Fatigue Crack Growth Behavior under Spectrum Loading

被引：0

作者：

Kujawski, Daniel ^{[1
]}

Stoychev, Stoyan ^{[2
]}

机构：

[1] Western Michigan Univ, Coll Engn & Appl Sci, Dept Mech & Aeronaut Engn, Kalamazoo, MI 49008 USA

[2] Dana Corp, Kalamazoo, MI 49008 USA

来源：

ENGINEERING AGAINST FRACTURE | 2009年

关键词：

Spectrum loading; Spectrum modification; Fatigue crack growth;

D O I：

10.1007/978-1-4020-9402-6_18

中图分类号：

TU [建筑科学];

学科分类号：

0813 ;

摘要：

The purpose of this study is to investigate experimentally the fatigue crack growth behavior under typical service loading spectrum recorded from military P-3 cargo airplane. The material is 2324 - T39 Al alloy widely used in the aircraft industry. Experiments were conducted using the full spectrum and modified versions of it such as only 'positive' (no negative loads) or with reduced (clipped) high peaks. The results show that the compressive loads decrease fatigue life of the specimen by similar to 300%. Furthermore, by running tests with clipped peaks it was found that the fatigue life was shorten significantly due to reduction of crack growth retardation caused by highest tensile peaks. Multiple tests were conducted in order to establish a scatter in the experimental data under spectrum loads.

引用

页码：215 / +

页数：3