Document Type: Research Paper
Authors
University of Kashan
Abstract
Keywords

Mechanics of Advanced Composite Structures 4 (2017) 918 

Semnan University 
Mechanics of Advanced Composite Structures journal homepage: http://MACS.journals.semnan.ac.ir 
Distribution of Residual Stresses in Polymer Reinforced Carbon Nanotubes and Laminated Carbon Fibers
A.R. Ghasemi^{*}, M. MohammadiFesharaki
Department of Solid Mechanics, Faculty of Mechanical Engineering, University of Kashan, Kashan, Iran
Paper INFO 

ABSTRACT 
Paper history: Received 20160723 Revised 20160923 Accepted 20161002 
In this study, the distribution of residual stress in fiberreinforced nanocomposites is investigated. Fiberreinforced nanocomposite is composed of three substances: carbon fiber, carbon nanotube (CNT), and polymer matrix. Unit cells in hexagonal packing array with different arrays as unit cell, 3*3 and 5*5 arrays have been selected as suitable for finite element analysis of residual stresses. Radial and tangential residual stress have been determined in different directions by finite element analysis using ABAQUS commercial software for each phase individually. The effect of the CNTs’ various volume fractions (0%, 1%, 2%, and 3%) on residual stress distribution has been studied in different directions and compared to one another for each phase. Results show that the 3*3 unit cells arrays are suitable for modeling microresidual stresses, and the results of this array are reliable. In addition, adding a 3% volume fraction of CNTs to the matrix is the best option for reduction of overall residual stresses with minimal fluctuation in local microresidual stresses. 



