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Journal articles on the topic 'Angle-ply laminated composites'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

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1

Al-Madani, Ramadan A., M. Jarnaz, K. Alkharmaji, and M. Essuri. "Finite Element Modeling of Composites System in Aerospace Application." Applied Mechanics and Materials 245 (December 2012): 316–22. http://dx.doi.org/10.4028/www.scientific.net/amm.245.316.

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The characteristics of composite materials are of high importance to engineering applications; therefore the increasing use as a substitute for conventional materials, especially in the field of aircraft and space industries. It is a known fact that researchers use finite element programs for the design and analysis of composite structures, use of symmetrical conditions especially in complicated structures, in the modeling and analysis phase of the design, to reduce processing time, memory size required, and simplifying complicated calculations, as well as considering the response of composite structures to different loading conditions to be identical to that of metallic structures. Finite element methods are a popular method used to analyze composite laminate structures. The design of laminated composite structures includes phases that do not exist in the design of traditional metallic structures, for instance, the choice of possible material combinations is huge and the mechanical properties of a composite structure, which are anisotropic by nature, are created in the design phase with the choice of the appropriate fiber orientations and stacking sequence. The use of finite element programs (conventional analysis usually applied in the case of orthotropic materials) to analysis composite structures especially those manufactured using angle ply laminate techniques or a combination of cross and angle ply techniques, as well considering the loading response of the composite structure to be identical to that of structures made of traditional materials, has made the use of, and the results obtained by using such analysis techniques and conditions questionable. Hence, the main objective of this paper is to highlight and present the results obtained when analyzing and modeling symmetrical conditions as applied to commercial materials and that applied to composite laminates. A comparison case study is carried out using cross-ply and angle-ply laminates which concluded that, if the composition of laminate structure is pure cross-ply, the FEA is well suited for predicting the mechanical response of composite structure using principle of symmetry condition. On the other hand that is not the case for angle-ply or mixed-ply laminate structure.

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2

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 (October 1, 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 is described. The results are then used to predict the nonlinear response of unidirectional laminae and angle-ply laminates. Comparison between theory and experiment for compression loading of AS4/3502 graphite-epoxy, angle-ply laminates shows excellent correlation.

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3

Wang, Yuan Ruo, and Tsu-Wei Chou. "Three-Dimensional Transient Interlaminar Thermal Stresses in Angle-Ply Composites." Journal of Applied Mechanics 56, no. 3 (September 1, 1989): 601–8. http://dx.doi.org/10.1115/1.3176134.

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This paper studies the three-dimensional transient interlaminar thermal stresses in elastic, angle-ply laminated composites due to sudden changes in the thermal boundary conditions. The transient temperature field and transient interlaminar thermal stresses of the laminate are obtained by solving the heat conduction equation and by a zeroth-order perturbation analysis of the equilibrium equations, respectively. Numerical results for a four-layer angle-ply laminate have shown that the interlaminar normal stress near the free edge is significantly higher than that in the interior region and it increases rapidly with the fiber volume fraction.

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4

Kim, K. S., and C. S. Hong. "Delamination Growth in Angle-Ply Laminated Composites." Journal of Composite Materials 20, no. 5 (September 1986): 423–38. http://dx.doi.org/10.1177/002199838602000502.

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5

Murakami, H. "A Mixture Theory for Wave Propagation in Angle-Ply Laminates, Part 1: Theory." Journal of Applied Mechanics 52, no. 2 (June 1, 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 constituents of the composite. For the special case of isotropic lamina the variational approach yields the same results as those derived by the asymptotic mixture theory with multiple scales [10] which requires the solution of the MBVP’s. The advantage of the variational approach over the alternative is that it makes the application of the technique feasible to wave propagation in fiber-reinforced and particulate composites. The application of the mixture model to angle-ply laminates is deferred to the second part of the paper, which also contains a study of dispersion of time harmonic waves in angle-ply laminates.

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6

Wu, Mengjin, Ruosi Yan, Zhihui Xia, Bao Shi, Sainan Wei, Wei Zhang, and Lixia Jia. "Characterization of mechanical properties of stab-resistant angle-ply flexible composites." Journal of Engineered Fibers and Fabrics 15 (January 2020): 155892502093555. http://dx.doi.org/10.1177/1558925020935554.

