Fatigue life scatter of aluminium alloy helicopter lugs

被引：2

作者：

Xi, NS ^{[1
]}

Xie, ML ^{[1
]}

Zhang, ZL ^{[1
]}

Tao, CH ^{[1
]}

机构：

[1] Beijing Inst Aeronaut Mat, Failure Anal Ctr AVIC, Beijing 100095, Peoples R China

来源：

ENGINEERING FAILURE ANALYSIS | 2000年 / 7卷 / 04期

关键词：

fatigue testing; recrystallization; fracture surfaces; stress analysis;

D O I：

10.1016/S1350-6307(99)00021-7

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

Fatigue tests were performed on lugs in five cases with stress ratio R = 0.1 and maximum load F-max=44 kN. However, it was found that there was a remarkable scatter of fatigue lives even in identical tests. Fractography of the fractured lugs has shown that each crack initiated at one origin, which was on the hole surface and near one side of the lug. Stress analysis has demonstrated that the crack origins locate in a high stress region and the fatigue stresses make the lugs fail in range of 10(5)-10(6) cycles. Detailed examination of the microstructure of the lugs has shown that the recrystallization degrees in the lugs vary. It is the scatter of recrystallization degree that increases the fatigue lives of lugs. A further analysis has indicated that the scatter of recrystallization degree may result from the differences of original bar stock sizes and deformations in die forging. (C) 2000 Elsevier Science Ltd. All rights reserved.

引用

页码：239 / 247

页数：9