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首页> 美国政府科技报告 >Exploration of Statistical Fatigue Failure Characteristics of 0.063-Inch Mill-Annealed Ti-6Al-4V Sheet and 0.050-Inch Heat-Treated 17-7PH Steel Sheet Under Simulated Flight-By-Flight Loading.
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Exploration of Statistical Fatigue Failure Characteristics of 0.063-Inch Mill-Annealed Ti-6Al-4V Sheet and 0.050-Inch Heat-Treated 17-7PH Steel Sheet Under Simulated Flight-By-Flight Loading.

机译：0.063英寸轧机退火Ti-6al-4V板材和0.050英寸热处理17-7pH钢板在模拟飞行载荷下的统计疲劳失效特性探讨。

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摘要

A total of 17 mill-annealed Ti-6Al-4V 0.063-in. sheet and 14 heat-treated 17-7PH steel 0.050-in. sheet, unique multidetail specimens were fatigue tested under a flight-by-flight loading spectrum to develop a data base for investigating the statistical materials/structures fatigue failure characteristics of these two alloys. Columnar buckling restraint was provided for specimens by welded fixtures sandwiching the specimens. A painted crack detection circuit was applied to locate and control size of initiated cracks. In several cases, test specimens of the relatively hard 17-7PH steel fractured before initiated cracks or initial flaws were detected. At open hole structural simulators detected fatigue cracks were removed by oversizing. The initiation data were examined by maximum likelihood methods for both log-normal and Weibull distributional representation. At a 0.50 reliability level, the results did not show an obvious distributional representation. At a 0.50 reliability level, the results did not show an obvious advantage of either distribution, but on increased levels of reliability, the Weibull distribution was a significantly more conservative simulation of the test data, which showed less variability than that estimated in a previous study.

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