A 3D PROGRESSIVE MATERIAL DAMAGE MODEL FOR FE SIMULATION OF MACHINING A UNIDIRECTIONAL FRP COMPOSITE

The Bi-directional Evolutionary Structural Optimisation (BESO) method is a numerical topology optimisation method developed for use in finite element analysis. This paper presents a particular application of the BESO method to optimise the energy absorbing capability of metallic structures. The optimisation objective is to evolve a structural geometry of minimum mass while ensuring that the kinetic energy of an impacting projectile is reduced to a level which prevents perforation. Individual elements in a finite element mesh are deleted when a prescribed damage criterion is exceeded. An energy absorbing structure subjected to projectile impact will fail once the level of damage results in a critical perforation size. It is therefore necessary to constrain an optimisation algorithm from producing such candidate solutions. An algorithm to detect perforation was implemented within a BESO framework which incorporated a ductile material damage model.

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The effect of temperature on fatigue strength and damage of FRP composite laminates

10.32920/ryerson.14645559.v1 ◽

2021 ◽

Author(s):

Hossein Mivehchi

Keyword(s):

Tensile Strength ◽

Fatigue Strength ◽

Ultimate Tensile Strength ◽

Fatigue Damage ◽

Composite Laminates ◽

Damage Model ◽

Effect Of Temperature ◽

Temperature Dependent ◽

Frp Composites ◽

Frp Composite

The present study intends to investigate the effect of temperature on cumulative fatigue damage of laminated fibre-reinforced polymer (FRP) composites. The effect of temperature on fatigue damage is formulated based on a previously proposed residual stiffness fatigue damage model. The fatigue strength of FRP composite laminates is also formulated to have temperature dependent parameters. The research work is divided into three main parts; the first part reviews the fatigue damage mechanism is fibre-reinforced composites based on stiffness degradation. The recent residual stiffness of Varvani-Shirazi was used as the backbone structure of damage analysis in this thesis. This model is capable of damage assessment while the effects of maximum stress, stress ratio and fibre orientation of FRP composites were recognized. The Varvani-Shirazi damage model was further developed to assess fatigue damage of FRP composites at various temperatures (T). Inputs of the damage model are temperature dependent parameters including Young's modulus (E), ultimate tensile strength(ðult) and fatigue life (Nf). As the next part of the proposed analysis, the temperature dependency of each parameter is formulated, and the relations of E-T and ðult-T are substituted in the Varvani-Shirazi fatigue model. Finally, all terms and equations are evaluated with the experimental data available in the literature. Six sets fatigue data were used in this thesis to evaluate fatigue of FRP specimens. The predicted results were found to be in good agreement with the experimentally obtained data. The proposed fatigue damage model was found promising to predict the fatigue damage of unidirectional (UD) and women FRP composites at different temperatures. Temperature dependant parameters of Young's modulus, ultimate tensile strength, and S-N diagram were also found to be responsive when used of UD, cross-ply, and quasi-isotropic FRP laminates.

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Simple Progression Law in Predicting the Damage Onset and Propagation in Composite Notched Laminates

International Journal of Engineering & Technology ◽

10.14419/ijet.v7i4.26.22160 ◽

2018 ◽

Vol 7 (4.26) ◽

pp. 163

Author(s):

Mohd Suhairil Meon ◽

Narasimha Rao Mekala ◽

Kai-Uwe S Schroeder

Keyword(s):

Damage Model ◽

Three Dimensional ◽

Failure Criteria ◽

Constitutive Law ◽

Fiber Reinforced Polymer ◽

Damage Initiation ◽

Frp Composite ◽

Reinforced Polymer ◽

Ultimate Failure ◽

Progressive Damage Model

The aim of this article is to simulate the damage initiation and progression in unidirectional (UD) laminates. A three-dimensional (3D) failure criteria of Puck incorporated with degradation scheme is developed. Two types of degradation law known as sudden degradation are used to predict the damage progression in UD laminates. The establishment of constitutive law in progressive damage model (PDM) is achieved through implementation of user subroutines in Abaqus. The failure analysis is applied to various composite stacking sequences and geometries, as well as different fiber reinforced polymer (FRP) composite materials. The comparative studies revealed that the predicted ultimate failure load agree well with those available in the literature.

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FEA Simulation of Clinching Process Based on GTN Damage Model

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.652-654.2254 ◽

2013 ◽

Vol 652-654 ◽

pp. 2254-2260 ◽

Cited By ~ 1

Author(s):

Bai Jun Shi ◽

Shu Hui Liao ◽

Song Peng ◽

Hang Li

Keyword(s):

Simulation Model ◽

Sheet Material ◽

Damage Model ◽

Model Parameters ◽

Material Damage ◽

Gtn Damage Model ◽

Fea Simulation ◽

Simulation Results ◽

Clinch Joining ◽

Joining Process

In this work, the Gurson-Tvergaard-Needleman (GTN) damage model is adopted to depict the material damage during the clinch joining process in a simulation-based theoretical model. The parameters of the GTN model which influence the void nucleation, growth and coalescence are identified. Their values of a specific material, C45E4 (ISO) steel, have been determined after carefully comparing the simulation results with the real sheet material tensile test. The established GTN damage model parameters are then imported into the simulation model to investigate the material damage during the mechanical clinch joining process. The Finite Element Analysis (FEA) simulation results show promising, because the material’s initial damage position can be located and analyzed. For a given design, the initial fracture point was predicted which is located on the inner side of the clinched joint neck of the upper sheet, which matches with the results of the experimental test very well. It can be concluded that the incorporation of GTN damage model has extend the capability of the simulation model.

