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)
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.
#1M.H. Nagaraj (Polytechnic University of Turin)H-Index: 4
#2Johannes Reiner (Deakin University)H-Index: 7
Last. Marco Petrolo (Polytechnic University of Turin)H-Index: 27
view all 5 authors...
Abstract The objective of the current work is the development of a numerical framework for the simulation of damage in composite structures using explicit time integration. The progressive damage is described using a Continuum Damage Mechanics (CDM) based material model, CODAM2, in which the damage initiation and progression are modelled using Hashin's failure criteria and crack-band theory, respectively. The structural modelling uses higher-order theories based on the Carrera Unified Formulatio...
10 CitationsSource
#1Ibrahim Kaleel (Polytechnic University of Turin)H-Index: 8
#2Erasmo Carrera (Polytechnic University of Turin)H-Index: 84
Last. Marco Petrolo (Polytechnic University of Turin)H-Index: 27
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Abstract This paper presents a novel numerical framework to simulate the progressive delamination in laminated structures based on 1D component-wise models. The proposed numerical tool is a part of the virtual testing platform built within the Carrera Unified Formulation, a hierarchical, higher-order structural framework to generate theories of structures via a variable kinematic approach. Formulated within the Lagrange polynomial CUF models, the component-wise approach models the components of ...
8 CitationsSource
#1Kangkang Wang (Beihang University)H-Index: 4
#2Libin Zhao (Beihang University)H-Index: 21
Last. Ning Hu (Chongqing University)H-Index: 60
view all 5 authors...
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...
9 CitationsSource
#1Fei Xia (JNU: Jinan University)H-Index: 1
#2Fang Jian (JNU: Jinan University)H-Index: 1
Last. Jianghong Xue (JNU: Jinan University)H-Index: 2
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Abstract In this paper, an extended first order shear deformation theory is proposed for Reissner-Mindlin laminated composite panels with internal delamination. The distinctive feature of the present theory is that a contact mechanism is involved in the governing equations based on FSDT by introducing a constitutive relation between the contact force and the transverse deflection and are expressed in terms of the displacements and the rotation functions. The proposed theory is applied to investi...
7 CitationsSource
#1Kangkang Wang (Beihang University)H-Index: 4
#2Libin Zhao (Beihang University)H-Index: 21
Last. Ning Hu (Chongqing University)H-Index: 60
view all 6 authors...
Abstract Laminated carbon fibre reinforced composite materials are very susceptible to delamination, which is one of the most serious failure modes in composite laminates. According to the requests of damage tolerance evaluation, to completely evaluate the buckling responses and failure behaviors of delaminated composites under uniaxial compression, an analytical model was established. Based on the principle of minimum potential energy and brittle damage mechanics, the analytical model incorpora...
10 CitationsSource
#1Anton Köllner (Technical University of Berlin)H-Index: 5
#2Christina Völlmecke (Technical University of Berlin)H-Index: 8
Abstract The problem of a delaminated composite plate subjected to in-plane compressive loading is investigated by employing a novel analytical framework previously developed by the authors. The framework is capable of modelling the post-buckling behaviour considering damage growth by using a set of generalized coordinates only. Therefore, in order to model the post-buckling responses of delaminated composite plates a R ayleigh –R itz formulation is employed. Thus, the post-buckling behaviour as...
12 CitationsSource
#1A. G. de Miguel (Polytechnic University of Turin)H-Index: 8
#2Ibrahim Kaleel (Polytechnic University of Turin)H-Index: 8
Last. Erasmo Carrera (Polytechnic University of Turin)H-Index: 84
view all 6 authors...
Abstract The objective of the current work is to perform a failure evaluation of fiber composite structures based on failure indices computed using the Hashin 3D failure criterion. The analysis employs 1D and 3D finite elements. 1D elements use higher-order structural theories from the Carrera Unified Formulation based on Lagrange expansions of the displacement field. The 3D model analysis exploits ABAQUS. Attention is paid to the free-edge effects, the mode of failure initiation - matrix or fib...
23 CitationsSource
#1Kangkang Wang (Beihang University)H-Index: 4
#2Libin Zhao (Beihang University)H-Index: 21
Last. Jianyu Zhang (Chongqing University)H-Index: 25
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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...
19 CitationsSource
#1S. Keshava Kumar (IISc: Indian Institute of Science)H-Index: 5
#2Dineshkumar Harursampath (IISc: Indian Institute of Science)H-Index: 13
Last. Stefano Valvano (Polytechnic University of Turin)H-Index: 18
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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...
31 CitationsSource
#1Xiaodong Chen (Tongji University)H-Index: 3
#2Zhangming Wu (Cardiff University)H-Index: 15
Last. Paul M. Weaver (UoB: University of Bristol)H-Index: 68
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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...
21 CitationsSource
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