scholarly journals Influence of Failure Criteria and Intralaminar Damage Progression Numerical Models on the Prediction of the Mechanical Behavior of Composite Laminates

2021 ◽  
Vol 5 (12) ◽  
pp. 310
Author(s):  
Aniello Riccio ◽  
Concetta Palumbo ◽  
Valerio Acanfora ◽  
Andrea Sellitto ◽  
Angela Russo
Keyword(s):  
Mechanical Behavior ◽  
Composite Laminates ◽  
Damage Evolution ◽  
Damage Mechanics ◽  
Numerical Models ◽  
Failure Criteria ◽  
Shear Loading ◽  
Local Damage ◽  
Loading Conditions ◽  
Numerical Predictions

This work evaluates the effectiveness of commonly adopted local damage evolution methods and failure criteria in finite element analysis for the simulation of intralaminar damage propagation in composites under static loading conditions. The proposed numerical model is based on a User Defined Material subroutine (USERMAT) implemented in Ansys. This model is used to predict the evolution of damage within each specific lamina of a composite laminate by introducing both sudden and gradual degradation rules. The main purpose of the simulations is to quantitatively assess the influence of the adopted failure criteria in conjunction with degradation laws on the accuracy of the numerical predictions in terms of damage evolution and failure load. The mechanical behavior of an open hole tension specimen and of a notched stiffened composite panel under shear loading conditions have been numerically simulated by Progressive Damage Models (PDM). Different failure criteria have been implemented in the developed Ansys USERMAT, together with sudden and gradual degradation rules based on the Continuum Damage Mechanics (CDM) approach. Numerical results have been validated against experimental data to assess the effects of the different failure criteria and damage evolution law on the global mechanical response and local damage predictions in composite laminates.

Progressive Damage of Solder Joints: Modeling, Implementation and Verification

2006 ◽  
Author(s):  
Zhengfang Qian
Keyword(s):  
Cyclic Loading ◽  
Damage Evolution ◽  
Damage Mechanics ◽  
Mathematical Structure ◽  
Failure Criteria ◽  
Progressive Damage ◽  
Electronic Packages ◽  
Flip Chips ◽  
Bga Package ◽  
Virtual Qualification

This paper presents a damage mechanics-based methodology for the progressive damage and virtual qualification of advanced electronic packages such as BGAs, DCAs, CSPs, and Flip-chips. The key technique is to implement the material nonlinearity into commercially available software tools. A unified viscoplastic constitutive framework with the damage evolution and failure criteria has been successfully implemented into the ABAQUS® code to model time-rate-temperature dependent material properties. The framework has been successfully applied to solder alloys, polymer films, and underfill encapsulants. The mathematical structure and numerical algorithm development of the unified constitutive framework as well as the key implementation techniques for commercial FEA codes have been summarized in this paper. Both crack initiation and propagation of a solder joint with damage evolution under mechanical cyclic loading have been demonstrated. Virtual simulations of TSOP component failure under mechanical cyclic loading and BGA package under thermal cyclic loading have also been presented.

GLOBAL-LOCAL PROGRESSIVE DAMAGE ANALYSIS OF COMPOSITE LAMINATES USING LAYER-WISE HIGHER-ORDER STRUCTURAL MODELSv

2021 ◽  
Author(s):  
MANISH H. NAGARAJ ◽  
ERASMO CARRERA ◽  
MARCO PETROLO
Keyword(s):  
Composite Laminates ◽  
Damage Mechanics ◽  
Numerical Models ◽  
Higher Order ◽  
Computational Time ◽  
Progressive Damage ◽  
Damage Analysis ◽  
Isotropic Composite ◽  
Integration Schemes ◽  
Laminated Structures

The objective of the current work is to develop a global-local framework for the progressive damage analysis of composite laminated structures. The technique involves two sequential analyses—an initial low-fidelity 3D-FE based linear analysis of the global structure, followed by the local nonlinear analysis of critical regions where damage is likely to occur. The numerical models used for the local analysis are developed using higher-order layer-wise structural theories obtained via the Carrera Unified Formulation. Composite damage is modelled using the CODAM2 model based on continuum damage mechanics, and the nonlinear problem is solved using explicit time integration schemes. Preliminary assessments are carried out to validate the proposed global-local framework by considering open-hole tensile specimens of quasi-isotropic composite laminates. Both full-scale CUF models and the proposed global-local approach are used to predict the tensile strength of the specimen. It is shown that the obtained results are in good agreement with experiment data, thus validating the framework, and a multi-fold improvement in computational time is demonstrated.

