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Impact on Vectran/Epoxy composites: Experimental and numerical analysis

Published online by Cambridge University Press:  21 November 2022

S.I.B. Syed Abdullah Open the ORCID record for S.I.B. Syed Abdullah [Opens in a new window] ,
L. Iannucci ,
E.S. Greenhalgh  and
F. Yusof Open the ORCID record for F. Yusof [Opens in a new window]
S.I.B. Syed Abdullah*
Affiliation:
Department of Aeronautics, Imperial College London, Exhibition Road, London SW7 2AZ, UK School of Mechanical Engineering, Universiti Sains Malaysia, Nibong Tebal, 14300 Penang, Malaysia
L. Iannucci
Affiliation:
Department of Aeronautics, Imperial College London, Exhibition Road, London SW7 2AZ, UK
E.S. Greenhalgh
Affiliation:
Department of Aeronautics, Imperial College London, Exhibition Road, London SW7 2AZ, UK
F. Yusof
Affiliation:
School of Mechanical Engineering, Universiti Sains Malaysia, Nibong Tebal, 14300 Penang, Malaysia
*
*Correspondence author. Email: syedidros86@gmail.com
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Abstract

The aim of this paper is to present a plane-stress damage model based on the Classical Lamination Theory (CLT), developed for polymer fibre-based composite. The proposed numerical model utilises a damage mechanics methodology coupled with fracture mechanics to predict composite failure, particularly under quasi-static and dynamic loadings. In addition, the proposed constitutive equations consider a single secant modulus to describe its tensile and compressive modulus, as opposed to the physically proposed tier models for polymer fibres which possesses a ‘skin-core’ structure. The result of single element and coupon-level modelling showed excellent correlation with the experimental results. In addition, it was also found that the proposed numerical model showed considerable accuracy on the response of the composite under low and high velocity impact loadings.

Keywords

Continuum Damage Mechanics (CDM)Finite Element (FE)Thermotropic Liquid Crystal Polymer (TLCP)Classical Lamination Theory (CLT)Fracture Mechanics
Type
Research Article
Information
The Aeronautical Journal , Volume 127 , Issue 1312 , June 2023 , pp. 923 - 949
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Copyright
© The Author(s), 2022. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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