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In this study, we fabricated para-aramid flexible angle-ply-laminated hybrid composites based on weft-knitted reinforcements. Here, four kinds of weft-knitted reinforcements with rib, interlock, punto di roma, and two-thread fleecy were prepared using para-aramid spun yarn. They were then compounded with silicone rubber and waterborne polyurethane–acrylate using the coating method. The layers were angle-plied to produce stab-resistant, weft-knitting-reinforced, flexible laminated hybrid composites. Tensile and tearing strengths of the para-aramid-knitted reinforcements were investigated. Relevant response analyses were chosen to evaluate the influence of three independent variables, including weft-knitted structures, matrix types, and ply orientations. The results showed that the mechanical properties of the composites were dependent on weft-knitted structures and matrix types. The fabric with high strength and the degree in approximate isotropy of stress in all composites was most suited for the reinforcement of the flexible stab-resistant composite. The optimum design with the best stab-resistant property was punto di roma/waterborne polyurethane–acrylate with a ply orientation angle of [0°/0°/0°/0°]. The interlaminar adhesion of flexible stab-resistant composite based on waterborne polyurethane–acrylate can be improved by increasing the surface roughness of fabric structure or modifying its surface.

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7

Kalita, Kanak, M. Ramachandran, Pramod Raichurkar, Sneha D. Mokal, and Salil Haldar. "Free Vibration Analysis of Laminated Composites by a Nine Node Isoparametric Plate Bending Element." Advanced Composites Letters 25, no. 5 (September 2016): 096369351602500. http://dx.doi.org/10.1177/096369351602500501.

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Composite laminates are being widely used in engineering industry primarily due to their high strength-to-weight ratio. Considerable research has been carried out to understand the static and dynamic behaviour of laminated composite plates. There is much demand for developing efficient finite element codes which can predict the dynamic responses of laminated structures at affordable computational cost. In this paper a nine node isoparametric plate bending element has been used for free vibration analysis of laminated composite plate. The first-order shear deformation theory (FSDT) has been incorporated in the element formulation. Composite plates with different side-to-thickness ratio (a/h), ply orientations and number of layers have been analysed. Based on comparison with literature data, we propose that the present formulation is capable of yielding highly accurate results. Laminated composites with central cut-outs are also studied. Novel data is reported for skew laminated composites. It is found that the natural frequency increases with the increase in skew angle (a) and decreases with increase in aspect ratio (b/a) and thickness (h).

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8

Dey, Sudip, and Amit Karmakar. "Effect of Location of Delamination on Free Vibration of Cross-Ply Conical Shells." Shock and Vibration 19, no. 4 (2012): 679–92. http://dx.doi.org/10.1155/2012/726986.

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Location of delamination is a triggering parameter for structural instability of laminated composites. In this paper, a finite element method is employed to determine the effects of location of delamination on free vibration characteristics of graphite-epoxy cross-ply composite pre-twisted shallow conical shells. The generalized dynamic equilibrium equation is derived from Lagrange's equation of motion neglecting Coriolis effect for moderate rotational speeds. The formulation is exercised by using an eight noded isoparametric plate bending element based on Mindlin's theory. Multi-point constraint algorithm is utilized to ensure the compatibility of deformation and equilibrium of resultant forces and moments at the delamination crack front. The standard eigen value problem is solved by applying the QR iteration algorithm. Finite element codes are developed to obtain the numerical results concerning the effects of location of delamination, twist angle and rotational speed on the natural frequencies of cross-ply composite shallow conical shells. The mode shapes are also depicted for a typical laminate configuration. Numerical results obtained from parametric studies of both symmetric and anti-symmetric cross-ply laminates are the first known non-dimensional natural frequencies for the type of analyses carried out here.

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9

Kanasogi, R. M., and M. C. Ray. "Active Constrained Layer Damping of Smart Skew Laminated Composite Plates Using 1–3 Piezoelectric Composites." Journal of Composites 2013 (June 5, 2013): 1–17. http://dx.doi.org/10.1155/2013/824163.

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This paper deals with the analysis of active constrained layer damping (ACLD) of smart skew laminated composite plates. The constraining layer of the ACLD treatment is composed of the vertically/obliquely reinforced 1–3 piezoelectric composites (PZCs). A finite element model has been developed for accomplishing the task of the active constrained layer damping of skew laminated symmetric and antisymmetric cross-ply and antisymmetric angle-ply composite plates integrated with the patches of such ACLD treatment. Both in-plane and out-of-plane actuations by the constraining layer of the ACLD treatment have been utilized for deriving the finite element model. The analysis revealed that the vertical actuation dominates over the in-plane actuation. Particular emphasis has been placed on investigating the performance of the patches when the orientation angle of the piezoelectric fibers of the constraining layer is varied in the two mutually orthogonal vertical planes. Also, the effects of varying the skew angle of the substrate laminated composite plates and different boundary conditions on the performance of the patches have been studied. The analysis reveals that the vertically and the obliquely reinforced 1–3 PZC materials should be used for achieving the best control authority of ACLD treatment, as the boundary conditions of the smart skew laminated composite plates are simply supported and clamped-clamped, respectively.