Application and Analysis of Plane Woven C/SiC Composites Based on Continuum Damage Mechanics

2012 ◽  
Vol 490-495 ◽  
pp. 3916-3919 ◽  
Author(s):  
Yan Jun Chang ◽  
Ke Shi Zhang ◽  
Gui Qiong Jiao ◽  
Jian Yun Chen
Keyword(s):  
Constitutive Model ◽  
Damage Evolution ◽  
Damage Mechanics ◽  
Kinematic Hardening ◽  
Ceramic Matrix Composites ◽  
Shear Loading ◽  
Internal Variables ◽  
Anisotropic Damage ◽  
Initial Modulus ◽  
Sic Composites

The aim of this article was to propose a macroscopic damage model, which describes the nonlinear behavior observed on woven C/SiC ceramic matrix composites. The model was built within a thermodynamic framework with internal variables. The anisotropic damage evolution processes of the material were described by nonlinear damage isotropic and kinematic hardening functions in this model. The anisotropic damage and damage coupling were considered with a damage yield function including anisotropic coefficients. Using the principle of energy equivalence, the damage variables were defined by the unloading modulus and initial modulus. The damage variable and the irrecoverable strain induced by micro-crack propagation were deduced by thermodynamics. The constants of constitutive model were identified and the damage evolution processes under tensile and shear loading. Uniaxial tension and shear tests had been used to valid the constitutive model to C/SiC composites.

Physically based damage models for laminated composites

2003 ◽  
Vol 217 (3) ◽  
pp. 163-199 ◽  
Author(s):  
L N McCartney
Keyword(s):  
Composite Laminates ◽  
Damage Mechanics ◽  
Laminated Composites ◽  
Damage Model ◽  
Shear Loading ◽  
Analytical Models ◽  
Element Analysis ◽  
Plane Shear ◽  
Triaxial Loading ◽  
Physically Based

The computing power that is available for engineering calculation continues to grow at a dramatic pace. Engineers in industry want to have seamless models that can be used to design across the scale range from atoms to structures, including simulation of the manufacturing process. A limited aspect of this wish is the requirement to deal effectively with the progressive growth of microstructural damage in composites and its effect on both property degradation and the catastrophic failure event. This paper reviews progress that is being made at the National Physical Laboratory (NPL) with the development and validation of physically based damage growth models for laminated composites. The review includes: (a) prediction of undamaged ply properties determined from the properties of the fibre and the matrix, with emphasis on comparison of analytical models with each other, and with finite and boundary element solutions; (b) discussion of various stress transfer models, and their validation, that have been developed for application to the prediction of the properties of composite laminates having ply crack damage; (c) prediction of ply cracking in multiple-ply cross-ply laminates subject to triaxial loading (without shear) and bending; (d) prediction of ply cracking in general symmetric laminates subject to combined triaxial loading and in-plane shear loading; (e) consideration in a damage mechanics context of progressive ply crack formation in general symmetric laminates subject to thermal residual stresses and general in-plane loading, where an important new methodology is described that results from attempting to develop a continuum damage model from a physically based discrete ply cracking model based on energy concepts; (f) discussion of how the models might be integrated into finite element analysis (FEA) systems to enable strain softening in structures to be adequately modelled. The paper also includes statements concerning the status of the various models in relation to alternative approaches, and to model validation.

Modelling Damage of Composite Laminates with Different Stacking Sequences

2013 ◽  
Vol 698 ◽  
pp. 1-10
Author(s):  
S. Benbelaid ◽  
B. Bezzazi ◽  
A. Bezazi
Keyword(s):  
Composite Laminates ◽  
Damage Mechanics ◽  
Progressive Failure ◽  
Damage Model ◽  
Continuum Damage Mechanics ◽  
Failure Criteria ◽  
Continuum Damage ◽  
Damage Development ◽  
Numerical Application ◽  
Element Analysis

This paper considers damage development mechanisms in composite laminates subjected to tensile loading. The continuum damage mechanics is the most widely used approach to capture the non linear behaviour of laminates due to cracking. In this study, a continuum damage model based on ply failure criteria, which is initially proposed by Ladevèze has been extended to cover all plies failures mechanisms using an accurate numerical model to predict the equivalent damage accumulation. However, this model requires a reliable representation of the elementary damage mechanisms which can be produced in the composite laminate. To validate this model, a numerical application has been carried on the cross-ply laminates of type [0n/90m]s..A shear lag model was adapted to calculate the average stress of the 0° and 90° plies. The solution presented is obtained by using finite element analysis which implements progressive failure analysis. The effect of the stacking sequences has been done by varying the thickness of the 90° plies.

scholarly journals Analytical model for determining effective stiffness and mechanical behavior of polymer matrix composite laminates using continuum damage mechanics

2020 ◽  
Vol 29 (10) ◽  
pp. 1512-1542
Author(s):  
Sota Onodera ◽  
Tomonaga Okabe
Keyword(s):  
Analytical Model ◽  
Composite Laminates ◽  
Damage Mechanics ◽  
Continuum Damage Mechanics ◽  
Shear Loading ◽  
Effective Stiffness ◽  
Continuum Damage ◽  
Transverse Tensile ◽  
Stiffness Reduction ◽  
Fiber Breaks

