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1

Yazdani Sarvestani, Hamidreza, and Ali Naghashpour. "Investigation of Through-Thickness Stresses in Composite Laminates Using Layerwise Theory." International Journal of Engineering Mathematics 2013 (December 12, 2013): 1–11. http://dx.doi.org/10.1155/2013/676743.

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In this study, an analytical method is developed to exactly obtain the interlaminar stresses near the free edges of laminated composite plates under the bending moment based on the reduced form of elasticity displacement field for a long laminate. The analytical and numerical studies were performed based on the Reddy’s layerwise theory for the boundary layer stresses within cross-ply, symmetric, angle-ply, and general composite laminates. Finally, a variety of numerical results are presented for the interlaminar normal and shear stresses along the interfaces and through thickness of laminates
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2

Biswas, Dhiraj, and Chaitali Ray. "Comparative perspective of various shear deformation theories with experimental verification for modal analysis of hybrid laminates." Journal of Vibration and Control 23, no. 8 (2015): 1321–33. http://dx.doi.org/10.1177/1077546315592766.

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The present paper deals with the free vibration modal analysis of hybrid laminates using a finite element model based on the third order shear deformation theory (TSDT) and the first order shear deformation theory (FSDT). A computer code has been developed using MATLAB, 2013. The experimental investigation on the free vibration of hybrid laminates made of carbon and glass fibres has been conducted. The hybrid laminate is prepared by placing carbon fibres in the outermost laminae and glass fibres in the rest of the laminate. The bi-directional glass and carbon fabrics and the epoxy resin are us
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3

Zulkifli, M. A. A., Z. I. A. Halim, N. A. S. Norbani, and J. Mahmud. "Failure Analysis of Boron/Epoxy Composite Laminates with Square Cutouts in Various Size under Uniaxial Tension." Journal of Physics: Conference Series 2051, no. 1 (2021): 012062. http://dx.doi.org/10.1088/1742-6596/2051/1/012062.

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Abstract Composite laminates have received much interest in precise engineering fields such as aerospace and automotive industries. Understanding the failure behaviour of laminated composites is important when designing modern structures, but many studies only focus on laminates without cutouts. In practice, the structures are design with cutouts to accommodate the space for fasteners, such as rivets, screws and bolts. This study analyses the failure behaviour of Boron/Epoxy composite laminates with square cutout of various sizes under uniaxial tension. In this study, failure analysis was perf
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4

Mathison, S. R., M. J. Pindera, and C. T. Herakovich. "Nonlinear Response of Resin Matrix Laminates Using Endochronic Theory." Journal of Engineering Materials and Technology 113, no. 4 (1991): 449–55. http://dx.doi.org/10.1115/1.2904125.

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The nonlinear response of laminated, resin matrix fibrous composites is modeled using orthotropic endochronic theory. The theory is formulated in terms of elastic constants and endochronic parameters characterizing the linear and nonlinear response, respectively, of unidirectional composites. All constants and parameters can be determined from normal (tension and/or compression) and shear tests on unidirectional and off-axis specimens. The nonlinear constitutive response relations for the unidirectional lamina are presented and the procedure for determining constants and parameters from test i
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5

Toledano, A., and H. Murakami. "A Composite Plate Theory for Arbitrary Laminate Configurations." Journal of Applied Mechanics 54, no. 1 (1987): 181–89. http://dx.doi.org/10.1115/1.3172955.

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In order to improve the accuracy of in-plane responses of shear deformable composite plate theories, a new laminated plate theory was developed for arbitrary laminate configurations based upon Reissner’s (1984) new mixed variational principle. To this end, across each individual layer, piecewise linear continuous displacements and quadratic transverse shear stress distributions were assumed. The accuracy of the present theory was examined by applying it to the cylindrical bending problem of laminated plates which had been solved exactly by Pagano (1969). A comparison with the exact solutions o
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6

Matsuda, Tetsuya, Y. Nimiya, Nobutada Ohno, and Masamichi Kawai. "Elastic-Viscoplastic Behaviour of Plain-Woven GFRP Laminates: Analysis Using Homogenization Theory." Key Engineering Materials 334-335 (March 2007): 45–48. http://dx.doi.org/10.4028/www.scientific.net/kem.334-335.45.

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In the present study, a method for reducing the domain of analysis is developed for the homogenization analysis of plain-woven laminates. Moreover, the method is applied to the quantitative prediction of elastic-viscoplastic deformation of plain-woven GFRP laminates. It is first shown that the internal structures of plain-woven laminates satisfy point-symmetry on the assumption that the laminates have the in-phase or out-of-phase laminate configuration of plain fabrics. The point-symmetry is then utilized for the boundary condition of unit cell problems, reducing the domain of analysis to 1/4
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7

NAKATA, K., T. MATSUDA, and M. KAWAI. "MULTI-SCALE CREEP ANALYSIS OF PLAIN-WOVEN LAMINATES USING TIME-DEPENDENT HOMOGENIZATION THEORY: EFFECTS OF LAMINATE CONFIGURATION." International Journal of Modern Physics B 22, no. 31n32 (2008): 6173–78. http://dx.doi.org/10.1142/s0217979208051753.

