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Generalized theoretical analysis method for free-edge delaminations in composite laminates

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Abstract

A simplified method for determining the individual mode components of the strain energy release rate of free-edge delaminations in composite laminates is proposed. Interlaminar stresses are evaluated as an interface moment and interface shear forces obtained from equilibrium equations of stress resultants at the interface between the adjacent layers. The deformation of edge-delaminated laminate is calculated by using a generalized quasi-three dimensional classical laminated plate theory developed by the authors. The analysis provides closed-form expressions for the Mode-I, Mode-II and Mode-III component of the strain energy release rate by combining the deformation of the edge-delaminated laminate with the interface moment and the interface shear forces. The presented method is compared with existing method suggested by Li for the asymmetry laminate. Comparison of the results with a finite element analysis using the virtual crack closure technique shows good agreement.

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Authors and Affiliations

  1. Department of Aerospace Eng., Chosun University, 375, Seosuk-dong, Gwangju, Korea

    In-Gwon Kim & Chang-Duk Kong

  2. Department of Aerospace Eng., Kyushu University, Fukuoka, Japan

    N. Uda

Authors
  1. In-Gwon Kim
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  2. Chang-Duk Kong
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  3. N. Uda
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Kim, IG., Kong, CD. & Uda, N. Generalized theoretical analysis method for free-edge delaminations in composite laminates. Journal of Materials Science 37, 1875–1880 (2002). https://doi.org/10.1023/A:1014903518913

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  • DOI: https://doi.org/10.1023/A:1014903518913

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