摘要
在对带有一个铆接孔的试件进行试验研究的基础上,利用性能退化失效曲线,提出了一种新的初始疲劳质量和裂纹扩展速率的确定方法。根据试验结果和理论推导,建立了裂纹扩展长度与加载循环次数的函数关系。在此基础上,估算了EIFS值,并用指数函数拟合方法估计了疲劳裂纹扩展速率。最后通过对临界裂纹尺寸的理论计算验证了新方法的可行性和有效性。
How to assess initial fatigue quality and crack growth rate rapidly and economically is the key of durability investigation.At present,experimentation is used to assess durability,which is very costly and time-consuming.Performance degradation curve includes a lot of information about fatigue failure.Based on the tests for specimens with one rivet hole respectirely,a new method of determining initial fatigue quality and crack growth rate with performance degradation curves of specimens are presented in the paper.According to the test results and theoretical derivation,the relationship of crack length with loading cycle is established.Then,the equivalent initial flaw size（EIFS） values are calculated and fatigue crack growth rates are estimated by using exponential fitting technique.The applicability and validity of the method are verified with theoretical computation of fracture limit finally.
出处
《航空材料学报》
EI
CAS
CSCD
北大核心
2011年第5期91-94,共4页
Journal of Aeronautical Materials
基金
江苏省高校自然科学研究计划项目(09KJB460006)
南京工业大学青年教师学术基金重点项目(39702011)
江苏省自然科学基金(BK2010556)
关键词
性能退化失效
当量初始缺陷尺寸
裂纹扩展速率
耐久性分析
临界裂纹尺寸
performance degradation failure
equivalent initial flaw size（EIFS）
crack growth rate
durability analysis
critical crack size