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In this study, multi-scale creep analysis of plain-woven GFRP laminates is performed using the time-dependent homogenization theory developed by the present authors. First, point-symmetry of internal structures of plain-woven laminates is utilized for a boundary condition of unit cell problems, reducing the domain of analysis to 1/4 and 1/8 for in-phase and out-of-phase laminate configurations, respectively. The time-dependent homogenization theory is then reconstructed for these domains of analysis. Using the present method, in-plane creep behavior of plain-woven glass fiber/epoxy laminates s
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8

Kormanikova, Eva, Kamila Kotrasova, Jozef Melcer, and Veronika Valaskova. "Numerical Investigation of the Dynamic Responses of Fibre-Reinforced Polymer Composite Bridge Beam Subjected to Moving Vehicle." Polymers 14, no. 4 (2022): 812. http://dx.doi.org/10.3390/polym14040812.

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In modern industry, heavy traditional materials are being substituted with light and strong fibre-reinforced polymer composite materials. Bridges and railroads made of composite laminates are considerably affected by traffic loads. Therefore, it is very important to analyse this effect which would find practical applications in engineering designs. This paper explains the theoretical formulation that governs the dynamic response of a composite beam subjected to a moving load. The governing equations for the dynamic effect on the laminated composite bridge beam are explained here. The main theo
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9

Wang, Junli, and Jinyang Li. "Failure Analysis and Optimization Design of Wing Skin Unbalanced Lay-Up." Advances in Materials Science and Engineering 2022 (November 2, 2022): 1–13. http://dx.doi.org/10.1155/2022/7131899.

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To clarify the influence of the unbalanced coefficient and the change in lay-up angle on the failure characteristics of the laminate in the static aeroelastic problem of the aircraft, numerical simulations were performed based on the classical laminate theory and the Tsai-Wu failure criterion, as well as the fluid-structure coupling calculation method. The structure’s stress-strain and failure curves are found to decrease as the unbalanced coefficient increases. The stress curve’s slope is relatively stable, whereas the strain and failure curves’ slopes change three times, indicating that stra
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10

Li, Shu, and Fei Han. "A New Failure Theory and Importance Measurement Analysis for Multidirectional Fiber-Reinforced Composite Laminates with Holes." Materials 15, no. 6 (2022): 2227. http://dx.doi.org/10.3390/ma15062227.

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In this paper, a failure theory for the multidirectional fiber-reinforced composite laminate with a circular hole is developed. In this theory, the finite fracture mechanics method is combined with the improved Puck’s failure theory including the in situ strength effect. It can predict the notched strength by only basic material properties of unidirectional laminas, geometries and stacking sequence of the laminate. In advance mechanical properties of the laminate are unnecessary. The notched laminates with different material types and stacking sequences are taken as examples to verify this fai
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11

Valot, E., P. Vannucci, and G. Verchery. "Complete In-plane Elastic Characterisation under Tensile Tests of Angle-Ply Laminates Composed of Polymer-Matrix Layers." Polymers and Polymer Composites 10, no. 7 (2002): 483–92. http://dx.doi.org/10.1177/096739110201000701.

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In this paper we present a new strategy to completely characterise the in-plane elastic properties of a large range of angle-ply laminates using only unidirectional tests. We consider laminates having the same number of identical plies in the α and – α directions. This new method uses some preceding results found by Verchery for orthotropic laminates, namely the conditions of existence of a specific direction ω, in which the shear-extension coupling is null. The characterisation of the laminate is then made using the results of three tensile tests: two in the orthotropy axes, and the third one
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12

Liew, K. M., J. Z. Zhang, T. Y. Ng, and J. N. Reddy. "Dynamic Characteristics of Elastic Bonding in Composite Laminates: A Free Vibration Study." Journal of Applied Mechanics 70, no. 6 (2003): 860–70. http://dx.doi.org/10.1115/1.1604838.

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In conventional analyses of composite laminates, the assumption of perfect bonding of adjoining layers is well accepted, although this is an oversimplification of the reality. It is possible that the bond strength may be less than that of the laminae. Thus, the study of weak bonding is an interesting focus area. In this study, an elastic bonding model based on three-dimensional theory of elasticity in a layerwise framework is used to study composite laminates. The differential quadrature (DQ) discretization is used to analyze the layerwise model. The present model enables the simulation of act
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13

Harris, William, Constantinos Soutis, and Christopher Atkin. "Impact Response of Curved Composite Laminates: Effect of Radius and Thickness." Applied Composite Materials 27, no. 5 (2020): 555–73. http://dx.doi.org/10.1007/s10443-020-09826-2.

