# Modelling of Hybrid Materials and Interface Defects through Homogenization Approach for the Prediction of Effective Thermal Conductivity of FRP Composites Using Finite Element Method

Authors: C. Mahesh; K. Govindarajulu; V. Balakrishna Murthy
Journal: Advances in Materials Science and Engineering
 (2013)

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## Abstract

Finite element method is effectively used to homogenize the thermal conductivity of FRP composites consisting of hybrid materials and fibre-matrix debonds at some of the fibres.  The homogenized result at microlevel is used to determine the property of the layer using macromechanics principles; thereby, it is possible to minimize the computational efforts required to solve the problem as in state through only micromechanics approach.  The working of the proposed procedure is verified for three different problems: (i) hybrid composite having two different fibres in alternate layers, (ii) fibre-matrix interface debond in alternate layers, and (iii) fibre-matrix interface debond at one fibre in a group of four fibres in one unit cell.  It is observed that the results are in good agreement with those obtained through pure micro-mechanics approach.


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## Body

## 1. Introduction

Composite materials are extensively used in many fields of engineering such as aerospace, electronic packaging, reactor vessels, and turbines, due to light weight, high strength, long durability, stability against chemical reaction, tailorable properties, and so forth. FRP composites can be designed as heat conductors for enhancing heat transfer rate and also for insulation purpose; this depends on the thermal properties, volume fraction, orientation, and so forth, of each constituent of the composite. The effective thermal conductivity and other thermophysical properties of composites have been a topic of considerable theoretical, experimental, and numerical interest from long period.Composite materials are nonhomogeneous and exhibit anisotropic response due to structural and thermal loads. Analysis of a composite structure as in state of heterogeneity by providing the material properties of constituent materials is mathematically complex, and therefore theories such as micromechanics and macromechanics are developed for the theoretical analysis. The homogenized properties of a composite lamina obtained from micromechanical theories are used for the macromechanical analysis of a composite made of several individual laminas stacked in a specified manner.The micromechanical theories select a particular portion of the composite known as “Representative Volume Elements” (RVE) and find the properties of RVE which are considered to be lamina properties. In this approach, there are many assumptions such as fibres which are arranged in a particular pattern (square/hexagonal) in a matrix, no voids in the matrix, all fibres are of uniform cross-section and perfectly aligned, the interface between the fibre and matrix is perfectly or totally debond; this leads to much deviation of theoretical and experimental results. Numerical approaches such as Finite Element Method (FEM) are developed to overcome some of the assumptions of micromechanical theories but still not explored in addressing many complexities in micromechanical approach. Though FEM is an approximate method, it can be effectively used after proper mesh refinement and validation.Aligned fibre composite laminates are frequently used in beam, plate, or shell form. The axial thermal conductivity (in the fibre direction) of each lamina is satisfactorily predicted by a simple rule of mixtures Chawla [1]. Prediction of through-thickness thermal conductivity is more problematic. Yet this is important, since heat sources one side of the laminate often create a through-thickness temperature gradient.Earlier several researchers studied thermal conductivities of composites by experimental, theoretical, and numerical approaches. Prediction of effective transverse thermal conductivity of fibre reinforced composites is made for several models, such as experimental determination of effective thermal conductivity of aligned fibre composite of Chamis [2], thermal conductivity of constituents of FRCL by backout method of Al-Sulaiman et al. [3], simple thermal resistance models of Chawla, Springer and Tsai [1, 4], as well as sophisticated conduction models of Rayleigh and Lu [5, 6] and interface resistance models of Hasselman and Johnson, Farmer and Covert, Zou et al., Benveniste [7–10], 2D numerical model of Islam and Pramila, [11], 3D numerical model of Rao et al. [12], 2D thermal contact resistance model of Ramani and Vaidyanathan, [13]. Hybrid composites are also playing a dominant role by adding desirable properties which are lagging with monofibre composites by Jawaid and Abdul Khalil [14].In the present analysis, a 3D FEM is proposed to address various nonsimilarities in the unit cells at microlevel and developing equivalence between micro- and macromechanical approaches through some of the examples of heat conduction. Three cases are considered for present study: case (i) hybrid composite constituting two different thermal conductivity fibres and matrix, case (ii) composite with alternate layers of fibres fully debonded, and case (iii) composite with one in set of four fibres of a unit cell is fully debonded.