Keywords: Residual stresses Carbon nanotube Nanocomposite Unit cell 

DOI: 10.22075/MACS.2016.476 
© 2017 Published by Semnan University Press. All rights reserved. 
Because of many favorable properties of composite materials high stiffness, strength, and corrosion resistance, to name a fewthese materials quickly found a special position in the industry. The high strengthtoweight ratio of polymer matrix composites (PMCs) has caused this type of composite substance to be oftenused. Curing is a production step in the manufacture of PMC components, and the distinct coefficient thermal expansion (CTE) properties of various constituent components can cause residual thermal stresses to be created in the cooling step.
The distribution of residual stresses is characterized as macro or microresidual stress. Macroresidual stresses are caused by interlaminar deformations in composite laminate layers, caused to varying CTE directional properties of the layers. Microresidual stresses develop due to varying CTEs within the constituent phases. In the field of microresidual stress distribution, Hann and Pagona [1] formulated a method based on total stressstraintemperature relations to determine the curing stresses in boron/epoxy composite and found the method to be preferable to the incremental method. More recently, Shokrieh and Ghasemi [23] presented a new method for calculating calibration factors for measuring residual stresses in composite laminate materials. Calibration factors of incremental holedrilling correlated the released strains to the residual stresses in each layer. Because of the nonuniform distribution of residual stresses through the thickness of each specimen, the integral method was used for determination of residual stresses in laminated composites.
Ghasemi et al. [4] employed the integral hole drilling method to calculate the nonuniform residual stresses in various composite laminates. Three ply configurationssymmetric crossply, asymmetric crossply and symmetric quasi–isotropic specimensused to study the model’s ability to predict residual stresses; the model produced results that agreed with theoretical results. Ghasemi and Mohammadi [56] used integral method for the approximation of residual stresses field in fibermetal laminates (FMLs). They experimented with an incremental hole–drilling method to measure the non–uniform residual stresses in each FML ply. The results showed close agreement with predictions using classical laminate plate theory.
Abouhamzeh et al. [7] presented an analytical model to predict warpage and residual stresses that develop during FML curing. They implemented change of stiffness and chemical shrinkage of the material during curing in the model. In the field of micro–residual stresses, common methods for determining residual stresses include finite element analysis [812], circular disc model (CDM) [1314], cylinder theory [1517], and energy method [1820]. Levin et al. [21] studied residual stresses in an Alumina–SiC particulate composite as a function of silicon carbide (SiC) content by Xray diffraction. According to Xray reflection shift and line broadening analysis, average microresidual stresses evaluated in each phase. Todd et al. [22] repeated measuring of micro–residual stresses in Alumina–SiC by neutron diffraction. Wu [23] used an analytical charge distortion model (CDM) for measuring micro–residual stresses in Alumina–SiC nanocomposite and compared his results with the experimental results presented by Levin et al. The comparison showed good agreement and certified CDM results. Maligno [24] investigated the effect of micro–residual stresses on damage of fiber–reinforced laminates as finite element modeling of a unit cell. Residual stresses introduced by curing were determined by considering two possibilities: 1) volume shrinkage of the matrix resin from the crosslink polymerization during isothermal curing and, 2) thermal contraction of both resin and fiber as a consequence of the cooling process to room temperature.