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Abstract This paper presents the results of drop-weight impact testing (5 J to 30 J) on curved ±55° E-glass-epoxy laminates of varying radii and wall thickness. Three radii (75 mm, 100 mm, and 125 mm) on laminates with an effective wall thickness of 2.5 mm, and three wall thicknesses (2.5 mm, 4.1 mm, and 6.6 mm) with a radius of 100 mm were investigated. The damage pattern remained consistent, with the exception of the damage area, across the tested energies and was dominated by internal matrix cracking and multiple delaminations. However, no damage was recorded following a 5 J impact on the 2
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14

Matsuda, Tetsuya, Jin Toyomura, Tsubasa Ogaki, and Masahiro Arai. "Two-Scale Analysis of Thermal Behavior of CFRP Laminates Based on a Thermoelastoviscoplastic Homogenization Theory." Key Engineering Materials 725 (December 2016): 433–38. http://dx.doi.org/10.4028/www.scientific.net/kem.725.433.

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In this study, a two-scale thermoelastoviscoplastic analysis method for carbon fiber-reinforced plastic (CFRP) laminates is proposed based on a homogenization theory for time-dependent composites. For this, macroscopic and microscopic boundary value problems for CFRP laminates are derived to discuss the relation between the two problems. Using the relation, a two-scale thermoelastoviscoplastic analysis method is constructed, and then applied to the analysis of thermal behavior of an unsymmetric cross-ply carbon fiber/epoxy laminate. The laminate is subjected to a macroscopic temperature change
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15

Chen, Yizhe, Zhuoqun Wang, Yi Lin, Hui Wang, and Lin Hua. "Theoretical Modeling and Experimental Verification of the Bending Deformation of Fiber Metal Laminates." Materials 16, no. 9 (2023): 3486. http://dx.doi.org/10.3390/ma16093486.

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Fiber metal laminates have been widely used as the primary materials in aircraft panels, and have excellent specific strength. Bending deformation is the most common loading mode of such components. An accurate theoretical predictive model for the bending process for the carbon reinforced aluminum laminates is of great significance for predicting the actual stress response. In this paper, based on the metal-plastic bending theory and the modified classical fiber laminate theory, a modified bending theory model of carbon-fiber-reinforced aluminum laminates was established. The plastic deformati
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16

Murakami, H. "A Mixture Theory for Wave Propagation in Angle-Ply Laminates, Part 1: Theory." Journal of Applied Mechanics 52, no. 2 (1985): 331–37. http://dx.doi.org/10.1115/1.3169049.

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In an effort to construct a continuum model with microstructure for elastic angle-ply laminates, an asymptotic mixture theory with multiple scales is presented in this two-part paper. The theory, which is in the form of a binary mixture, can simulate wave propagation in linearly elastic laminated composites with orthotropic lamina. Reissner’s new variational principle has been adopted to avoid the numerous solution procedures of microstructure boundary value problems (MBVP’s), which are required to find mixture properties in terms of the geometrical and material properties of the two constitue
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17

Noh, Nurul Najwa, Azizul Hakim Samsudin, and Jamaluddin Mahmud. "Failure Analysis of Glass/Epoxy and Graphite/Epoxy Laminates due to the Effect of Variation in Lamination Scheme and Angle of Fibre Orientation." Materials Science Forum 889 (March 2017): 36–44. http://dx.doi.org/10.4028/www.scientific.net/msf.889.36.

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Understanding the failure behaviour of composite laminate is crucial in designing a reliable composite structure. Failure analyses have been carried out widely. Nevertheless, the composite laminate displacements before the occurrence of failure have not been analysed thoroughly, especially when comparing between Glass/Epoxy and Graphite/Epoxy, which are the two most common composite laminates. For example, it could be observed that the lamination schemes and variations of angle orientation could affect the displacements and failure behaviour of the symmetric laminate. Therefore, this paper aim
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18

Liu, Jen-Chieh, Robert J. Moon, Alan Rudie, and Jeffrey P. Youngblood. "Mechanical performance of cellulose nanofibril film-wood flake laminate." Holzforschung 68, no. 3 (2014): 283–90. http://dx.doi.org/10.1515/hf-2013-0071.

