Parameter studies and evaluation principles of delamination damage in laminated composites

Published on Jul 1, 2021in Chinese Journal of Aeronautics2.215
· DOI :10.1016/J.CJA.2020.10.022
Kangkang Wang4
Estimated H-index: 4
(Beihang University),
Libin Zhao21
Estimated H-index: 21
(Beihang University)
+ 2 AuthorsYu Gong12
Estimated H-index: 12
(Chongqing University)
Source
Abstract
Abstract Delamination represents one of the most severe failure modes in composite laminates, especially when they are subjected to uniaxial compression loads. The evaluation of the delamination damage has always been an essential issue of composite laminates for durability and damage tolerance in engineering practice. Focusing on the most typical and representative elliptical delamination issue, an analytical model simultaneously considering the conservative buckling process and non-conservative delamination propagation process is implemented. Various computational cases considering different delamination depths, directions, aspect ratios, and areas are established, and the predicted results based on the analytical model are carefully compared. Effects of these geometrical delamination parameters on the buckling, delamination propagation, and failure behaviors of composite laminates are thoroughly analyzed, and innovative evaluation principles of the delamination damage have been concluded. It is found that the delamination area is the key factor that truly affecting the failure behaviors of delaminated composites, and the local / global buckling and failure loads show clear linearity with the delamination area, whilst the delamination depth and direction only have slight effects.
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#1Kangkang Wang (Beihang University)H-Index: 4
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Abstract Delamination is one of the most serious failure modes in carbon fiber reinforced composite laminates, because it can reduce the overall stiffness, which further leads to premature structural buckling and failure at loads below the design level. Arbitrary elliptical delamination is the most representative case in engineering practice, and the delamination propagation and failure behaviors are much complicated. To completely evaluate the compressive failure behaviors of composite laminate...
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Abstract Low velocity impact (LVI) has always been a potential threaten to composite structures. This out-of-plane dynamic impact load easily leads to a dramatic increase of the strain state in the material transverse plane, which can affect the dynamic stress state and damage evolution of the composite laminate, especially for LVI with a relatively high energy. However, the strain rate effect was always neglected in existing investigations, thus introducing inevitable errors in numerical predic...
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ABSTRACTThe present paper considers the modal analysis of delaminated composite shell structures with double-curvature geometry. The finite element for shell with variable through-the-thickness kinematic is adopted for the analysis. The refined models are grouped in the Unified Formulation by Carrera (CUF) and they permit the distribution of displacements along the thickness of the multilayered shell to be accurately described. The shell element has nine nodes and the Mixed Interpolation of Tens...
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Variable angle tow (VAT) composite laminates, in which fibre orientation varies spatially in-plane in a continuous fashion yet is piecewise constant through-thickness, have been made possible by advanced automated fibre placement technology. Such designs have shown considerable potential to improve the performance of lightweight composite structures. In the present study, an analytical model is developed to study the buckling behaviour of VAT composite plates with a through-the-width or an embed...
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