【摘要】 给出加筋板多处损伤裂纹扩展的预测计算和试验 ,其目的是研究飞机真实结构———加筋板多裂纹扩展的预测计算方法。用Walker裂纹扩展方程和Willenborg Chang裂纹扩展模型为根据 ,并在每个载荷循环都考虑裂纹之间的相互影响。用循环接循环进行裂纹累积 ,用虚拟施加剩余强度载荷和裂尖韧带塑性区连通判据确定临界裂纹尺寸。文中给出典型随机谱下加筋板多裂纹扩展计算预测 ,并给出初始裂纹和剩余强度载荷的改变对临界裂纹尺寸和扩展寿命的影响 ,也给出在恒幅谱及程序块谱载荷下加筋板多裂纹的扩展试验以及试验与计算的比较更多还原

【Abstract】 The prediction and test research of crack growth for multiple site damage in stiffened panel are presented. The goal of investigation is to give a prediction calculation method for multiple site cracks growth in real aircraft structure——stiffened panel. The Walker equation and the Willenborg-Chang model are used in prediction calculation. The interaction of cracks is considered at each load cycle, and crack size is accumulated by cycle-by-cycle. The fictitious residual load is applied. The residual strength criterion for crack tip ligament yield is used to determine critical size of crack. The prediction calculation of crack growth under typical stochastic spectrum is given. The effects on critical crack size and crack growth life by the initial crack size and residual strength loading change are given. The crack growth under constant-load amplitude and procedure spectrum are tested. The results are compared with prediction calculation.更多还原