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Abstract Homogeneous and transparent CNF films, fabricated from the (2,2,6,6- tetramethylpiperidin-1-yl) oxyl (TEMPO)-modified CNF suspension, were laminated onto wood flakes (WF) based on phenol-formaldehyde (PF) resin and the reinforcement potential of the material has been investigated. The focus was on the influence of CNF film lamination, relative humidity (RH), heat treatment, and anisotropic properties of WF on the CNF-WF laminate tensile properties (elastic modulus, ultimate tensile strength, strain to failure). Results demonstrated that CNF-WF laminates had improved mechanical perform
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19

Tsai, C. L., I. M. Daniel, and G. Yaniv. "Torsional Response of Rectangular Composite Laminates." Journal of Applied Mechanics 57, no. 2 (1990): 383–87. http://dx.doi.org/10.1115/1.2892001.

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The torsional response of a composite laminate of rectangular cross-section was analyzed by the Mindlin-Reissner theory. The analysis takes into account separately the shear properties of each layer. A general closed-form relationship was derived between torque and angle of twist in terms of the geometric parameters and shear properties of the laminae. In the case of unidirectional laminates, relations can be expressed involving the three principal shear moduli, G12, G13, and G23. An experimental method was also developed for determining these moduli by measuring surface and edge strains with
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20

Ray, M. C. "Zeroth-Order Shear Deformation Theory for Laminated Composite Plates." Journal of Applied Mechanics 70, no. 3 (2003): 374–80. http://dx.doi.org/10.1115/1.1558077.

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In this paper a zeroth-order shear deformation theory has been derived for static and dynamic analysis of laminated composite plates. The responses obtained by the theory for symmetric and antisymmetric laminates are compared with the existing solutions. The comparison firmly establishes that this new shear deformation theory can be used for both thick and thin laminated composite plates with high accuracy.
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21

Parhizgar, Shahrokh. "Verification of Laminated Plate Theory for Unsymmetrical Laminates." Journal of Composite Materials 25, no. 5 (1991): 578–92. http://dx.doi.org/10.1177/002199839102500506.

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22

Xiao, J., Y. Li, and W. X. Fan. "A laminate theory of piezoresistance for composite laminates." Composites Science and Technology 59, no. 9 (1999): 1369–73. http://dx.doi.org/10.1016/s0266-3538(98)00176-6.

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23

Fragoudakis, Roselita. "A numerical approach to determine fiber orientations around geometric discontinuities in designing against failure of GFRP laminates." International Journal of Structural Integrity 10, no. 3 (2019): 371–79. http://dx.doi.org/10.1108/ijsi-10-2018-0064.

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Purpose Determining fiber orientations around geometric discontinuities is challenging and simultaneously crucial when designing laminates against failure. The purpose of this paper is to present an approach for selecting the fiber orientations in the vicinity of a geometric discontinuity; more specifically round holes with edge cracks. Maximum stresses in the discontinuity region are calculated using Classical Lamination Theory (CLT) and the stress concentration factor for the aforementioned condition. The minimum moment to cause failure in a lamina is estimated using the Tsai–Hill and Tsai–W
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24

Yang, Chihdar, and Su-Seng Pang. "Stress-Strain Analysis of Single-Lap Composite Joints Under Tension." Journal of Engineering Materials and Technology 118, no. 2 (1996): 247–55. http://dx.doi.org/10.1115/1.2804896.

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Based on the laminated anisotropic plate theory, an analytical model is proposed to determine the stress and strain distributions of adhesive-bonded composite single-lap joints under tension. The laminated anisotropic plate theory is applied in the derivation of the governing equations of the two bonded laminates. The entire coupled system is then obtained through assuming the peel stress between the two laminates. With the Fourier series and appropriate boundary conditions, the solutions of the system are obtained. Based on the proposed model, the stress and strain distributions of the adhere
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25

Huang, Chunfang, Mingchang He, Yonglyu He, et al. "Exploration relation between interlaminar shear properties of thin-ply laminates under short-beam bending and meso-structures." Journal of Composite Materials 52, no. 17 (2017): 2375–86. http://dx.doi.org/10.1177/0021998317745586.

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Carbon fiber reinforced polymer matrix composite laminates with standard thickness plies (0.125 mm) usually have weak interlaminar shear strength, meanwhile, for thin-thickness laminate structures such as aircraft wing skin, it is difficult to design a balanced laminate with the standard plies. It is a possible way to improve the interlaminar shear performance of carbon fiber reinforced polymer composite laminates and enlarge the design space of the thin-thickness structures by using thin-plies technology. In this paper, the interlaminar shear strength of carbon fiber/epoxy laminates with thin
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26

Kim, Won Seok, Sang Hoon Kim, and Jung Ju Lee. "Structural Health Monitoring of Composite Laminates by Using Embedded FBG Optical Fiber Sensors." Key Engineering Materials 297-300 (November 2005): 2158–63. http://dx.doi.org/10.4028/www.scientific.net/kem.297-300.2158.