## 2. Problem Modelling

### 2.1. Geometric Modelling

Figures1, 3, and 5 represent the microlevel view of case (i) hybrid composite constituting two different thermal conductivity fibres and matrix, case (ii) composite with alternate layers of fibres fully debonded, and case (iii) composite with one in set of four fibres of a unit cell debonded, respectively. Because of high degree of symmetry in the alignment of fibres, thermal loading, one-fourth model is used for the analysis as shown in Figures 2 and 4. For case (iii), even though material and geometric symmetry exists, due to non-symmetric thermal loading a full model is taken for the analysis as shown in Figure 6. Dimensions considered for the analysis are a=100 units, b=100 units, radius of fibres corresponds to volume fractions ranging from 0.1 to 0.7.Figure 1
Concept of square unit cell for aligned pattern of hybrid composite with two different types of fibres.Figure 2
One-fourth model of unit cell for aligned pattern of fibres.Figure 3
Concept of square unit cell for aligned pattern of composite with alternate layers of debonded fibres.Figure 4
One-fourth model of unit cell for composite with alternate layers of debonded fibres.Figure 5
Concept of square unit cell for aligned pattern of composite with one in set of four fibres of unit cell totally debonded.Figure 6
Full model for aligned pattern of composite with one in set of four fibres of unit cell totally debonded.In macromechanics approach for first two cases, two blocks are modelled one over the other. For case (i) one block represents fibre1 and matrix portion and the other block is for fibre2 and matrix portion. Case (ii) one block represents total debonded fibre matrix and other perfectly bonded fibre matrix, whereas for case (iii) four blocks are modelled in square pattern. One block represents debonded fibre and matrix portion and other three blocks for perfectly bonded fibre matrix. Surfaces at the junction of blocks are merged for heat transfer connectivity without any interfacial thermal barrier.


### 2.2. Finite Element Modelling

The problem is modelled in commercial Finite Element Software ANSYS 12 [15]. A 3D quadratic brick element having 20 nodes with a single degree of freedom (temperature) at each node, named SOLID90, is used for discretization of the constituents. For hybrid composite two material properties are assigned for fibre1 and fibre2, whereas for case (ii) and case (iii) only one material property is assigned for fibres. CONTA174 and TARGE170 elements of ANSYS software are used for studying interface thermal contact behaviour between fibre and matrix. The finite element mesh is properly refined, and converged results are verified with Hasselman-Johnson and Farmer-Covert models for perfect bond and total debond at fibre-matrix interfaces. Results are present in Section 3. Figure 7 represents the Geometry and FE mesh of a 3D model for case (i) and case (ii) and Figure 8 represents the Geometry and FE mesh of a 3D model for case (iii).Figure 7
Geometry and FE mesh of a 3D model for case (i) and case (ii).Figure 8
Geometry and FE mesh of a 3D model for case (iii).


### 2.3. Boundary Conditions

Temperature difference (dT) of 100°C is maintained on two isothermal surfaces perpendicular to heat flow direction. All other surfaces are subjected to insulation boundary conditions. For debond between fibre and matrix contact conductance hc=1E-6 and for perfect contact between fibre and matrix contact conductance hc=1E6 are taken.


### 2.4. Material Properties

For the validation of the models developed in the present analysis, the following properties of fibres and matrix [2] are considered.Polyimide matrix with thermal conductivityKm=0.19 W/mK.(T-300) Carbon fibre with thermal conductivityKf1=8.365218 W/mK.For all the three cases of the study, matrix is polyimide matrix.For the hybrid model, fibre1 : fibre2 : matrix thermal conductivity ratios used are 100 : 10 : 1, 80 : 8 : 1, 60 : 6 : 1, and 40 : 4 : 1.For the debond models, fibre thermal conductivities range from 0.14 W/mK to1E6 W/mK.