Moreno and Marques [25] considered a different configuration of unit cells and boundary conditions to identify effective properties of active fiber composites (AFCs). AFCs are composed of uniaxial–oriented piezoceramic fibers embedded in a polymer matrix that is sandwiched between two interdigitated electrodes that can be designed as sensors and actuators for applications such as structurehealth monitoring and vibration control. They compared results to past researches and showed good agreement. Shokrieh and GhaneiMohammadi [26] investigated finite element analysis of residual stresses in fiber–reinforced laminate composites. Three types of representative volume element configurationscircular, square and hexagonal modeled were tested, and the effect of each type of fiber packing was studied. They examined the effect of fiber neighbor and boundary conditions on the residual stress distribution of different unit cells and introduced new boundary conditions for the monofiber model to enable it to predict macrobehavior in an efficient way. Shokrieh and Safarabadi [27] used the energy method to identify microresidual stresses in cylinder unit cells. They considered the interphase region between the fiber phase and the matrix phase, as well as the effect of interphase thickness on axial, radial, and shear residual stresses in unit cells.
In threephase composite materials, Shokrieh et al. [28] used carbon nanotubes (CNTs) in fiberreinforced laminate composites. Using polymer matrix, they investigated the effect of CNTs on the reduction of residual stresses by the energy method and slitting method. Another nanomaterial that is used to reduce residual stresses is carbon nanofiber. Ghasemi et al. [29] studied the effect of carbon nanofibers (CNFs) on the reduction of thermal residual stresses in fiber–reinforced composite materials. Micromechanical models are used for determining mechanical and thermal properties of three–phase composites, including carbon fiber, CNT, and polymer matrix. Ghasemi and Mohammadi [3032] studied the distribution of residual stresses in three–phase composite materials used in CNTs as reinforcement of carbon fiber by the electrophoresis method in laminate composites. They used CDM, cylinder theory, and finite element analysis to determine residual stresses in every phase individually.
In this paper, distribution of residual stresses is investigated in the three phases of fiber–reinforced nanocomposite, including carbon fiber, CNT, and polymer matrix. Residual stress distribution is studied in different unit–cell arrays to select an ideal array for this analysis. Radial and tangential residual stress is studied in every phase separately, and the effect of 0%, 1%, 2% and 3% CNT volume fractions on residual stresses is studied in different directions.
Representative volume element (RVE), or unit cell, is a qualified representation element for micromechanical analysis of fiberreinforced, unidirectional laminate composites. For unit cells, the ideal regular arrangement of reinforcing fibers is assumed to be in the matrix. Squarepacking array and hexagonalpacking array are two prevalent arrays used for unidirectional fiberreinforced composite laminates. Schematics of these arrays are shown in Fig. 1. Hexagonal packing array is more useful and suitable for residual stress analysis than is squarepacking array [24]; hence; it is the focus of this paper.
Unit cell 
Because of the high mechanical and thermal properties of nanomaterials, they are used as additional substances in composite materials. Nanomaterials improve mechanical and thermal properties of composite materials. CNTs are typically dispersed into the polymer matrix to reinforce composite materials. The reinforced matrix is, in turn, used as a new matrix for unidirectional fibers. Mechanical and thermal properties of carbon fiber, epoxy matrix, and CNT are shown in Table 1. E, α_{T}_{,} and ν are elastic modulus, transverse CTE, and Poisson’s ratio, respectively.
CNTs should be homogeneously distributed in the matrix to improve the mechanical properties of nanocomposites. Unit cells with homogenous dispersion of 1% CNT volume fraction and 60% carbonfiber volume fraction are shown in Fig. 2(a).
The CNT and carbon fiber radii are considered equal (4 e5 mm and 3.25 e3 mm) and corresponding to actual dimensions. Three different directions are selected to determine residual stress distribution: 1) around the central carbon fiber, 2) OP direction, and 3) OQ direction, as shown in Fig. 2(b). Boundary conditions of residual stresses analysis for unit cells are shown in Fig. 2(b). According to Zhao et al. [33], these are qualified boundary conditions for residual stress analysis.
(a)
Unit Cell 
(b)
Unit Cell 
Figure 1. Schematic of unit cell; (a) hexagonal packing array and (b) square packing array.
Table 1. Mechanical and thermal properties of various phases [30]. 