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10

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 (October 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 in the ω direction, in order to have always a pure one-dimensional state of stress. We show that for the most common unidirectional fibre-reinforced materials, the angle ω is, in most cases, close to the α direction of the fibres. This result permits a complete experimental characterisation of the laminate, which then does not need any a priori knowledge of the elastic properties of the elementary layer. In addition, it provides a simple method to verify the predictions of the laminate behaviour obtained by the Classical Laminated Plate Theory (CLPT) when the elementary layer is completely known. The paper ends with numerical examples and with the results of some experimental tests.

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11

Ye, Jian Qiao. "Edge effects in angle-ply laminated hollow cylinders." Composite Structures 52, no. 2 (May 2001): 247–53. http://dx.doi.org/10.1016/s0263-8223(00)00172-0.

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12

Chaudhuri, Reaz A. "Analysis of laminated shear-flexible angle-ply plates." Composite Structures 67, no. 1 (January 2005): 71–84. http://dx.doi.org/10.1016/j.compstruct.2004.01.002.

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13

Yi, Sung, and H. H. Hilton. "Free Edge Stresses in Elastic and Viscoelastic Composites Under Uniaxial Extension, Bending, and Twisting Loadings." Journal of Engineering Materials and Technology 119, no. 3 (July 1, 1997): 266–72. http://dx.doi.org/10.1115/1.2812255.

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Time-dependent interlaminar stresses in elastic and viscoelastic laminated composites subjected to arbitrary combinations of axial extension, bending and/or twisting loads are obtained based on integral constitutive relations and Pipes and Pagano’s displacement field for laminates under a generalized plane deformation state. Numerical results obtained from the present formulation are compared against experimental data and excellent agreement within two percent was obtained between these results. Time-dependent interlaminar stresses for cross-ply and angle-ply laminates subjected to uniaxial extension, bending and twisting are also presented. Appreciable stress relaxation occurred during the loading period resulting in decreased magnitudes of residual stresses. It is seen that the rate of interlaminar shear stress relaxation is greater than the normal one, since the relaxation of shear moduli is larger than that of the normal moduli.

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14

Topal, Umut. "Frequency optimization of laminated composite spherical shells." Science and Engineering of Composite Materials 19, no. 4 (December 1, 2012): 381–86. http://dx.doi.org/10.1515/secm-2012-0026.

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AbstractThis paper deals with frequency optimization of symmetrically laminated angle-ply spherical shells. The design objective is the maximization of the fundamental frequency, and the design variable is the fiber orientation in the layers. The first-order shear deformation theory and nine-node isoparametric finite element model are used for the finite element solution of the laminates. The modified feasible direction (MFD) method is used for the optimization routine. For this purpose, a program based on FORTRAN is used. Finally, the numerical analysis is carried out to investigate the effects of geometrical parameters and boundary conditions on the optimal designs, and the results are compared.

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15

Huang, Bin, Yan Guo, Ji Wang, Jianke Du, Zhenghua Qian, Tingfeng Ma, and Lijun Yi. "Bending and free vibration analyses of antisymmetrically laminated carbon nanotube-reinforced functionally graded plates." Journal of Composite Materials 51, no. 22 (December 20, 2016): 3111–25. http://dx.doi.org/10.1177/0021998316685165.

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In this paper, a simple four-variable first-order shear deformation theory is further applied to solve the bending and free vibration problems of antisymmetrically laminated functionally graded carbon nanotube (FG-CNT)-reinforced composite plates. The adopted four-variable theory contains only four unknowns in its displacement field which is less than the Reddy’s first-order theory. The equations of motion are derived from the Hamilton’s principle with the help of specific boundary conditions. Laminated FG-CNT-reinforced plates with different distribution types of carbon nanotube through the thickness are considered. The material properties of individual layer are estimated by using the extended rule of mixture. Analytical solutions of various simply supported antisymmetric cross-ply and angle-ply laminates are given for case study. The effects of carbon nanotube volume fraction, length to width ratio and thickness to width ratio on the non-dimensional fundamental frequency and the central deflection are investigated for antisymmetrically laminated FG-CNT-reinforced plates.

