摘要
本文以裂纹尺寸达到经济修理极限对应的结构细节条件裂纹萌生P-S-N曲线为基础,将谱载下安全寿命的存活率与裂纹超越数概率联系在一起,建立各应力区的P(i,τ)随时间变化曲线,进而评估指定时间的结构损伤度,并预测经济寿命,构成完整的耐久性裂纹萌生方法,最后给出一个简单实例。
In this paper, a crack initiation metho . for durability analysis is developed. The method connected the reliability of safe life under load spectrum with the crack exceedance probability on the basis of P-S-N curves for structure members crack initiation, the condition is that the crack length reaches economic repairment limit. And the P(i,τ)-τ curves of every stress region are established. Then the structure damage degree is evaluated and the structure economic life is predicted. Finally, a simple example is given.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1992年第3期A182-A186,共5页
Acta Aeronautica et Astronautica Sinica
关键词
耐久性
裂纹萌生
经济寿命
飞机
durability analysis, crack initiation, economic life