Fail-safe design of integral metallic aircraft structures reinforced by bonded crack retarders

被引：45

作者：

Zhang, X. ^{[1
]}

Boscolo, M. ^{[1
]}

Figueroa-Gordon, D. ^{[2
]}

Allegri, G. ^{[1
]}

Irving, P. E. ^{[2
]}

机构：

[1] Cranfield Univ, Dept Aerosp Engn, Cranfield MK43 0AL, Beds, England

[2] Cranfield Univ, Dept Mat, Cranfield MK43 0AL, Beds, England

来源：

ENGINEERING FRACTURE MECHANICS | 2009年 / 76卷 / 01期

基金：

英国工程与自然科学研究理事会;

关键词：

Integral metallic structure; Crack retarders; Bonded straps; Fail-safe; Fatigue crack growth life;

D O I：

10.1016/j.engfracmech.2008.02.003

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

This paper presents an investigation on the effectiveness of crack growth retarders bonded to integral metallic structures. The study was performed by both numerical modelling and experimental tests. It focuses on aluminium alloy panels reinforced by bonded straps made of carbon-epoxy, glass-epoxy composite materials or a titanium alloy. The goal was to develop a fail-safe design for integrally stiffened skin-stringer panels applicable to aircraft wing structures. The modelling strategy and finite element models are presented and discussed. The requirements that the models should meet are also discussed. The study has focused on establishing the extent of crack retarder benefits, in terms of fatigue crack growth life improvement, by numerical simulation and experimental tests of various crack retarders. The results of predicted fatigue crack growth retardation have been validated by tests of laboratory samples. This study concludes that by bonding discrete straps to an integral structure, the fatigue crack growth life can be significantly improved. (c) 2008 Elsevier Ltd. All rights reserved.

引用

页码：114 / 133

页数：20

共 22 条

[1]

[Anonymous], 47 AIAA ASME ASCE AH

[2]

BOSCOLO M, 2007, 48 AIAA ASME ASCE AH

[3]

Brock D., 1986, Elementary Engineering Fracture Mechanics

[4]

CARTIE D, FM94 UNPUB

[5]

Colavita M, 2006, P SAMPE C 2006

[6] Delamination effects on cracked steel members reinforced by prestressed composite patch [J].

Colombi, P ;

Bassetti, A ;

Nussbaumer, A .

THEORETICAL AND APPLIED FRACTURE MECHANICS, 2003, 39 (01) :61-71

[7]

DATOO MH, 1991, MECH FIBROUS COMPOSI, pCH7

[8]

EHRSTROM JC, 2005, 23 S INT COMM AER FA, P79

[9]

FIGUEROAGORDON D, 2007, FATIGUE CRACK UNPUB

[10]

Glinka G., 1979, FRACTURE MECH, P198, DOI DOI 10.1520/STP34914S

← 1 2 3 →