Abstract
In this paper, the coupled local-global buckling behavior in laminated composite plates with elliptic delaminations and the associated mechanisms of delamination growth under compressive loads are critically examined. The J-integral technique is used for delamination growth prediction in terms of pointwise energy release rate distribution along the delamination edge. A Multi-plate model, in conjunction with a 3-noded quasi-conforming shell element, is used to model the delaminated plates. The incremental equilibrium equations are set up based on total Lagrangian formulation. The solution strategy incorporates Gauss elimination in a cycle of Newton-Raphson iterations and is augmented with automated arc-length controled load incrementation and equilibrium iterations; and with automated post-buckling path tracing based on a linearised asymptotic solution. The effects of structural parameters such as delamination thickness, size and shape, on the post-buckling behavior and on the delamination growth are critically examined.
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Communicated by S. N. Atluri, 10 January 1995
This work was supported by the FAA to the Center of Excellence for Computational Modeling of Aircraft Structures at Georgia Institute of Technology, and in part by a grant from ONR.
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Naganarayana, B.P., Atluri, S.N. Strength reduction and delamination growth in thin and thick composite plates under compressive loading. Computational Mechanics 16, 170–189 (1995). https://doi.org/10.1007/BF00369779
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DOI: https://doi.org/10.1007/BF00369779