Phase 
E (GPa) 
α_{T} (1/°C) 
ν 

Carbon fiber 
230 
15 e6 
0.2 

CNT 
1000 
15 e6 
0.1 

Epoxy ML506 
3.13 
62.45e–6 
0.35 

(a)
(b)
Figure 2. Unit cell schematics: (a) homogenous dispersion of CNTs and (b) boundary conditions and different directions.
ABAQUS commercial software was used for finite element modeling and residual stress analysis in different arrays and different CNT volume fractions. Unit cells were modeled as two dimensional and simply supported boundary conditions are applied around the plate, as shown in Fig. 2(b). Curing temperature was considered equal to 120 ^{°}C, and Δt = 100 ^{°}C was considered for residual stress analysis with respect to an ambient temperature of 20 ^{°}C. The cooling process, from curing temperature to ambient temperature, is applied smoothly and neglected changes of mechanical and thermal properties of every phase. For example, the finite element modeling of a unit cell, 3*3 and 5*5 arrays of 1% CNT volume fraction are shown in Figs. 3(a), 3(c), and 3(d) as two dimensional, respectively. A part of a unit cell composed of three phases is shown in Fig. 3(b) in very fine detail. The CNTs are modeled according to actual dimensions, and mechanical and thermal properties. Considered as a triangle, CPS4R is the carbon fiber and CNT’s element type, and CPS3 is the matrix element type. The approximate global size is equal to 18e5 (mm); the 3*3 unitcell array model comprises 22,442 elements, and the 5*5 array models comprise 201,978 and 561,050 elements, respectively.
(a)
CNT 
(b)
(c)
(d)
Figure 3. Unit cell Finite element modeling: (a) unit cell, (b) zone of unit cell elements, (c) 3*3 array and (d) 5*5 array.
In order to consider the neighborhood conditions of carbon fiber and more adaptability of modeling to actuality, two other additional arrays were considered for comparing residual stress distribution and selection of suitable arrays for analysis. To study the residual stresses in different arrays, the unit cell was considered twophased, with 60% carbon fiber volume fraction and without CNT.
The distribution of radial residual stress for different unit cell arrays around the central carbon fiber is shown in Fig. 4. In all cases, radial residual stress distribution is symmetric around the central carbon fiber and is consistent with real conditions. The distribution of radial residual stress around the central carbon fiber in various arrays indicates that increasing the number of carbon fibers caused converged radial residual stress distribution results. The stress distribution in the 3*3 and 5*5 arrays around the central carbon fiber were close together and functioned differently than they would separately in a unit cell. Neighborhood conditions caused the carbon fiber to change locations, affecting the magnitude of the maximum residual stress around central carbon fiber in both arrays. The maximum radial residual stress distribution difference between the 3*3 and 5*5 arrays is less than 7%; however, the radial residual stress distribution of a unit cell is completely different than that of other arrays. This shows that the effect of neighboring carbon fibers is not negligible.
The tangential residual stress distribution around the central carbon fiber is shown in Fig. 5. Change of residual stresses around it is due to the effect of neighboring carbon fibers. Distribution of tangential residual stress converges by increasing the amount of carbon fiber, as the maximum difference of tangential residual stresses in 3*3 and 5*5 arrays is less than 2%. For the unit cell array, the magnitude and the distribution of tangential residual stresses are so different with other arrays, as 3*3 array and 5*5 array, that shows no accuracy of the unit cell array.
Figure 4. Radial residual stress distribution around the central fiber for different arrays. 
The OP direction is considered the direction between two carbon fibers. Radial residual stress distribution is investigated in the OP direction for different arrays in Fig. 6. For a unit cell, radial residual stress distribution is zero at the end of the OP direction. In this location, radial residual stresses did not equal zero for 3*3 and 5*5 arrays due to existence and increase of neighboring carbon fibers.
For the 3*3 and 5*5 arrays, the radial residual stress distribution is very close together, as the maximum radial residual stress difference in the arrays is less than 8%. Radial residual stress distribution is symmetric in the OP direction from the central carbon fiber to the neighboring carbon fiber; however, due to free stress at the edge in the unit cell array, the radial residual stress distribution was not symmetric in the OP direction.
Figure 5. Tangential residual stress distribution around central fiber for different arrays. 
Figure 6. Radial residual stress distribution in the OP direction for different arrays. 
The tangential residual stress distribution of different arrays in the OP direction is shown in Fig. 7. Tangential residual stresses are compressive in carbon fiber and tensional in resin matrix. In unit cells, tangential residual stress distribution is asymmetrical, but increasing the number of carbon fibers caused symmetric distribution of tangential residual stresses in the 3*3 and 5*5 arrays. Tangential residual stress distribution converged when the number of carbon fibers increased, so tangential residual stress distribution was very close together in both arrays.
Radial residual stress in the OQ direction is shown in Fig. 8. In the unit cell, radial residual stresses were decreased in the carbon fiber and matrix from –3.57 (MPa) in the central fiber to the OQ’s free stress edge. Increasing the number of carbon fibers caused a change in the radial residual stress distribution in both arrays as a result of neighboring carbon fibers. Radial residual stresses are increased to the carbon fiber and matrix boundaries in both arrays, where radial residual stresses are decreased from the edge of the central carbon fiber to the end of OQ direction. Radial residual stress distribution of the 3*3 and 5*5 arrays are close together and the maximum difference of radial residual stress in the 3*3 and 5*5 arrays became less than 9%. Tangential residual stress distribution for different arrays in the OQ direction is shown in Fig. 9. Tangential residual stresses become compressive in carbon fiber and tensional in the resin matrix. Increasing number of carbon fibers caused tangential residual stress results to converge in this direction, as well; somehow the 3*3 and 5*5 arrays coincided in every phase.
Figure 7. Tangential residual stress distribution in the OP direction for different arrays.
Figure 8. Radial residual stress distribution in the OQ direction for different arrays. 
Figure 9. Tangential residual stress distribution in the OQ direction for different arrays.

