航空科学技术2016，Vol.27Issue(8)：54-57,4.
金属加筋壁板疲劳裂纹扩展研究
Study on Fatigue Crack Growth of Stiffened Metal Panels
施剑玮1
作者信息
- 1. 上海飞机设计研究院 强度设计研究部，上海 201210
- 折叠
摘要
Abstract
The prediction and test research on fatigue crack growth for the stiffened aluminum alloy panels of“工”section stringer were presented. The stress intensity factor for the stiffened panel was calculated based on the linear elastic fracture mechanics and finite element analysis. The crack growth rate equation used in NASGRO and the load interaction model named the modified generalized Willenborg were used as the basis for the calculation of cycle-by-cycle crack growth life. The predictions and the test results for crack growth of stiffened panels are in good agreement.关键词
加筋壁板/裂纹扩展/载荷交互作用/飞-续-飞载荷谱Key words
stiffened panel/crack growth/load interaction/flight-by-flight load spectrum分类
航空航天引用本文复制引用
施剑玮..金属加筋壁板疲劳裂纹扩展研究[J].航空科学技术,2016,27(8):54-57,4.