## 2.1. Geometric Modelling

Figures1, 3, and 5 represent the microlevel view of case (i) hybrid composite constituting two different thermal conductivity fibres and matrix, case (ii) composite with alternate layers of fibres fully debonded, and case (iii) composite with one in set of four fibres of a unit cell debonded, respectively. Because of high degree of symmetry in the alignment of fibres, thermal loading, one-fourth model is used for the analysis as shown in Figures 2 and 4. For case (iii), even though material and geometric symmetry exists, due to non-symmetric thermal loading a full model is taken for the analysis as shown in Figure 6. Dimensions considered for the analysis are a=100 units, b=100 units, radius of fibres corresponds to volume fractions ranging from 0.1 to 0.7.Figure 1
Concept of square unit cell for aligned pattern of hybrid composite with two different types of fibres.Figure 2
One-fourth model of unit cell for aligned pattern of fibres.Figure 3
Concept of square unit cell for aligned pattern of composite with alternate layers of debonded fibres.Figure 4
One-fourth model of unit cell for composite with alternate layers of debonded fibres.Figure 5
Concept of square unit cell for aligned pattern of composite with one in set of four fibres of unit cell totally debonded.Figure 6
Full model for aligned pattern of composite with one in set of four fibres of unit cell totally debonded.In macromechanics approach for first two cases, two blocks are modelled one over the other. For case (i) one block represents fibre1 and matrix portion and the other block is for fibre2 and matrix portion. Case (ii) one block represents total debonded fibre matrix and other perfectly bonded fibre matrix, whereas for case (iii) four blocks are modelled in square pattern. One block represents debonded fibre and matrix portion and other three blocks for perfectly bonded fibre matrix. Surfaces at the junction of blocks are merged for heat transfer connectivity without any interfacial thermal barrier.


## 2.2. Finite Element Modelling

The problem is modelled in commercial Finite Element Software ANSYS 12 [15]. A 3D quadratic brick element having 20 nodes with a single degree of freedom (temperature) at each node, named SOLID90, is used for discretization of the constituents. For hybrid composite two material properties are assigned for fibre1 and fibre2, whereas for case (ii) and case (iii) only one material property is assigned for fibres. CONTA174 and TARGE170 elements of ANSYS software are used for studying interface thermal contact behaviour between fibre and matrix. The finite element mesh is properly refined, and converged results are verified with Hasselman-Johnson and Farmer-Covert models for perfect bond and total debond at fibre-matrix interfaces. Results are present in Section 3. Figure 7 represents the Geometry and FE mesh of a 3D model for case (i) and case (ii) and Figure 8 represents the Geometry and FE mesh of a 3D model for case (iii).Figure 7
Geometry and FE mesh of a 3D model for case (i) and case (ii).Figure 8
Geometry and FE mesh of a 3D model for case (iii).


## 2.3. Boundary Conditions

Temperature difference (dT) of 100°C is maintained on two isothermal surfaces perpendicular to heat flow direction. All other surfaces are subjected to insulation boundary conditions. For debond between fibre and matrix contact conductance hc=1E-6 and for perfect contact between fibre and matrix contact conductance hc=1E6 are taken.


## 2.4. Material Properties

For the validation of the models developed in the present analysis, the following properties of fibres and matrix [2] are considered.Polyimide matrix with thermal conductivityKm=0.19 W/mK.(T-300) Carbon fibre with thermal conductivityKf1=8.365218 W/mK.For all the three cases of the study, matrix is polyimide matrix.For the hybrid model, fibre1 : fibre2 : matrix thermal conductivity ratios used are 100 : 10 : 1, 80 : 8 : 1, 60 : 6 : 1, and 40 : 4 : 1.For the debond models, fibre thermal conductivities range from 0.14 W/mK to1E6 W/mK.