The present paper proposes a new analytical model for predicting the effective stiffness of composite laminates with fiber breaks and transverse cracks. The model is based on continuum damage mechanics and the classical laminate theory. We derived damage variables describing stiffness reduction due to fiber breaks and its maximum value during ultimate tensile failure from the global load-sharing model. Furthermore, a simplified analytical model is presented for obtaining two damage variables for a cracked ply subjected to transverse tensile loading or in-plane shear loading. This model was developed assuming that the displacement field of the longitudinal direction can be expressed in the form of a quadric function by loosening the boundary condition for the governing differential equation. For verifying the developed model, the elastic constants of damaged composite laminates were predicted for cross-ply and angle-ply laminates and compared with the finite element analysis results. As for the appropriate expression of the effective elastic stiffness matrix of the damaged ply, we verified four types of effective compliance/stiffness matrices including the Murakami, Yoshimura, Li, and Maimí models. We found the Maimí model to be the most appropriate among these four models. Moreover, we successfully simplified the expressions for damage variables in the complicated infinite series obtained in our previous study. We also proved that this could contribute toward improving the accuracy of our analysis. After verifying the present model, the stress–strain response and failure strength of carbon- or glass-fiber-reinforced plastic cross-ply laminates were predicted using Maimí’s compliance model and the simplified damage variables.

Effect of intra-yarn hybridisation and fibre architecture on the impact response of composite laminates: Experimental and numerical analysis

2021 ◽  
pp. 095440622110373
Author(s):  
Hussein Dalfi
Keyword(s):  
Numerical Analysis ◽  
Composite Laminates ◽  
Composite Structures ◽  
Damage Mechanics ◽  
Failure Criteria ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Element Analysis ◽  
Velocity Impact ◽  
The Impact

Advanced composite laminates (i.e. glass composite laminates) are highly susceptible to low velocity impact, and the induced damage failures substantially reduced their residual mechanical properties and safe-service life during their application. Therefore, experiments and simulation efforts to predict their low-velocity impact damages and energy absorbing have significant importance in composite structures design. In this regards, experimental and finite element analysis (FEA) with aiding Abaqus software were respectively performed to investigate the influence of yarn hybridisation on the response of composite laminates under low velocity impact. The hybrid yarns, which consisted of S-glass and polypropylene yarns have been used to manufacture two types of composites; non-crimp cross-ply hybrid yarns and twill hybrid fabric composites. Additionally, for comparison, the non-crimp cross-ply and twill fabric composite laminates have been made from glass fibres only. The vacuum infusion resin process has been adopted to manufacture these composite laminates. The impact performance of composite laminates has been investigated using low-velocity impact at 15 J, 35, and 50 impact energy levels. The numerical analysis was executed using Abaqus/Explicit and Hashin failure criteria and continuum damage mechanics by using homogenous shell were adopted to simulate the intra-laminar damage in layers. Meanwhile, standard cohesive inter-laminar interfaces that inserted between composite layers with quadratic stress failure criteria have been used to model delamination failures. The numerical results regarding impact force-time, displacement–time and energy-time histories plots, as well as the damage evolution behaviour of matrix crack and fibre fracture, presented an agreement with experimental results.

Experimental verification of the virtual isotropic material concept for the last-ply-failure of U-notched quasi-isotropic E-glass/epoxy composite laminates under tension-shear loading

2020 ◽  
pp. 152808372095520
Author(s):  
Ali Reza Torabi ◽  
Ebrahim Pirhadi
Keyword(s):  
Composite Laminates ◽  
Isotropic Material ◽  
Mixed Mode ◽  
Epoxy Composite ◽  
Laminated Composite ◽  
Shear Loading ◽  
Mode I ◽  
Loading Conditions ◽  
Damage Initiation ◽  
Material Concept

Fracture investigation of U-notched E-glass/epoxy laminated composite specimens with various notch root radii is performed under mixed mode I/II loading conditions both experimentally and theoretically. Rectangular E-glass/epoxy composite laminates with two numbers of ply (8-ply and 16-ply) and the quasi-isotropic [0/90/+45/–45]s lay-up configuration are fabricated for conducting the fracture tests. To measure the damage initiation angles (DIAs) and the last-ply-failure (LPF) loads of the fabricated composite samples containing horizontal and inclined U-notches, as the main aim of this study, the specimens are loaded under tension by the universal testing machine. The experimental LPF loads are theoretically predicted with the aid of a novel concept, called the Virtual Isotropic Material Concept (VIMC). The proposed VIMC is linked to the two well-known stress-based fracture criteria, namely the maximum tangential stress (MTS) and the mean stress (MS) criteria, in the context of the linear elastic notch fracture mechanics (LENFM). It is proved that the two combined criteria, namely the VIMC-MTS and VIMC-MS criteria, can predict well the LPF loads of the U-notched laminated composite specimens tested under mixed mode I/II loading conditions. One of the important merits of these new criteria is that the predictions of the LPF loads of the U-notched composite specimens are performed without complicated and time-wasting ply-by-ply damage analyses.

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