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16

Zenkour, AM, and AF Radwan. "Free vibration analysis of multilayered composite and soft core sandwich plates resting on Winkler–Pasternak foundations." Journal of Sandwich Structures & Materials 20, no. 2 (June 12, 2016): 169–90. http://dx.doi.org/10.1177/1099636216644863.

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Free vibration of laminated composite and soft core sandwich plates resting on Winkler–Pasternak foundations using four-variable refined plate theory are presented. The theory accounts for the hyperbolic distribution of the transverse shear strains through the plate thickness, and satisfies the zero traction boundary conditions on the surfaces of the plate without using shear correction factors. Equations of motion are derived from the dynamic version of the principle of virtual work. Navier technique is employed to obtain the closed-form solutions of antisymmetric cross-ply, angle-ply, and soft core laminates or soft core sandwich plates resting on elastic foundations. Numerical results obtained using present theory are compared with three-dimensional elasticity solutions and those computed using the first-order and the other higher-order theories. It can be concluded that the proposed theory is not only accurate, but also efficient in predicting the natural frequencies of laminated composite and soft core sandwich plates resting on Winkler–Pasternak foundations.

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17

Chen, Lien-Wen, and Jenq-Yiing Yang. "Nonlinear vibration of antisymmetric imperfect angle-ply laminated plates." Composite Structures 23, no. 1 (January 1993): 39–46. http://dx.doi.org/10.1016/0263-8223(93)90072-x.

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18

Faroughi, S., E. Shafei, and D. Schillinger. "Isogeometric Stress, Vibration and Stability Analysis of In-Plane Laminated Composite Structures." International Journal of Structural Stability and Dynamics 18, no. 05 (May 2018): 1850070. http://dx.doi.org/10.1142/s0219455418500700.

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We present a computational study that develops isogeometric analysis based on higher-order smooth NURBS basis functions for the analysis of in-plane laminated composites. Focusing on the stress, vibration and stability analysis of angle-ply and cross-ply 2D structures, we compare the convergence of the strain energy error and selected stress components, eigen-frequencies and buckling loads according to overkill solutions. Our results clearly demonstrate that for in-plane laminated composite structures, isogeometric analysis is able to provide the same accuracy at a significantly reduced number of degrees of freedom with respect to standard [Formula: see text] finite elements. In particular, we observe that the smoothness of spline basis functions enables high-quality stress solutions, which are superior to the ones obtained with conventional finite elements.

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19

Harris, C. E., D. H. Allen, E. W. Nottorf, and S. E. Groves. "Modelling Stiffness Loss in Quasi-Isotropic Laminates Due to Microstructural Damage." Journal of Engineering Materials and Technology 110, no. 2 (April 1, 1988): 128–33. http://dx.doi.org/10.1115/1.3226020.

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Continuous fiber laminated composites are known to undergo substantial load induced damage in the form of matrix cracking, interior delamination, fiber fracture, etc. These damage modes produce significant losses in component performance measures such as stiffness, residual strength, and life. The authors have previously constructed a general model for predicting the response of laminated composites with damage. The current paper utilizes the model to predict stiffness loss as a function of damage in quasi-isotropic and angle-ply laminates with matrix cracks. It is shown that the model is capable of predicting the stiffness loss for any layup by utilizing the same input data, thus producing a model which is independent of stacking sequence. The favorable comparisons of the model to experimental results reported herein support the validity of the model.

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20

Hosseini-Toudeshky, Hossein, and Bijan Mohammadi. "Coupling of Continuum Damage Mechanics with De-Cohesive Element for Delamination Analysis in Laminated Composites." Advanced Materials Research 123-125 (August 2010): 527–30. http://dx.doi.org/10.4028/www.scientific.net/amr.123-125.527.

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To predict the progressive damages including the large delamination growth in composite laminates, a new interface de-cohesive constitutive law is developed which is compatible with 3D continuum damage mechanics (CDM). To avoid the difficulties of 3D mesh generation and 3D interface modeling between the layers, the interface element is implemented in the Reddy’s full layer-wise plate theory. An angle-ply laminate is analyzed to evaluate the developed CDM+Interface procedure in edge delamination initiation and evolution at final stage of CDM damage progress.

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21

Mohammadi, Bijan, Hossein Hosseini-Toudeshky, and Mohammad Homayoun Sadr-Lahidjani. "Damage Evolution of Laminated Composites Using Continuum Damage Mechanics Incorporate with Interface Element." Key Engineering Materials 385-387 (July 2008): 277–80. http://dx.doi.org/10.4028/www.scientific.net/kem.385-387.277.