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In this paper, a new Structural Health Monitoring (SHM) technique for composite laminates through the use of embedded FBG sensors is presented. This method monitors the ply stress states of a laminate and compares them with failure criteria continuously during structures’ service time. The ply stress state of each ply composing the composite laminate can be obtained by embedding three FBG sensors in the laminate based on the classical lamination theory. In this study FBG sensor embedded graphite/epoxy composite laminate specimens were fabricated. With ply stress states being monitored, tension
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27

Mal, A. K., C. C. Yin, and Y. Bar-Cohen. "Analysis of Acoustic Pulses Reflected From Fiber-Reinforced Composite Laminates." Journal of Applied Mechanics 59, no. 2S (1992): S136—S144. http://dx.doi.org/10.1115/1.2899478.

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The time histories and spectral characteristics of acoustic pulses reflected from fiberreinforced composite laminates immersed in water are recorded in the laboratory and analyzed through a generalized ray theory and an exact theory. Calculated results for an unidirectional laminate and two angle-ply laminates are compared with measured data. It is shown that for a unidirectional laminate a finite number of mode-converted waves contribute to the overall signal reflected from a thick specimen resulting in certain irregular behavior of the reflected pulses. A phenomenological model of wave atten
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28

Aljanabi, Maytham, Mustafa Hunain, and Salah Alnomani. "Experimental and Theoretical Studies of Last Ply Failure Analysis on the Laminate Polymer Composite Materials with Different Orientation and Stacking Sequence of Fibers Based on Classical Laminate Theory." Kerbala Journal for Engineering Sciences 1, no. 2 (2021): 170–90. https://doi.org/10.63463/kjes1029.

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Unidirectional composite materials are among the most important composite materials and have many applications in daily life. The angle of the fibers of the lamina is an important factor in controlling properties of the composite materials as well as the sequence of layers. The aim of this study is to obtain the best laminate with good mechanical properties (strength and stiffness) with the selection of the appropriate failure theory. This study was conducted to carbon /epoxy laminate with different angles (0°,25°,30°,50°,60°,75°,90°) by three theories of failure (maximum stress theory, Tsai-H
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29

Guillén-Rujano, R., A. Hernández-Pérez, and F. Avilés. "Examination of the plate twist specimen for thick specially orthotropic laminated composites and sandwich plates by using first-order shear deformation theory." Journal of Sandwich Structures & Materials 21, no. 7 (2017): 2239–65. http://dx.doi.org/10.1177/1099636217748349.

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Analytical (closed-form) solutions are developed for the deflections and rotations of thick specially orthotropic plate twist specimens by using first-order shear deformation theory. Results are compared with outcomes from finite element method, previously reported experiments, and a classical laminated plate theory solution. A [(0/90)6]s cross-ply laminate and a sandwich panel with aluminum face sheets and a polyvinyl chloride (PVC) foam core are used as baseline materials. Overall, good agreement between first-order shear deformation theory and finite element method is obtained for complianc
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30

Goto, Keita, and Tetsuya Matsuda. "Free Edge Stress Analysis of Unidirectional CFRP Laminates Based on a Homogenization Theory for Time-Dependent Composites." Key Engineering Materials 535-536 (January 2013): 397–400. http://dx.doi.org/10.4028/www.scientific.net/kem.535-536.397.

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In this study, distributions of microscopic stress at free edges of unidirectional carbon fiber-reinforced plastic laminates (CFRP laminates) are analyzed three-dimensionally, based on a homogenization theory for time-dependent composites. For this, the homogenization theory is reconstructed for free edge problems using a traction-free boundary condition. Then, an analysis domain is reduced using the point-symmetry of the internal structure of the unidirectional CFRP laminate. Moreover, the substructure method is newly introduced into the theory to reduce the computational costs required for t
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31

Padhi, Ansuman, and Mihir K. Pandit. "Bending and free vibration response of sandwich laminate under hygrothermal load using improved zigzag theory." Journal of Strain Analysis for Engineering Design 52, no. 5 (2017): 288–97. http://dx.doi.org/10.1177/0309324717714710.

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In this work, the effects of variations in temperature and moisture concentrations on the static and free vibration response of sandwich laminated plates with low-density core have been studied. A higher order zigzag laminate theory is used which satisfies the continuity in transverse shear stress at the layer interfaces and zero transverse shear stress condition at the top and bottom surfaces of the laminate . The displacement field in this theory suitably allows for the quadratic distribution of transverse shear stress across the thickness and transverse compressibility effect of the core. A
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32

ARCINIEGA, R. A., P. B. GONÇALVES, and J. N. REDDY. "BUCKLING AND POSTBUCKLING ANALYSIS OF LAMINATED CYLINDRICAL SHELLS USING THE THIRD-ORDER SHEAR DEFORMATION THEORY." International Journal of Structural Stability and Dynamics 04, no. 03 (2004): 293–312. http://dx.doi.org/10.1142/s0219455404001240.

