。采用已发表的实验来应用和验证这个方法,结果表明:本模型预测的剩余强度与实验值相比误差在10%之内。

A method is proposed to predict the residual strength of the aircraft structure with multiple site cracks. The method is based on the crack tip opening displacement （CTOD） of the small crack closed to the leading crack. The CTOD and the residual strength are obtained by performing elastic-plas- tic finite element analysis. The experiment from the open literature is used for the application and the verification of the method. The relative error between the prediction and the experiment is within 10%.