## 3. Discussion of Results

The analytical solution for 1D heat conduction in homogeneous slabs is readily available. However, the analytical solution for 1D heat conduction is quite complex for heterogeneous materials such as fibre reinforced composite materials. Thus, the numerical finite element models have been developed to suit the different cases under consideration for this study. The models are first tested for mesh-independent solution by imposing earlier stipulated boundary conditions; then with the heat flux obtained from ANSYS software, effective thermal conductivity of composite is found by Fourier’s law of heat conduction [3],
(1)q=-KdTdx,
where dT/dx is temperature gradient between two isothermal surfaces. q is the heat flux W/m2.FE model developed in ANSYS is first validated with the Hasselman and Johnson model (H-J) [7] and Farmer and Covert model (F-C) [8]. Figure 9 shows the comparison of results between Hasselman-Johnson model, Farmer-Covert model, and FEM model. It reveals that the results predicted by FE model for full debond case exactly match for complete range of volume fraction and up to nearly 50% Vf for perfect bond condition with both H-J and F-C models and deviation with H-J model from 50% Vf is due to assumptions made in the model and quite coherent with the higher order F-C model.Figure 9
Variation in transverse thermal conductivity with respect to Vf for perfect bond and total debond conditions.Figures10, 11, and 12 show variation in principal thermal conductivities with respect to volume fraction and fibre1 : fibre2 : matrix thermal conductivity ratios for case (i).Figure 10
Variation inK1 of hybrid composite with respect to Vf for different Kf1 : Kf2 : Km.Figure 11
Variation inK2 of hybrid composite with respect to Vf for different Kf1 : Kf2 : Km.Figure 12
Variation inK3 with respect to Vf of hybrid composite for different Kf1 : Kf2 : Km.Figures13, 14, and 15 show variation in principal thermal conductivities with respect to volume fraction and fibre-matrix thermal conductivity ratios for case (ii).Figure 13
Variation inK1 with respect to Vf of a composite with alternate layers of fibres fully debonded.Figure 14
Variation inK2 with respect to Vf of a composite with alternate layers of fibres fully debonded.Figure 15
Variation inK3 with respect to Vf of a composite with alternate layers of fibres fully debonded.Figures16 and 17 show variation in principal thermal conductivities with respect to volume fraction and fibre-matrix thermal conductivity ratios for case (iii).Figure 16
Variation inK1 with respect to Vf for a composite with one in four fibres in unit cell fully debonded.Figure 17
Variation ofK2=K3 with respect to Vf for a composite with one in four fibres in unit cell fully debonded.Table1 represents % error between micro- and macromechanics approaches for case (i).Table 1
% Error between macro- and micromechanics approach results for case-(i) hybrid composite.
Vf
100 : 10 : 01
80 : 08 : 01
60 : 06 : 01
40 : 04 : 01
K
2
K
3
K
2
K
3
K
2
K
3
K
2
K
3
% Error
% Error
% Error
% Error
% Error
% Error
% Error
% Error
0.1
0.025
0.022
0.008
0.010
0.000
0.003
0.000
0.010
0.2
0.021
0.013
0.007
0.024
0.028
0.006
0.029
0.022
0.3
0.017
0.009
0.029
0.016
0.065
0.004
0.074
0.057
0.4
0.037
0.028
0.057
0.038
0.093
0.060
0.160
0.095
0.5
0.085
0.037
0.125
0.046
0.173
0.097
0.294
0.177
0.6
0.136
0.103
0.193
0.143
0.269
0.230
0.440
0.389
0.7
0.212
0.369
0.273
0.502
0.371
0.708
0.521
1.092Table2 represents % error between micro- and macromechanics approaches for case (ii).Table 2
% Error between macro- and micromechanics approaches for composite with alternate layers of fibres fully debonded.
Vf
K
f/Km = 0.74
K
f/Km = 4.03
K
f/Km = 526.32
K
f/Km = 5263.2
K
f/Km = α
K
2
K
3
K
2
K
3
K
2
K
3
K
2
K
3
K
2
K