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In this paper, 3D continuum damage mechanics (CDM) incorporated with layer-wise theory and interface element is employed to investigate the progressive damage inside and between the laminate's layers under quasi-static axial loading. For this purpose, a finite element program is developed. To simulate the delamination, a quadratic interface element is used which is compatible with the 8-node numerical layers of layer-wise theory. Matrix cracking and delamination initiation and propagation of [302/-302]s angle-ply laminate are investigated and the obtained results are compared with the available experimental evidence.

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22

He, Jian, Liang He, and Bin Yang. "Analysis on the impact response of fiber-reinforced composite laminates: an emphasis on the FEM simulation." Science and Engineering of Composite Materials 26, no. 1 (January 28, 2019): 1–11. http://dx.doi.org/10.1515/secm-2017-0222.

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AbstractThe effects of units, material parameters, and constitutive relationships on the dynamic mechanical response of composite laminates subjected to high- and low-velocity impacts were investigated. Additionally, the role of impact or shape, including hemispherical, flat, and conical, on the damage area of the adhesive layer and displacement of the center of the laminated plates was investigated. The results show that the energy absorption of composite laminates increases with impact velocity, and specific energy absorption changes with the density of the contact surface, which is affected by ply thickness. Moreover, the target energy absorption decreases with increasing layer angle. Under a low-velocity impact, the maximum contact force, damage area of the adhesive layer, and displacement of the center of the laminated plate increase as the impact energy increases, thus showing that impact energy is not directly related to contact duration and energy absorption of composite laminates. The results of different geometric shapes show that the damage area of the adhesive layer and the displacement of the center of the laminated plates are largest for a conical impactor and smallest for a flat impactor.

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23

LI, N., and S. MIRZA. "VIBRATION OF ANTISYMMETRIC ANGLE-PLY LAMINATED PLATES INCLUDING TRANSVERSE SHEAR DEFORMATION." Mechanics of Composite Materials and Structures 2, no. 2 (June 1995): 163–75. http://dx.doi.org/10.1080/10759419508945836.

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24

Cakiroglu, Celal, Gebrail Bekdaş, and Zong Geem. "Harmony Search Optimisation of Dispersed Laminated Composite Plates." Materials 13, no. 12 (June 26, 2020): 2862. http://dx.doi.org/10.3390/ma13122862.

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One of the major goals in the process of designing structural components is to achieve the highest possible buckling load of the structural component while keeping the cost and weight at a minimum. This paper illustrates the application of the harmony search algorithm to the buckling load maximisation of dispersed laminated composite plates with rectangular geometry. The ply thicknesses and fiber orientation angles of the plies were chosen as the design variables. Besides the commonly used carbon fiber reinforced composites, boron/epoxy and glass/epoxy composite plates were also optimised using the harmony search algorithm. Furthermore, the optimisation algorithm was applied to plates with three different aspect ratios (ratio of the longer side length to the shorter side length of the plate). The buckling loads of the plates with optimised dispersed stacking sequences were compared to the buckling loads of plates with the commonly applied 0°, ±45°, and 90° fiber angle sequence and identical ply thicknesses. For all three aspect ratios and materials in this study, the dispersed stacking sequences performed better than the plates with regular stacking sequences.

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25

Zhang, Daxu, Jianqiao Ye, and Dennis Lam. "Free-Edge and Ply Cracking Effect in Angle-Ply Laminated Composites Subjected to In-Plane Loads." Journal of Engineering Mechanics 133, no. 12 (December 2007): 1268–77. http://dx.doi.org/10.1061/(asce)0733-9399(2007)133:12(1268).

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26

Turvey, G. J., and M. Y. Osman. "Large deflection initial failure analysis of angle-ply laminated plates." Composite Structures 25, no. 1-4 (January 1993): 529–39. http://dx.doi.org/10.1016/0263-8223(93)90201-z.

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27

Topal, Umut. "Frequency optimization of laminated composite plates with different intermediate line supports." Science and Engineering of Composite Materials 19, no. 3 (September 1, 2012): 295–306. http://dx.doi.org/10.1515/secm-2012-0004.

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AbstractThis paper deals with frequency optimization of symmetrically laminated 4-layered angle-ply plates with one or two different intermediate line supports. The design objective is the maximization of the fundamental frequency and the design variable is the fiber orientation in the layers. The first order shear deformation theory and nine-node isoparametric finite element model are used for finding the natural frequencies of laminates. The modified feasible direction method is used for the optimization routine. For this purpose, a program based on FORTRAN is used. Finally, the numerical analysis is carried out to investigate the effects of location of the internal line supports, plate aspect ratios and boundary conditions on the optimal designs and the results are compared.

