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Open Engineering

formerly Central European Journal of Engineering

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2391-5439
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Delamination of impacted composite structures by cohesive zone interface elements and tiebreak contact

1Material Research Centre, SEC Faculty, Kingston University, London, SW15 3DW, UK

2Department of Mechanical Engineering, Wichita State University, Wichita, KS, 67260, USA

© 2012 Versita Warsaw. This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License. (CC BY-NC-ND 3.0)

Citation Information: Open Engineering. Volume 2, Issue 4, Pages 612–626, ISSN (Online) 2391-5439, DOI: 10.2478/s13531-012-0018-0, September 2012

Publication History

Published Online:
2012-09-27

Abstract

Maximising impact protection of fibre reinforced plastic (FRP) laminated composite structures and predicting and preventing the negative effects of impact on these structures are paramount design criteria for ground and space vehicles. In this paper the low velocity impact response of these structures will be investigated. The current work is based on the application of explicit finite element software for modelling the behaviour of laminated composite plates under low velocity impact loading and it explores the impact, post impact and failure of these structures. Three models, namely thick shell elements with cohesive interface, solid elements with cohesive interface, and thin shell elements with tiebreak contact, were all developed in the explicit nonlinear finite element code LS-DYNA. The FEA results in terms of force and energy are validated with experimental studies in the literature. The numerical results are utilized in providing guidelines for modelling and impact simulation of FRP laminated composites, and recommendations are provided in terms of modelling and simulation parameters such as element size, number of shell sub-laminates, and contact stiffness scale factors.

Keywords: Impact; Laminated composite; Cohesive zone; Tiebreak contact; LS-DYNA

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