Damage Analysis Of Composite Laminates Research Articles

Ordinary state-based peridynamic model for out-of-plane deformation and damage analysis of composite laminates

An ordinary state-based peridynamic (PD) model for predicting out-of-plane mechanical behaviour of composite laminates has been proposed, in which three types of PD bonds are used to describe the reinforcement properties. The non-local strain energy density and peridynamic formulations are obtained based on the principle of virtual work by using Total Lagrange formulation, and the force density is reformulated by interpolation technique. Since the Mindlin plate is regarded as the research object of this PD model, the transverse shear deformation of laminates is considered. Also, the dilatation term is included in the force density vector, and flaws in Poisson's ratio of materials can be overcome. In the proposed PD, the critical strain energy density rather than the critical curvature is adopted as the failure criterion. The capability of the developed PD model was demonstrated by the bending examples of composite laminates with different fiber orientations, and damage analysis was further conducted to demonstrate the strong capability of proposed PD model in replicating the damage process of laminates. In addition, a single-layer material point model (SLMPM) can be implemented in the proposed PD algorithm, and the computational efficiency of numerical models will be greatly improved.

Peridynamics for out-of-plane damage analysis of composite laminates

Peridynamics for out-of-plane damage analysis of composite laminates

Progressive damage analysis of composite laminates subjected to low-velocity impact using 2D layer-wise structural models

The present work deals with the progressive damage analysis of composite laminates subjected to low-velocity impact. We develop a numerical model using higher-order structural theories based on the Carrera Unified Formulation (CUF) with Lagrange polynomials and resulting in a 2D refined layer-wise model. To model damage, we use a combination of the continuum damage-based CODAM2 intralaminar damage model to account for fibre and matrix damage within the ply, and cohesive elements to account for delamination between successive composite plies. We carry out numerical assessments for the case of a linear elastic composite plate subjected to impact, to compare the current framework with standard approaches based on 3D finite element (FE) analysis. We, then, consider the elastoplastic analysis of a bimetallic laminated plate to compare the performance of the proposed layer-wise model and 3D-FE approaches, for the case of nonlinear impact analysis. The final assessment considers progressive damage due to low-velocity impact, and the results are compared with available literature data. The numerical predictions show a good correlation with reference experimental and simulation results, thus validating the current framework for impact analysis of composite structures. Comparisons of the proposed layer-wise structural models with those based on 3D finite elements demonstrate the improved computational efficiency of the CUF models in terms of model size and analysis time.

Peridynamics for predicting damage and its growth in composites

AbstractThis study concerns progressive damage analysis of composite laminates by using peridynamics. It is not limited to any fibre orientation and laminate layup. Its validity is established by comparing against the recent data generated by the Air Force Research Laboratory under the Tech Scout Project. The model simulations predict the stiffness, strength and damage progression in each ply for three different laminate layups with a circular hole under tensile/compressive loading. These predictions compare well with the experimental observations and measurements for each laminate layup.

A damage mechanics model for low-velocity impact damage analysis of composite laminates

ABSTRACTA method was developed to predict numerically the damage of composite laminates with multiple plies under low-velocity impact loading. The Puck criterion for 3D stress states was adopted to model the intralaminar damage including matrix cracking and fibre breakage, and to obtain the orientation of the fracture plane due to matrix failure. According to interlaminar delamination mechanism, a new delamination criterion was proposed. The influence of transverse and through-thickness normal stress, interlaminar shear stress and damage conditions of adjacent plies on delamination was considered. In order to predict the impact-induced damage of composite laminates with more plies quickly and efficiently, an approach, which can predict the specific damage of several plies in a single solid element, was proposed by interpolation on the strains of element integration points. Moreover, the proposed model can predict specific failure modes. A good agreement between the predicted delamination shapes and sizes and the experimental results shows correctness of the developed numerical method for predicting low-velocity impact damage on composite laminates.

Development of a Finite Element Model for Progressive Damage Analysis of Composite Laminates Subjected to Low Velocity Impact

Fiber reinforced polymer laminates are susceptible to transverse low velocity impact which can cause significant damages, such as matrix cracks, delamination and fiber breakage. A 3-Dimensional (3-D) finite element model (FEM) is presented for the progressive damage analysis of fiber reinforced laminates subjected to low velocity impact. The constitutive equations of material used in the FEM are based on the continuum damage mechanics (CDM). The modified HASHIN failure criterions are used in the material model to detect the initiation of all the failure modes of laminates. A simplified material stiffness degradation scheme is used to characterize the material degradation due to damages. The failure criterions and material degradation scheme have been incorporated in the software ABAQUS/Explicit through the user defined material subroutine VUMAT. The available experiments of thin carbon fiber reinforced epoxy laminates subjected to low velocity impact were used to validate the developed FEM. The good agreement of the impact contact force history and damage area between the analysis results and the experimental data shows the validation of the developed FEM.

Implementation of a micro-meso approach for progressive damage analysis of composite laminates

The mismatch of ply orientations in composite laminates can cause high interlaminar stress concentrations near the free edges. Evaluation of these interlaminar stresses and their role in the progressive damage analysis of laminates is desirable. Recently, the authors developed a new method to relate the physically based micromechanics approach with the meso-scale CDM considering matrix cracking and induced delamination. In this paper, the developed method is applied for the analysis of edge effects in various angle-ply laminates such as <TEX>$[10/-10]_{2s}$</TEX>, <TEX>$[30/-30]_{2s}$</TEX> and <TEX>$[45/-45]_{2s}$</TEX> and comparing the results with available traditional CDM and experimental results. It is shown that the obtained stress-strain behaviors of laminates are in good agreement with the available experimental results and even in better agreement than the traditional CDM results. Variations of the stresses and stiffness components through the laminate thickness and near the free edges are also computed and compared with the available CDM results.