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28

SARANGI, SAROJ KUMAR, and M. C. Ray. "SMART CONTROL OF NONLINEAR VIBRATIONS OF LAMINATED PLATES USING ACTIVE FIBER COMPOSITES." International Journal of Structural Stability and Dynamics 12, no. 06 (December 2012): 1250050. http://dx.doi.org/10.1142/s0219455412500502.

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This paper deals with the geometrically nonlinear dynamic analysis of smart laminated composite plates integrated with the patches of active constrained layer damping (ACLD) treatment. The constraining layer of the ACLD treatment is made of active fiber composite (AFC) materials. The Von Kármán type nonlinear strain–displacement relations and the first-order shear deformation theory (FSDT) are adopted in deriving the coupled electromechanical nonlinear finite element (FE) model. The Golla–Hughes–McTavish (GHM) method is implemented to model the constrained viscoelastic layer of the ACLD treatment in time domain. Symmetric/antisymmetric cross-ply and antisymmetric angle-ply laminated substrate plates are considered in the numerical analyses. The results indicate that the ACLD patches significantly improve the damping characteristics of the plates for suppressing the geometrically nonlinear transient vibrations of the plates. The effects of variation of piezoelectric fiber orientation in the AFC constraining layer on the control authority of the ACLD patches have also been investigated.

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29

GORJI, M. "Large deflection of antisymmetric angle-ply composite laminated plates in cylindrical bending." Composites Science and Technology 46, no. 2 (1993): 167–74. http://dx.doi.org/10.1016/0266-3538(93)90172-d.

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30

Şahi̇n, Ömer Sinan. "Thermal buckling of hybrid angle-ply laminated composite plates with a hole." Composites Science and Technology 65, no. 11-12 (September 2005): 1780–90. http://dx.doi.org/10.1016/j.compscitech.2005.03.007.

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31

Patel, B. P., Y. Nath, and K. K. Shukla. "Thermo-elastic buckling characteristics of angle-ply laminated elliptical cylindrical shells." Composite Structures 77, no. 1 (January 2007): 120–24. http://dx.doi.org/10.1016/j.compstruct.2005.06.001.

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32

Gorji, M. "Nonlinear Analysis of Angle-Ply Laminated Strips in Cylindrical Bending." Journal of Reinforced Plastics and Composites 11, no. 12 (December 1992): 1396–430. http://dx.doi.org/10.1177/073168449201101205.

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33

Ashour, A. S. "Vibration of angle-ply symmetric laminated composite plates with edges elastically restrained." Composite Structures 74, no. 3 (August 2006): 294–302. http://dx.doi.org/10.1016/j.compstruct.2005.04.003.

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34

Nallim, Liz Graciela, and Ricardo Oscar Grossi. "Vibration of angle-ply symmetric laminated composite plates with edges elastically restrained." Composite Structures 81, no. 1 (November 2007): 80–83. http://dx.doi.org/10.1016/j.compstruct.2006.07.012.

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35

Mohammadrezazadeh, Shahin, and Ali Asghar Jafari. "Nonlinear vibration analysis of laminated composite angle-ply cylindrical and conical shells." Composite Structures 255 (January 2021): 112867. http://dx.doi.org/10.1016/j.compstruct.2020.112867.

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36

Topal, Umut. "Thermal buckling load optimization of laminated general quadrilateral and trapezoidal thin plates." Science and Engineering of Composite Materials 20, no. 1 (February 1, 2013): 87–94. http://dx.doi.org/10.1515/secm-2012-0103.

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AbstractThis paper deals with thermal buckling load optimization of symmetrically laminated angle-ply general quadrilateral and trapezoidal thin plates. The objective function is to maximize the critical temperature capacity of the quadrilateral and trapezoidal laminated plates and the fiber orientation is considered as a design variable. The mathematical formulation is based on the classical laminated plate theory for the frequency analysis. The modified feasible direction method is used as the optimization routine. Therefore, a program based on FORTRAN is used. Finally, the significant effects of aspect ratios, boundary conditions, taper ratios and unsymmetric trapezoidal plates on the optimal results are investigated and the results are compared.

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Sabik, A. "In-plane shear nonlinearity in failure behavior of angle-ply laminated shells." Composite Structures 225 (October 2019): 111164. http://dx.doi.org/10.1016/j.compstruct.2019.111164.