According to the radial and tangential residual stress distribution in different arrays for the twophase unit cell (60% carbon fiber and 0% CNT volume fraction), the increasing number of carbon fibers caused the results to converge and be more logical. The distribution of residual stresses in 3*3 array are so close to 5*5 array that shows stable results and considering more array do not have significant effect on the residual stress distribution. In this research, 3*3 array is selected between different arrays due to better results respect to the unit cell array and less time for the finite element analysis respect to 5*5 array.
Four different CNT volume fractions (0%, 1%, 2%, and 3%) with a constant 60% volume fraction of carbon fiber were employed to evaluate the effect of additional CNTs on residual stress distribution. Dispersion of CNTs in the matrix must be homogenous to have a sufficient effect on it.
Schematic modeling of homogenous dispersion of different CNT volume fractions is shown in Fig. 10. According to homogenous CNT dispersion, and considering actual CNT size, increasing the CNT volume fraction changed the number of CNTs in select directions and in the distance between one another. A CNT stayed in the OP direction certainly for the 2% CNT volume fraction only. As shown in Fig. 10, the number of CNTs in the OP and OQ directions is different in various cases.
In this section, radial and tangential residual stress distribution is investigated in different directions for different CNT volume fractions. The comparison of residual stress distribution of different arrays in the previous section show that the 3*3 array is suitable for determining residual stress distribution in a different direction. Radial residual stress distribution around the central carbon fiber for different CNT volume fractions is shown in Fig. 11.
Figure 10. Unit cell with different CNT volume fractions: a) 1% CNT; b) 2% CNT; c) 3% CNT. 
Maximum and minimum radial residual stress distribution occurred where adjacent carbon fibers were at a maximum and minimum distance from the central carbon fiber in the 0% CNT volume fraction. The existence of CNTs caused a change in the location and magnitude of radial residual stress. Increasing and neighborhood of CNT to carbon fiber caused a fluctuation in radial residual stress.
Tangential residual stress distribution around the central carbon fiber is shown in Fig. 12. Adding CNTs caused the magnitude and location of maximum and minimum tangential residual stress distribution to change. For the 0% CNT volume fraction, tangential residual stress distribution is smoother than other cases because of the CNTs effect on tangential residual stress distribution. For the 1%, 2%, and 3% CNT volume fractions, adding CNTs caused a fluctuation of tangential residual stress in the central carbon fiber.
Figure 11. Radial residual stress distribution around fiber for different CNT volume fractions. 
Figure 12. Tangential residual stresses distribution around fiber for different CNT volume fractions.
The radial residual stress distribution in the OP direction is shown in Fig. 13. The distribution became symmetric, so the magnitude of radial residual stress in the central fiber carbon and neighboring carbon fiber is similar in the OP direction. The presence of CNTs, along with their increase, caused nonuniformity of the radial residual stress distribution in the matrix. However, no significant change in residual stress distribution occurred in the carbon fibers. For the 2% CNT volume fraction, the radial residual stress increased suddenly from 5.14 (MPa) in the matrix to 24.8 (MPa) in the CNTs. This sudden change is due certainly to the presence of CNTs in the OP direction. In the case of the 3% CNT volume fraction, a greater number of CNTs are present near the OP direction. The effect of these CNTs was fluctuation of the radial residual stress distribution in the matrix.
Fluctuation of the radial residual stress distribution is the reason for the increasing CNTs adjacent to the OP direction for the 1% and 3% CNT volume fraction, but the sudden change in radial residual stress distribution for the 2% CNT volume fraction accounts for the existence of a CNT in this direction (Fig. 10(b)).
Tangential residual stress distribution in the OP direction is shown in Fig. 14. Tangential residual stresses become compressive residual stresses in carbon fiber and tensional residual stresses in the matrix. The existence of CNTs is caused by the non–uniformity of the tangential residual stress in the matrix. Tangential residual stress distribution is symmetric for the 0% and 1% CNT volume fractions. Regarding the 2% CNT volume fraction, the existence of a CNT in the OP direction changed the tangential residual stress from 13.4 (MPa) in the matrix to 9.2 (MPa) in the CNT, so the tangential residual stress equaling 9.2 (MPa) is the magnitude of the tangential residual stress in the CNT in this case. For the 3% CNT volume fraction, the effect of the CNTs near the OP direction in the matrix caused fluctuation of the tangential residual stress.
Radial residual stress distribution in the OQ direction is shown in Fig. 15. For the 0% CNT volume fraction, the distribution of radial residual stresses was uniform. By adding CNT to the matrix, some CNTs placed on OQ direction that caused to change the distribution of radial residual stresses. For the 1% CNT volume fraction, radial residual stresses changed from 5.76 (MPa) in the matrix to 25.5 (MPa) in CNT. Regarding the 2% CNT volume fraction, as CNT location changed, the position of the radial residual stress peak changed to CNT location. And for the 3% CNT volume fraction, two CNTs in the OQ direction caused radial residual stresses to change from 6.82 (MPa) in the matrix to 26.17 (MPa) in CNT. This change of radial residual stress occurred for the second CNT in the OQ direction from 7.95 (MPa) in the matrix to 23.7 (MPa) in CNT.
Figure 13. Radial residual stress distribution in the OP direction for different CNT volume fractions. 
Figure 14. Tangential residual stress distribution in the OP direction for different CNT volume fractions.

