An experimental evaluation of fatigue crack growth

被引：123

作者：

Barter, S

Molent, L

Goldsmith, N

Jones, R

机构：

[1] Monash Univ, DSTO, Ctr Struct Mech, Dept Mech Engn, Clayton, Vic 3800, Australia

[2] Def Sci & Technol Org, Air Vehicles Div, Fishermans Bend, Vic 3207, Australia

来源：

ENGINEERING FAILURE ANALYSIS | 2005年 / 12卷 / 01期

关键词：

fatigue crack growth; crack growth; load history; aircraft structures; joint failures;

D O I：

10.1016/j.engfailanal.2004.04.002

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

This paper examines the fatigue crack growth histories of a range of test specimens and service loaded components and concludes that in all cases, the crack growth shows, as a first approximation a linear relationship between the log of the crack length or depth and the service history (number of cycles). These cracks have grown from; semi- and quarter elliptical surface cuts, holes, pits and inherent material discontinuities in test specimens, fuselage lap joints, welded butt joints, and complex tubular jointed specimens and include cracks grown under uniaxial and biaxial loading. The implications of this exponential growth are discussed. (C) 2004 Elsevier Ltd. All rights reserved.

引用

页码：99 / 128

页数：30

共 56 条

[1]

ANDERSON BE, 1978, AERONAUTICAL RES LAB, V448

[2]

Athiniotis N, 1996, DSTOTR0328

[3]

BARTER S, 2003, P INT AER C BRISB AU

[4]

BARTER SA, 1997, P 9 INT C FRACT SYDN