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Ju, Shen-Haw, Wen-Yu Liang, Hsin-Hsiang Hsu, and Jiann-Quo Tarn. "Analytic solution of angle-ply laminated plates under extension, bending, and torsion." Journal of Composite Materials 54, no. 8 (September 9, 2019): 1093–106. http://dx.doi.org/10.1177/0021998319873025.

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This paper develops a Hamiltonian state space approach for analytic determination of deformation and stress fields in multilayered monoclinic angle-ply laminates under the combined action of extension, bending, and torsion. The present solution satisfies the equations of anisotropic elasticity, the end conditions, the traction-free boundary conditions on the four edge surfaces of the rectangular section, and the interfacial continuity conditions in multilayered laminates. The proposed method only requires the solutions of matrix and eigen equations, regardless of the number or lamination of the layers. The finite element analyses are used to validate the accuracy of the analysis. The analytical solution and the numerical solutions are in excellent agreement.

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Hosokawa,, Kenji, Masaki Murayama,, and Toshiyuki Sakata,. "Free Vibration Analysis of Angle-Ply Laminated Circular Cylindrical Shells with Clamped Edges." Science and Engineering of Composite Materials 9, no. 2 (June 2000): 75–82. http://dx.doi.org/10.1515/secm.2000.9.2.75.

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40

Lee, Sang-Kwon, Sungil Bang, and Jiseon Back. "Effect of laminated angle of carbon fiber on interior noise on an enclosure under center point excitation." Journal of Reinforced Plastics and Composites 38, no. 3 (October 22, 2018): 117–32. http://dx.doi.org/10.1177/0731684418808091.

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This paper presents a novel method to control passively the interior noise of an enclosure such as car cabin by using the movement of the peak level and peak frequency according to the laminated angle of carbon fiber reinforced plastic composite plate. Recently, the use of carbon fiber reinforced plastic laminated plates in a car has been increased in order to reduce the weight of a car. For example, the metal plate roof has been replaced by the carbon fiber reinforced plastic plate roof for weight reduction of an electric vehicle. The characteristics of the interior noise inside of a car made of carbon fiber reinforced plastic plate roof can be changed according to the laminated angle of carbon fiber. In this paper, how this characteristic is changed was studied based on the effect of laminated angle of carbon fiber. In order to perform this study, a closed box with one flexible side wall and five acoustically rigid side walls was modelled as the interior compartment of a car. The flexible side wall of the closed box regards as the roof plate of a car. For the flexible side wall of the closed box, three carbon fiber reinforced plastic plates with different angle-ply (± θ) laminates each other were used. Therefore, three carbon fiber reinforced plastic plates with the fiber lamination angles of [−15/15/15/–15]s, [–30/30/30/–30]s, and [–75/75/75/–75]s were fabricated and used as the flexible side wall of the closed box. How the interior noise inside of the closed box was changed according to the laminated angle was studied by theoretical and numerical methods. For the validation of theoretical and numerical methods, the experimental work was performed. Finally, the carbon fiber reinforced plastic plate roof for a passenger car was numerically simulated, and the effect of the laminated angle on the interior noise was studied.

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Bishay, Peter L., and Christian Aguilar. "Parametric Study of a Composite Skin for a Twist-Morphing Wing." Aerospace 8, no. 9 (September 13, 2021): 259. http://dx.doi.org/10.3390/aerospace8090259.

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Although the benefits of morphing wings have been proven in many studies in the last few decades, the wing skin design remains one of the challenges to advancing and implementing the morphing technology. This is due to the conflicting design requirements of high out-of-plane stiffness to withstand aerodynamic loads and low in-plane stiffness to allow morphing with the available actuation forces. Advancements in the design of hybrid and flexible composites might allow for design solutions that feature this balance in stiffness required for this application. These composites offer new design parameters, such as the number of plies, the fiber-orientation angle of each ply in the skin laminate, and the spatial distribution of the plies on the skin surface. This paper presents a parametric study of a composite skin for a twist-morphing wing. The skin is made of periodic laminated composite sections, called “Twistkins”, integrated in an elastomeric outer skin. The twisting deformation is localized in the elastomeric sections between the Twistkins. The design parameters considered are the number of plies in the composite Twistkins, the fiber-orientation angle of the plies, the torsional rigidity of the elastomer, the width ratio, and the number of elastomeric sections. The computational analysis results showed that the torsional compliance can be increased by increasing the width ratio, decreasing the number of elastomeric sections, number of composite plies and the elastomer’s torsional rigidity. However, this would also lead to a decrease in the out-of-plane stiffness. The nonlinearity and rates at which these parameters affect the skin’s behavior are highlighted, including the effect of the fiber-orientation angle of the laminate plies. Hence, the study guides the design process of this twist-morphing skin.

