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    A finite element analysis of impact damage in composite laminates

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    Authors
    Shi, Yu
    Soutis, Constantinos
    Affiliation
    University of Chester; University of Manchester
    Publication Date
    2012-12-01
    
    Metadata
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    Abstract
    In this work, stress-based and fracture mechanics criteria were developed to predict initiation and evolution, respectively, of intra- and inter-laminar cracking developed in composite laminates subjected to low velocity impact. The Soutis shear stress-strain semi-empirical model was used to describe the nonlinear shear behaviour of the composite. The damage model was implemented in the finite element (FE) code (Abaqus/Explicit) by a user-defined material subroutine (VUMAT). Delamination (or inter-laminar cracking) was modelled using interface cohesive elements and the splitting and transverse matrix cracks that appeared within individual plies were also simulated by inserting cohesive elements between neighbouring elements parallel to the fibre direction in each single layer. A good agreement was obtained when compared the numerically predicted results to experimentally obtained curves of impact force and absorbed energy versus time. A non-destructive technique (NDT), penetrant enhanced X-ray radiography, was used to observe the various damage mechanisms induced by impact. It has been shown that the proposed damage model can successfully capture the internal damage pattern and the extent to which it was developed in these carbon fibre/epoxy composite laminates.
    Citation
    Shi, Y., & Soutis, C. (2012). A finite element analysis of impact damage in composite laminates. The Aeronautical Journal, 116 (1186), 1331-47. https://doi.org/10.1017/S0001924000007661
    Publisher
    Cambridge University Press
    Journal
    The Aeronautical Journal
    URI
    http://hdl.handle.net/10034/621147
    DOI
    10.1017/S0001924000007661
    Additional Links
    https://www.cambridge.org/core/journals/aeronautical-journal/article/finite-element-analysis-of-impact-damage-in-composite-laminates/1C553EDE76E767B0B75E4B82933AA430
    Type
    Article
    Language
    en
    ISSN
    2059-6464
    ae974a485f413a2113503eed53cd6c53
    10.1017/S0001924000007661
    Scopus Count
    Collections
    Mechanical Engineering

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