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In the present work the buckling and postbuckling behavior of laminated cylindrical shells under axial compression and lateral pressure loading are investigated. A nonlinear theory for thin cylinders incorporating the effects of transverse shear deformation is employed. A modal solution based on the Koiter theory is utilized to derive the nonlinear equilibrium equations for the postcritical behavior of the shell. The Rayleigh–Ritz method is used to obtain analytical solutions for the critical load through algebraic routines written in Maple. Prebuckling and postbuckling equations are also solv
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33

Mohammadi, B., H. Hosseini-Toudeshky, and M.-H. Sadr-Lahidjani. "Free-edge effects analysis of angle-ply laminates under transverse loading using layer-wise finite-element method with semi-analytical shear stress calculation." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 223, no. 2 (2008): 293–306. http://dx.doi.org/10.1243/09544062jmes1063.

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Free-edge stress fields are of an utmost localized nature exhibiting steep stress gradients and they rapidly decay with increasing distance from the laminates’ edges. Layer-wise theory has already been used to analyse the stress field at the free edges of the laminates. In this investigation, the layer-wise theory in finite-element method (FEM) is used to analyse the stress field of the laminates’ free edges. In this study, apart from the conventional FEM in which the stresses are calculated from the constitutive laws, the shear stress components along the thickness are calculated from the equ
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34

Peng, L. X. "Free Vibration Analysis of Symmetrically Laminated Folded Plate Structures Using an Element-Free Galerkin Method." Mathematical Problems in Engineering 2015 (2015): 1–13. http://dx.doi.org/10.1155/2015/124296.

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An element-free Galerkin method for the solution of free vibration of symmetrically laminated folded plate structures is introduced. Employing the mature meshfree folded plate model proposed by the author, a folded laminated plate is simulated as a composite structure of symmetric laminates that lie in different planes. Based on the first-order shear deformation theory (FSDT) and the moving least-squares (MLS) approximation, the stiffness and mass matrices of the laminates are derived and supposed to obtain the stiffness and mass matrices of the entire folded laminated plate. The equation gove
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35

Goto, Keita, Takuya Tomioka, Masahiro Arai, and Tetsuya Matsuda. "Elasto-Viscoplastic Analysis of Slanting-Weft Woven Fabric Composites Based on Homogenization Theory." Key Engineering Materials 725 (December 2016): 410–15. http://dx.doi.org/10.4028/www.scientific.net/kem.725.410.

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The elasto-viscoplastic behavior of slanting-weft woven laminates, the fiber bundles of which are not crossed at a right angle, is investigated both macroscopically and microscopically. For this, an analysis model for the [±θ] slanting-weft woven laminate with a cross angle ±θ and its diamond-shaped unit cell are considered. Then, a basic cell, which is quarter of the unit cell, is defined as an analysis domain by considering the point-symmetry of the internal structure. For the basic cell, the homogenization theory for nonlinear time-dependent composites with point-symmetric internal structur
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36

Sajid, Zubair, Saravanan Karuppanan, Kee Kok Eng, and Syed Zulfiqar Hussain Shah. "Analytical Method for the Optimization of the Open-Hole and Filled-Hole Laminates at the Preliminary Design Stage." Materials 16, no. 6 (2023): 2213. http://dx.doi.org/10.3390/ma16062213.

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In recent years, there has been an increasing interest in open-hole and filled-hole laminate failure analysis. The open and filled-hole laminate failure analysis is used in several important areas, especially in designing mechanically fastened composite joints. Various analytical, empirical, and numerical methods are available for the design of mechanically fastened composite joints. The large number of material and geometrical design variables at the preliminary design stage makes the empirical and numerical methods effortful, expensive, and time-consuming. Therefore, analytical methods are r
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37

Thinh, Tran Ich, and Ngo Nhu Khoa. "Hygroscopically induced residual stresses in composite laminates." Vietnam Journal of Mechanics 23, no. 3 (2001): 173–82. http://dx.doi.org/10.15625/0866-7136/9950.

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In this paper the exact moisture concentration function m(z, t) is used to compute the hygroscopic residual stresses in laminated composites. The governing equations were established by using a full higher-order displacement theory. Hygroscopically induced residual stresses in thick graphite-epoxy composite laminates: Cross-ply [0/90] 8 based on this approach were compared with those obtained by assumption: the moisture concentration m is a constant in all plies through the laminates thickness
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38

Qiu, Jiabo. "Equivalent stiffness calculation of composite hat stiffened laminate." Vibroengineering PROCEDIA 47 (December 12, 2022): 42–48. http://dx.doi.org/10.21595/vp.2022.23045.