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Benzair, A., M. Maachou, KH Amara, and A. Tounsi. "Effect of transverse cracks on the elastic properties of high temperature angle-ply laminated composites." Computational Materials Science 37, no. 4 (October 2006): 470–75. http://dx.doi.org/10.1016/j.commatsci.2005.11.006.

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Cai, J. B., W. Q. Chen, and G. R. Ye. "Effect of interlaminar bonding imperfections on the behavior of angle-ply laminated cylindrical panels." Composites Science and Technology 64, no. 12 (September 2004): 1753–62. http://dx.doi.org/10.1016/j.compscitech.2003.12.009.

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Yan, Wei, J. Ying, and W. Q. Chen. "The behavior of angle-ply laminated cylindrical shells with viscoelastic interfaces in cylindrical bending." Composite Structures 78, no. 4 (June 2007): 551–59. http://dx.doi.org/10.1016/j.compstruct.2005.11.017.

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Sheng, Hong Yu, and Jianqiao Ye. "State space solution for axisymmetric bending of angle-ply laminated cylinder with clamped edges." Composite Structures 68, no. 1 (April 2005): 119–28. http://dx.doi.org/10.1016/j.compstruct.2004.03.006.

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Yapici, A. "Thermal Buckling Behavior of Hybrid-Composite Angle-Ply Laminated Plates with an Inclined Crack." Mechanics of Composite Materials 41, no. 2 (March 2005): 131–38. http://dx.doi.org/10.1007/s11029-005-0040-x.

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Abu-Farsakh, Ghazi A., Amin H. Almasri, and Dana H. Qa’dan. "Stress concentration around a central hole as affected by material nonlinearity in fibrous composite laminated plates subject to in-plane loading." Science and Engineering of Composite Materials 22, no. 1 (January 1, 2015): 31–36. http://dx.doi.org/10.1515/secm-2013-0125.

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AbstractThe distribution of stresses in laminated composite plates with a central circular hole and having various stacking sequences, different geometric dimensions and subjected to in-plane axial tensile loading was investigated. The ANSYS computer program was utilized using the finite element method to study the linear and nonlinear material effects. A new method was proposed for the purpose of incorporating the material nonlinearity model into the ANSYS computer program using the secant modulus material model. The aim of the authors is to analyze the effect of D/b and a/b ratios (where D is hole diameter, b is plate width, and a is plate length) on stresses induced in such plates. Analysis was carried out for angle-ply, four-layered symmetric laminated rectangular plates with various stacking sequences [±θ]s.

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Matsunaga, Hiroyuki. "Free vibration and stability of angle-ply laminated composite and sandwich plates under thermal loading." Composite Structures 77, no. 2 (January 2007): 249–62. http://dx.doi.org/10.1016/j.compstruct.2005.07.002.

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Das Neogi, Sanjoy, Amit Karmakar, and Dipankar Chakravorty. "Study of Dynamic Behavior of Multilayered Clamped Composite Skewed Hypar Shell Roofs under Impact Load." Journal of Engineering 2013 (2013): 1–10. http://dx.doi.org/10.1155/2013/192176.

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With advancement in the field of structural engineering, hunt for smarter materials has channelised the research towards the application of composite material. It is the high specific weight and specific stiffness of this material that have drawn the interest of different industrial sectors. Civil engineers also picked up composites to use it as a roofing material. Laminated composite shells, which can cover large column-free area and reduces dead weight of structure, show vulnerability under sudden impact due to their low transverse shear resistances. This study utilises finite element tool to investigate the dynamic response of a multilayered laminated composite hypar shells for fully clamped boundary condition. This class of shells is unique in a sense that the curvature has only the radius of cross curvature and these shells do not admit easy closed form solution particularly when the boundary conditions are complicated. Contact behavior of impactor and impacted mass has been modeled by modified Hertzian contact law and time-dependent equations are solved using Newmark’s time integration technique. Basic aim is to analyse the shell for symmetrically placed multilayered angle and cross ply lamination under different impact velocities.

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Shooshtari, A., and S. Razavi. "Nonlinear free and forced vibrations of anti-symmetric angle-ply hybrid laminated rectangular plates." Journal of Composite Materials 48, no. 9 (April 18, 2013): 1091–111. http://dx.doi.org/10.1177/0021998313482156.

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