Figure 15. Radial residual stress distribution in the OQ direction for different CNT volume fractions. 
Figure 16. Tangential residual stress distribution in the OQ direction for different CNT volume fractions. 


%CNT 
Fiber Phase 
CNT Phase 
Matrix Phase 
%0 
3.09 
 
13.25 
%1 
3.08 
9.79 
13.37 
%2 
3.08 
9.40 
13.40 
%3 
3.10 
10.47* 7.36** 
13.70 
* First CNT
** Second CNT
The distribution of tangential residual stresses in the OQ direction is displayed in Fig. 16. Tangential residual stresses became compressive in the carbon fiber and tensional in the CNT and matrix. Distribution of tangential residual stress became smooth in the absence of CNT. For the 1% CNT volume fraction, the presence of a CNT caused the tangential residual stresses to decrease from 13.37 (MPa) in the matrix to 9.79 (MPa) in the CNT. In the case of the 2% CNT volume fraction, the CNT location changed with respect to the 1% CNT volume fraction, causing the tangential residual stress peak to change locations. For the 3% CNT volume fraction case, two CNTs stayed in the OQ direction in the matrix, which caused the tangential residual stress to change suddenly, from 12.71 (MPa) in the matrix to 7.36 (MPa) in first CNT, and from 13.7 (MPa) in the matrix to 10.47(MPa) in the second CNT. The magnitude of tangential residual stress for different cases in every phase are shown in Table 2.
The distribution of residual stresses for threephase CNT/matrix/fiber composites has been investigated. ABAQUS commercial finite element software was used and residual stress in different directions of a unit cell were studied. The results showed that:
References
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[2] Shokrieh MM, Ghasemi AR. Simulation of central hole drilling process for measurement of residual Stresses in isotropic, orthotropic, and laminated composite plates .J Compos Mater 2007; 41(4): 435452.
[3] Ghasemi AR, Shokrieh MM. Development of an integral method for determination of nonuniform residual stresses in laminated composites. Iran J Polym Sci & Tech 2008; 21(4): 347355.
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[5] Ghasemi AR, Mohammadi M. Calculation of calibration factors for determination of residual stresses in fibermetal laminates using incremental holedrilling method. J Sci Tech Compos 2014; 1(1): 3544.
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[8] Chen Y, Xia Z, Ellyin F. Evolution of Residual Stresses Induced During Curing Processing Using a Viscoelastic Micromechanical Model. Compos. Mater 2001; 35: 522542.
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[10] Karami G, Garnich M. Micromechanical Study of Thermoelastic Behavior of Composites with Periodic Fiber Waviness, Compos Part B 2005; 36: 241248.
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[12] Jin KK, Huang Y, Lee Y, Sung KH. Distribution of MicroStresses and Interfacial Tractions in Unidirectional Composites. Compos Mater 2008; 42: 18251849.
[13] Quek M. Analysis of Residual Stresses in a Single Fibre–Matrix Composite. IntJ Adhes Adhes 2004; 24(5): 379388.
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[20] Song DY, Takeda N, Ogihara S. A Method of Stress Analysis for Interfacial Property Evaluation in Thermoplastic Composites. Mater Sci Eng 2000; 278: 242246.
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[30] Ghasemi AR and Mohammadi M. Threedimensional residual stresses analysis of nanocomposite polymeric matrix based on fiber reinforced carbon nanotubes. J Sci Tech Comp 2016; 4(2): 2330.