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The stiffness is the main reason that restricts the large-scale of composite ships, the basis to solve this problem is to solve the stiffness of composite ships’ skeleton structure. Based on classical laminates theory, this paper calculated the equivalent in-plane stiffness and bending stiffness of composite hat stiffened laminate using equivalent stiffness principle. The hat stiffened laminate can be simplified and equivalent to orthotropic laminates using this solution idea, which solves the problem that it is difficult to obtain the analytical solutions of deformation, stress and strain of
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39

Liu, G. R., J. Tani, K. Watanabe, and T. Ohyoshi. "Lamb Wave Propagation in Anisotropic Laminates." Journal of Applied Mechanics 57, no. 4 (1990): 923–29. http://dx.doi.org/10.1115/1.2897662.

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The wave propagation in arbitrary anisotropic laminates is investigated on the basis of an exact theory. The dispersion relations of Lamb waves are determined for graphite/epoxy symmetric angle-ply laminates and hybrid composite ones which consist of carbon/epoxy and glass/epoxy layers. The dispersion and anisotropy of phase velocities for fundamental modes are discussed in detail. The energy distributions in the thickness direction of laminates are calculated for each kind of Lamb wave. A hybrid composite laminate is found to have better capability in absorbing impact energy by analyzing the
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40

Xu, Zhuo, Hui Li, Wen-yu Wang, Yuan-ning Liu, and Bang-chun Wen. "Inverse identification of mechanical parameters of fiber metal laminates." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 234, no. 8 (2019): 1516–27. http://dx.doi.org/10.1177/0954406219893719.

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In this paper, an inverse method to identify the mechanical parameters of fiber metal laminates is proposed on the basis of the measured and calculated frequency response functions. The classical laminates theory, orthogonal polynomial method, and energy method are employed to characterize the theoretical modal of a fiber metal-laminated thin plate under pulse excitation. And, an iterative solution on the basis of frequency response functions and least square method is proposed to identify the mechanical parameters of fiber metal laminates, which conclude the elastic modulus, Poisson's ratios,
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41

Jameel, Adnan Naji, and Kawther Khalid Younus. "Buckling Analysis Of Damaged Composite Plates Under Uniform Or Non-Uniform Compressive Load." Journal of Engineering 18, no. 08 (2023): 961–78. http://dx.doi.org/10.31026/j.eng.2012.08.09.

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The present study focused mainly on the buckling behavior of composite laminated plates subjected to mechanical loads. Mechanical loads are analyzed by experimental analysis, analytical analysis (for laminates without cutouts) and numerical analysis by finite element method (for laminates with and without cutouts) for different type of loads which could be uniform or non-uniform, uniaxial or biaxial. In addition to many design parameters of the laminates such as aspect ratio, thickness ratio, and lamination angle or the parameters of the cutout such as shape, size, position, direction, and rad
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42

Ye, Junjie, Yuanying Qiu, Xuefeng Chen, Yumin He, and Zhi Zhai. "A Study of Failure Strength for Fiber-Reinforced Composite Laminates with Consideration of Interface." Advances in Materials Science and Engineering 2015 (2015): 1–10. http://dx.doi.org/10.1155/2015/158578.

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Composite laminates can exhibit the nonlinear properties due to the fiber/matrix interface debonding and matrix plastic deformation. In this paper, by incorporating the interface stress-displacement relations between fibers and matrix, as well as the viscoplastic constitutive model for describing plastic behaviors of matrix materials, a micromechanical model is used to investigate the failure strength of the composites with imperfect interface bonding. Meanwhile, the classic laminate theory, which provides the relation between micro- and macroscale responses for composite laminates, is employe
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Lu, WT, S. Singh, and WS Chan. "A novel stress analysis method for composite Z-stiffeners under mechanical and thermal loads." Journal of Composite Materials 53, no. 26-27 (2019): 3807–18. http://dx.doi.org/10.1177/0021998319846947.

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A closed-form analytical solution is developed for analyzing laminated composite beam with asymmetric Z cross-section. The explicit expressions for evaluating sectional properties such as centroid, shear center, equivalent bending/torsional stiffness and warping stiffness are formulated based upon modified lamination theory and taken into consideration of the structural deformation characteristics of beam with narrow section. The ply stresses of flanges and web laminates are computed for composite Z-stiffener under axial, bending, and torsional loads. The present results give excellent agreeme
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44

Luo, Shen-Yi, and Faruk Taban. "Deformation of Laminated Elastomer Composites." Rubber Chemistry and Technology 72, no. 1 (1999): 212–24. http://dx.doi.org/10.5254/1.3538791.

