Experimental study on delamination migration in composite laminates

被引：59
作者：
Pernice, Maria Francesca [1 ]
De Carvalho, Nelson V. [2 ]
Ratcliffe, James G. [3 ]
Hallett, Stephen R. [1 ]
机构：
[1] Univ Bristol, ACCIS, Bristol BS8 1TR, Avon, England
[2] NASA, Langley Res Ctr, Natl Inst Aerosp, Resident Durabil Damage Tolerance & Reliabil Bran, Hampton, VA 23681 USA
[3] NASA, Langley Res Ctr, Durabil Damage Tolerance & Reliabil Branch, Hampton, VA 23681 USA
来源：
COMPOSITES PART A-APPLIED SCIENCE AND MANUFACTURING | 2015年 / 73卷
基金：
美国国家航空航天局; 英国工程与自然科学研究理事会;
关键词：
Delamination; Transverse cracking; Mechanical testing; Finite element analysis (FEA); SUBSEQUENT MIGRATION; FRACTURE-TOUGHNESS; GROWTH; CRACK; DCB;
D O I：
10.1016/j.compositesa.2015.02.018
中图分类号：
T [工业技术];
学科分类号：
08 ;
摘要：
The transition of delamination growth between different ply interfaces in composite tape laminates, known as migration, was investigated experimentally. The test method used promotes delamination growth initially along a 0/theta ply interface, which eventually migrates to a neighbouring theta/0 ply interface. Specimens with theta = 60 degrees and 75 degrees were tested. Migration occurs in two main stages: (1) the initial 0/theta interface delamination turns, transforming into intraply cracks that grow through the theta plies; this process occurs at multiple locations across the width of a specimen, (2) one or more of these cracks growing through the theta plies reaches and turns into the theta/0 ply interface, where it continues to grow as a delamination. A correlation was established between these experimental observations and the shear stress sign at the delamination front, obtained by finite element analyses. Overall, the experiments provide insight into the key mechanisms that govern delamination growth and migration. (C) 2015 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY license (http://creativecommons.org/licenses/by/4.0/).
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页码：20 / 34
页数：15
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