摘要
本文对孔边三维短裂纹扩展特性进行试验研究和理论分析。首先用复形法测出板中孔边三维短裂纹在等幅载荷和单峰超载时扩展规律,然后运用弹塑性断裂力学和裂纹闭合理论对短裂纹的扩展作定性分析,用闭合模型计算短裂纹扩展寿命。理论计算与实验结果较吻合。
In this paper, the behaviour of small crack growth originating at the edge of a hole was studied experimentally and theoretically. The growth of small crack at the edge of central holes under constant-amplitude loading and single-peak overloading is measured by taking surface replicas at regular intervals. The behaviour of small crack growsh is explained by elastic -plastic fracture mechanics and crack closure theory.A Computer program was executed to predict the life of small cracks using the crack closure model. The computing results are in good agreement with the measured results.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1989年第2期B581-B586,共6页
Acta Aeronautica et Astronautica Sinica
关键词
裂纹扩展
疲劳
飞机
经济寿命
small crack, single-peak overloading, crack closure model.