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Abstract Flexible elastomer composites subjected to finite deformation are usually associated with significant fiber re-orientation and configuration change which cannot be described by classical composite lamination theory. Utilizing the Lagrangian description and a strain-energy density approach, this work presents a set of 2-D constitutive equations in terms of the overall deformation of laminated composites. This model includes both geometric and material nonlinearities of the laminate. Interlaminar shear deformation is addressed but not studied in this analysis. Theoretical predictions ha
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Yang, Xiao Mei. "Double-Superposition Assumption for Piezoelectric Laminate Beam Theory." Advanced Materials Research 163-167 (December 2010): 2101–5. http://dx.doi.org/10.4028/www.scientific.net/amr.163-167.2101.

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An attempt is made to extend the double superposition hypothesis for elastic laminate analysis to piezoelectric laminate structure analysis. In addition to the displacement, the double superposition technique is also applied to the electric potential. The double-superposition hypothesis for piezoelectric laminate analysis can predict the zigzag feature of the field variables along the transverse direction in piezoelectric laminates. Moreover, the elastic field computational cost of double superposition assumption is no more than that of high-order shear theories for global coordinates, and the
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46

Kenny, A., A. Palazzolo, G. T. Montague, and A. F. Kascak. "Theory and Test Correlation for Laminate Stacking Factor Effect on Homopolar Bearing Stiffness." Journal of Engineering for Gas Turbines and Power 126, no. 1 (2004): 142–46. http://dx.doi.org/10.1115/1.1615258.

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The effect of the laminate stacking factor on homopolar magnetic bearing performance is examined. Stacked laminates are used on the bearing rotor and in the stator. These laminate stacks have anisotropic permeability. Equations for the effect of the stacking factor on homopolar bearing position stiffness are derived. Numerical results are calculated and compared to measurements. These results provide an answer for the common discrepancy between test and theory for homopolar magnetic bearing position stiffnesses.
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47

Huang, Zheng-Ming, X. C. Teng, and S. Ramakrishna. "Progressive Failure Analysis of Laminated Knitted Fabric Composites Under 3-Point Bending." Journal of Thermoplastic Composite Materials 14, no. 6 (2001): 499–522. http://dx.doi.org/10.1106/uw1g-83l2-91w9-g47y.

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The bending behavior of laminated beams reinforced with differently arranged plain-weft knitted fabrics has been investigated in this paper. Experiments were carried out to measure the bending stiffness and strength of six layers knitted fabric rein-forced epoxy composite laminates under 3-point bending. The laminate lay-ups of [0/0/0/0/0/0], [90/90/90/90/90/90] and [0/-45/45/45/-45/0] have been taken into account, where 0 denotes that the fabric wale direction is arranged along the beam axial direction. A simulation procedure is presented to analyze the bending property of the laminated beams
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48

Mahadevan, S., and X. Liu. "Probabilistic Optimum Design of Composite Laminates." Journal of Composite Materials 32, no. 1 (1998): 68–82. http://dx.doi.org/10.1177/002199839803200104.

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This paper proposes a procedure for the optimum design of composite laminates under probabilistic considerations. The problem is formulated to consider the minimization of laminate weight as the objective function and the reliability requirements as the constraints. Both system-level and element-level reliabilities are considered. The first-order reliability method (FORM) is used to estimate the reliability of each ply group, and system reliability is computed based on series or parallel system assumptions. The Tsai-Wu strength criterion is adopted to derive the limit state function of individ
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Naresh, Kakur, Shankar Krishnapillai, and Ramachandran Velmurugan. "Effect of Fiber Orientation on Carbon/Epoxy and Glass/Epoxy Composites Subjected to Shear and Bending." Solid State Phenomena 267 (October 2017): 103–8. http://dx.doi.org/10.4028/www.scientific.net/ssp.267.103.

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In this study, the Interlaminar shear strength (ILSS) and flexural properties for five different laminate orientations [0°, 45°, [45°/-45°/45°]s, [±45°/0°/90°]s and 90°] of unidirectional carbon fiber reinforced plastic (CRP) and glass fiber reinforced plastic (GRP) composites are investigated. The different approach is used by applying the tensile load on notched specimens for measuring the inter-laminar shear strength. The theoretical flexural properties are obtained using the classical laminate theory [CLT]. The good agreement is obtained between the theoretical model and experimental resul
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Gadade, Appaso M., Achchhe Lal, and Bhairu N. Singh. "Progressive Failure Analysis of Laminated Composite Plate by Using Higher Order Shear Deformation Theory." Applied Mechanics and Materials 592-594 (July 2014): 1151–54. http://dx.doi.org/10.4028/www.scientific.net/amm.592-594.1151.

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A finite element analysis procedure is developed for progressive failure analysis of laminated composite plates under in plane tensile loading. A finite element model is based on higher order shear deformation theory (HSDT) with seven degrees of freedom. The degradation technique used for degradation of material properties of a failed ply is a ply discounting approach. The mode dependant Hashin and Lee failure criterion is used for the progressive failure analysis. The results of first ply failure load and last ply failure load are obtained for different stacking sequence of composite plate. T
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