3
% Error
% Error
% Error
% Error
% Error
% Error
% Error
% Error
% Error
% Error
0.1
0.01
0.02
0.10
0.10
0.07
0.12
0.09
0.11
0.09
0.10
0.2
0.01
0.13
0.37
0.34
0.35
0.43
0.35
0.43
0.34
0.44
0.3
0.06
0.26
0.82
0.77
0.82
0.88
0.82
0.88
0.82
0.88
0.4
0.20
0.41
1.37
1.34
1.38
1.51
1.39
1.51
1.40
1.51
0.5
0.31
0.88
1.89
1.93
1.92
2.27
1.93
2.28
1.94
2.28
0.6
0.75
0.87
2.24
2.30
2.28
2.53
2.30
2.54
2.30
2.54
0.7
1.45
1.82
2.03
2.08
1.97
3.08
1.96
3.09
1.97
3.09Table3 represents % error between micro- and macromechanics approaches for case (iii).Table 3
% Error between macro- and micromechanics approach results for composite with one out of four fibres of unit cell fully debonded.
Vf
K
f/Km = 0.74
K
f/Km = 44.03
K
f/Km = 526.32
K
f/Km = 5263.2
K
f/Km = α
K
2 = K3
K
2 = K3
K
2 = K3
K
2 = K3
K
2 = K3
% Error
% Error
% Error
% Error
% Error
0.1
0.01
0.01
0.03
0.01
0.01
0.2
0.01
0.02
0.06
0.06
0.08
0.3
0.03
0.10
0.15
0.15
0.15
0.4
0.15
0.26
0.36
0.37
0.35
0.5
0.34
0.61
0.79
0.79
0.78
0.6
0.93
1.27
1.54
1.56
1.56
0.7
2.08
2.65
3.23
3.28
3.28Effective longitudinal thermal conductivity for three cases matches with the simple rule of mixtures and increases in linear manner with the increase in Vf (Figures10, 13, and 16) since the fibre thermal conductivity dominates the matrix thermal conductivity. K1 increases with increase in fibre1 : fibre2 : matrix thermal conductivity ratios and its effect is significant at higher Vf. As low and high Kf/Km values prevent better pictorial visibility, in Figures 13 and 16 plots for Kf/Km values of 44.03 and 526.32 are made, as the focus of this paper is comparison between micro- and macromechanics approaches. Also for the three cases, % error between micro- and macromechanics results is zero, so % error for effective longitudinal thermal conductivity is not shown in tables given below.Transverse thermal conductivitiesK2 and K3 for case (i) vary nonlinearly with the variation in Vf, at low values of Vf a gradual rise in K2 and K3 and at higher Vf beyond 0.6 a steep rise in K2 and K3 is observed (Figures 11 and 12). Fibre1 : fibre2 : matrix thermal conductivity ratio is not significant at lower Vf and an increasing trend with respect to Kf/Km is observed at higher Vf.% error between micro- and macromechanics approaches for K2 and K3 lies between 0.01 and 1.09 (Table 1).For case (ii) inplane thermal conductivityK2 and case (iii) both transverse thermal conductivities K2 and K3 vary nonlinearly with volume fraction, and behaviour is similar to case (i) for Kf/Km values greater than unity, but these properties decrease linearly with increase in Vf for Kf/Km value less than unity. Thermal conductivity mismatch ratio is significant at higher volume fractions. % error between micro- and macromechanics approaches for K2 lies between 0.01 and 3.09 (Table 2).For case (ii) through-thickness thermal conductivityK3 decreases almost linearly with increase in Vf, and there is no significant effect of thermal conductivity mismatch ratio at all volume fractions. % error between micro- and macromechanics approaches for K2 lies between 0.01 and 3.28 (Table 3).


## 4. Conclusions

Applicability of homogenization technique by using finite element method is successfully tested for predicting effective thermal conductivities of a hybrid and thermal contact resistance models for different volume fractions within practically possible range of 10% to 70% and thermal conductivity mismatch ratio 0.74 toα. It is evident from the results that macro-mechanics approach yields minimal errors with minimum effort. The same can be extended to composite with more other kinds of dissimilarities which is quite difficult with pure micromechanical models.



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*Source: 147693-2013-10-30.xml*