Cold expansion effects on cracked fastener holes under constant amplitude and spectrum loading in the 2024-T351 aluminum alloy

被引：23

作者：

Warner, Jacob John ^{[1
]}

Clark, Paul N. ^{[2
]}

Hoeppner, David W. ^{[3
]}

机构：

[1] A10 Aircraft Struct Integr Program, Hill AFB, UT 84056 USA

[2] Southwest Res Inst, San Antonio, TX 78238 USA

[3] Univ Utah, Dept Mech Engn, Salt Lake City, UT 84112 USA

来源：

INTERNATIONAL JOURNAL OF FATIGUE | 2014年 / 68卷

关键词：

Cold expansion; Cold working; Fatigue crack growth; Fatigue load spectra; Life prediction;

D O I：

10.1016/j.ijfatigue.2014.05.002

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

The increased number of aging aircraft in operation today requires a deeper understanding of fatigue life improvement methods. This research focused on the fatigue life benefit from cold expanded holes with preexisting cracks approximately 1.270 mm (0.050 in.) long under constant amplitude and wing spectrum loading. Holes with preexisting cracks were tested to simulate the worst case scenario of a hole with a crack the size of the detection threshold, 1.270 mm (0.050 in.), present before cold expansion that was not found by Non Destructive Inspection. Test results were compared to crack growth models generated in AFGROW. At high stress levels the AFGROW models yielded non conservative results greater than 150% of the test demonstrated fatigue life. Published by Elsevier Ltd.

引用

页码：209 / 216

页数：8

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