An experimental and numerical study on the crush behaviour of hybrid unidirectional/woven carbon-fibre reinforced composite laminates
File(s)
Author(s)
Liu, H
Falzon, BG
Dear, JP
Type
Journal Article
Abstract
In composite aircraft structures, woven carbon-fibre reinforced plies are often used as the surface plies of a monolithic composite panel, made from unidirectional plies, to mitigate damage during drilling and provide a measure of impact damage resistance. This research presents, for the first time, a detailed experimental and numerical study on the crush behaviour of hybrid unidirectional/woven carbon-fibre reinforced composite laminates. Quasi-static crush tests are performed on composite specimens with two different trigger geometries; a bevel-trigger and a steeple-trigger. A computational model, which accounts for both interlaminar and intralaminar damage in hybrid unidirectional (UD)/woven composite laminates, implemented as a user subroutine in Abaqus/Explicit, was used. A comparison between experimental and numerical results confirms the computational tool's accuracy in predicting the energy absorption and damage mechanisms of hybrid specimens. The proposed approach could significantly reduce the extent of physical testing required in the development of crashworthy structures.
Date Issued
2019-12-01
Date Acceptance
2019-09-12
ISSN
0020-7403
Publisher
Elsevier BV
Journal / Book Title
International Journal of Mechanical Sciences
Volume
164
Copyright Statement
© 2019 Elsevier Ltd. All rights reserved. This manuscript is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International Licence http://creativecommons.org/licenses/by-nc-nd/4.0/.
Subjects
Mechanical Engineering & Transports
0910 Manufacturing Engineering
0905 Civil Engineering
0913 Mechanical Engineering
Publication Status
Published
Article Number
ARTN 105160
Date Publish Online
2019-09-13