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Progressive Damage Model of FRP Composite Laminates with Central Hole

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.194-196.1581 ◽

2011 ◽

Vol 194-196 ◽

pp. 1581-1585

Author(s):

Chong Qiang Sun ◽

Jian Yu Zhang ◽

Bin Jun Fei

Keyword(s):

Composite Laminates ◽

Failure Process ◽

Damage Model ◽

Failure Criteria ◽

Numerical Results ◽

Central Hole ◽

Progressive Damage ◽

Element Mesh ◽

Damage Models ◽

Frp Composite

Progressive damage method is adopted to predict the static mechanics properties of FRP composite laminates with central hole. Progressive damage models with three different 3D failure criteria and material degradation models are established and analyzed via a user defined subroutine embedded into the general FEA package. Numerical results indicate that all the three 3D failure criteria can simulate the failure process of FRP laminates with central hole, but the final failure load is different. Degradation coefficient and the finite element mesh have significant effect on the numerical results.

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The effect of temperature on fatigue strength and damage of FRP composite laminates

10.32920/ryerson.14645559 ◽

2021 ◽

Author(s):

Hossein Mivehchi

Keyword(s):

Tensile Strength ◽

Fatigue Strength ◽

Ultimate Tensile Strength ◽

Fatigue Damage ◽

Composite Laminates ◽

Damage Model ◽

Effect Of Temperature ◽

Temperature Dependent ◽

Frp Composites ◽

Frp Composite

The present study intends to investigate the effect of temperature on cumulative fatigue damage of laminated fibre-reinforced polymer (FRP) composites. The effect of temperature on fatigue damage is formulated based on a previously proposed residual stiffness fatigue damage model. The fatigue strength of FRP composite laminates is also formulated to have temperature dependent parameters. The research work is divided into three main parts; the first part reviews the fatigue damage mechanism is fibre-reinforced composites based on stiffness degradation. The recent residual stiffness of Varvani-Shirazi was used as the backbone structure of damage analysis in this thesis. This model is capable of damage assessment while the effects of maximum stress, stress ratio and fibre orientation of FRP composites were recognized. The Varvani-Shirazi damage model was further developed to assess fatigue damage of FRP composites at various temperatures (T). Inputs of the damage model are temperature dependent parameters including Young's modulus (E), ultimate tensile strength(ðult) and fatigue life (Nf). As the next part of the proposed analysis, the temperature dependency of each parameter is formulated, and the relations of E-T and ðult-T are substituted in the Varvani-Shirazi fatigue model. Finally, all terms and equations are evaluated with the experimental data available in the literature. Six sets fatigue data were used in this thesis to evaluate fatigue of FRP specimens. The predicted results were found to be in good agreement with the experimentally obtained data. The proposed fatigue damage model was found promising to predict the fatigue damage of unidirectional (UD) and women FRP composites at different temperatures. Temperature dependant parameters of Young's modulus, ultimate tensile strength, and S-N diagram were also found to be responsive when used of UD, cross-ply, and quasi-isotropic FRP laminates.

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Constitutive Modelling for Anisotropic Damage in Woven E-Glass Reinforcements

The Open Materials Science Journal ◽

10.2174/1874088x01711010009 ◽

2017 ◽

Vol 11 (1) ◽

pp. 9-21

Author(s):

Ping Yang ◽

Ying Tong

Keyword(s):

Composite Laminates ◽

Damage Model ◽

Fixed Time ◽

Constitutive Modelling ◽

Anisotropic Damage ◽

Material Damage ◽

Lower Velocity ◽

Damage Area ◽

Gfrp Composite ◽

Damage Process

It is easy for composite laminates to be damaged by relative lower velocity impact which could give rise to internal delamination that will strongly weaken the compressive strength of laminates. In order to predict the occurrence of matrix failure, the elastic-brittle behaviors of fiber-reinforced composites were modeled constitutively by an anisotropic damage model. The dynamic tensile testing was performed at a constant velocity of 2 mm/min until the sample broke to achieve the mechanical parameters of E-glass reinforcements. The elastic constitutive equation and the constitutive damage model were obtained on basis of the fundamental theory of mechanics about the orthotropic constitutive of reinforcements. The methodology for this constitutive model which is developed by Hashin considered both the effect of fiber and matrix failure. Then, the developed constitutive equations were incorporated into the FE (finite element) codes, ABAQUS, through the user subroutine module to simulate the process of projectile impacting GFRP composite laminates. The results show that the material deformation reaches a maximum at 24 μs, then occurs rebound with the increase of the time. The stress of reinforcements traverse section linearly increases outward from 0 MPa to 509.8 MPa. Material damage area increases with the prolonging of time, and for a fixed time, material damage gradually increases from the edges to the center and reaches a constant value of 1, which means the rupture of the damage process.

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