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Predicting low-velocity impact damage in composites by a quasi-static load model with cohesive interface elements

Published online by Cambridge University Press:  27 January 2016

X. Zhang ,
F. Bianchi  and
H. Liu
F. Bianchi
Affiliation:
Aerospace Engineering Dept, Cranfield University, Bedford, UK
H. Liu
Affiliation:
AVIC First Aircraft Institute, Xi’an, China
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Abstract

A numerical model is developed for predicting low-velocity impact damage in laminated composites. Stacked shell elements are employed to model laminate plies with discrete interface elements in pre-determined zones to model the onset and propagation of matrix cracks and delamination. These interface elements are governed by a bi-linear cohesive failure law. Cohesive element zone size is determined by a separate finite element analysis using solid elements to identify the stress concentration sites. In order to save the computational effort, low-velocity impact load is modelled by quasi-static loading. Influence of contact force induced friction on shear driven mode II delamination is modelled by a friction model. For a clustered cross-ply laminate, calculated impact force and damage area are in good agreement with the test results. It is shown that matrix cracks should be included in the model in order to simulate delamination in adjacent interface. The practical outcome of this research is a validated modelling approach that can be further improved for predicting low-velocity impact damage in other stacking sequences.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1186 , December 2012 , pp. 1367 - 1381
Copyright
Copyright © Royal Aeronautical Society 2012 

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