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[1] Hahn HT, Pagano NJ. Curing stresses in composite laminates. J Compos Mater 1975; 9(1): 91106.
[2] Shokrieh MM, Ghasemi AR. Simulation of central hole drilling process for measurement of residual Stresses in isotropic, orthotropic, and laminated composite plates .J Compos Mater 2007; 41(4): 435452.
[3] Ghasemi AR, Shokrieh MM. Development of an integral method for determination of nonuniform residual stresses in laminated composites. Iran J Polym Sci & Tech 2008; 21(4): 347355.
[4] Ghasemi A, TaheriBehrooz F, Shokrieh M. Determination of nonuniform residual stresses in laminated composites using integral hole drilling method: Experimental evaluation. J Compos Mater 2014; 48(4): 415425.
[5] Ghasemi AR, Mohammadi M. Calculation of calibration factors for determination of residual stresses in fibermetal laminates using incremental holedrilling method. J Sci Tech Compos 2014; 1(1): 3544.
[6] Ghasemi AR, Mohammadi M. Residual stress measurement of fiber metal laminates using incremental holedrilling technique in consideration of the integral method. Int J Mech Sci 2016; 114: 246256.
[7] Abouhamzeh M, Sinke J, Jansen KMB, Benedictus R. Closed form expression for residual stresses and warpage during cure of composite laminates. Compos Struct 2015; 133: 902910.
[8] Chen Y, Xia Z, Ellyin F. Evolution of Residual Stresses Induced During Curing Processing Using a Viscoelastic Micromechanical Model. Compos. Mater 2001; 35: 522542.
[9] Aghdam MM, Khojeh A. More on the Effects of Thermal Residual and Hydrostatic Stresses on Yielding Behavior of Unidirectional Composites. Compos Struct 2003; 62: 285290.
[10] Karami G, Garnich M. Micromechanical Study of Thermoelastic Behavior of Composites with Periodic Fiber Waviness, Compos Part B 2005; 36: 241248.
[11] Zhao LG, Warrior N.A, Long AC. A ThermoViscoelastic Analysis of ProcessInduced Residual Stress in FibreReinforced Polymer–Matrix Composites, Mater Sci Eng 2007; 452: 483498.
[12] Jin KK, Huang Y, Lee Y, Sung KH. Distribution of MicroStresses and Interfacial Tractions in Unidirectional Composites. Compos Mater 2008; 42: 18251849.
[13] Quek M. Analysis of Residual Stresses in a Single Fibre–Matrix Composite. IntJ Adhes Adhes 2004; 24(5): 379388.
[14] Hsueh C H, Becher PF, Sun EY. Analyses of thermal expansion behavior of intergranular twophase composites. J Mater Sci 2001; 36: 255261.
[15] Jayaraman K, Reifsnider KL. Residual Stresses in a Composite with Continuously Varying Young’s Modulus in the Fiber/Matrix Interphase. Compos Mater 1992; 26: 770791.
[16] Jayaraman K, Reifsnider KL. The Interphase in Unidirectional FiberReinforced Epoxies: Effect of Residual Thermal Stresses. Compos Sci Technol 1993; 47: 119129.
[17] Bianchi V, Goursat P, Menessier E. CarbonFiberReinforced YMAS Glass Ceramic Matrix IV Thermal Residual Stresses and Fiber/Matrix Interfaces. Compos Sci Technol 1998; 58: 409418.
[18] Quek MY, Yue CY. Axisymmetric Stress Distribution inthe Single Filament Pull outTest. Mater Sci Eng 1994; 189: 105116.
[19] Zhang Y, Xia Z, Ellyin F. Evolution and Influence of Residual Stresses/Strains of Fiber Reinforced Laminates. Compos Sci Technol 2004; 64: 16131625.
[20] Song DY, Takeda N, Ogihara S. A Method of Stress Analysis for Interfacial Property Evaluation in Thermoplastic Composites. Mater Sci Eng 2000; 278: 242246.
[21] Levin I, Kaplan WD, Brandon D,Wieder T. Residual stresses in aluminaSiC nanocomposites. Acta Metall Mater 1994; 42(4): 11471154.
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