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Academic literature on the topic 'Composite Plates'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

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Journal articles on the topic "Composite Plates"

1

Pasnur, Pallavi K., and ,. Anant V. Kharche. "A Review Paper on Laminated Composite Plates." Journal of Advances and Scholarly Researches in Allied Education 15, no. 2 (April 1, 2018): 612–16. http://dx.doi.org/10.29070/15/56936.

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Khandan, Rasoul, Philip Sewell, Siamak Noroozi, and Mohammad Reza Ramazani. "FE Design Tool for Laminated Composite Plates." Applied Mechanics and Materials 248 (December 2012): 379–83. http://dx.doi.org/10.4028/www.scientific.net/amm.248.379.

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Considering the non-linearity, complexity and anisotropy of constitutive equations in composite materials, numerical methods are essential to evaluate the behaviour of this material. The finite element method (FEM) is a powerful computational technique for the solution of differential and integral equations that arise in various fields of engineering and applied science such as composite materials. Here, an FEM tool is designed to analyse non-linearity in the behaviour of composites caused by the effect of transverse shear and twist in laminated composite plates. The tool is established by using FEM for composites in ABAQUS combined with programming in Python to run the tests for all possible fibre orientations in laminated composite plates. It is shown that the tool has the ability to design laminated composite plates by considering the effect of transverse shear and the tool’s output provides results for all different fibre orientations. It is demonstrated that there is good agreement between numerical results obtained from this tool and experimental results. The advantages of the tool give designers the opportunity to use this tool for wide range of products.

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3

Dibyajyoti, D., and B. Alfia. "Review on laminated composite plates." Proceedings of the 12th Structural Engineering Convention, SEC 2022: Themes 1-2 1, no. 1 (December 19, 2022): 83–88. http://dx.doi.org/10.38208/acp.v1.477.

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A composite material is a combination of different material which can be assembled to provide required engineering properties like bending, buckling, stiffness etc. It can give better properties than those of individual components. A lamina is the building block of modern composite laminated structures. A lamina is also known as a ply, or a layer. A laminate has several layers of lamina, or laminae. Since the early years of engineering, various types of laminated composite materials have been used in various engineering fields, such as in aerospace, military and automotive industries that are subjected to high temperatures. Thermal stress caused due to change in temperature, increase in temperature causes the changes in material properties of a plate which in turn complicates the analysis and design and may affect the structure also. Therefore, the analysis of thermal stress in design of structure is very important. A critical review of available literature for the prediction of the behaviour of laminated composites under thermal conditions is carried out and summarized. This work attempts to review the studies carried out from 2000 on laminated composite plates by representing classification based on Classical laminate plate concept, First order shear deformation theory, Higher order shear deformation theory, Layerwise theory and Thermal stress on laminated plates.

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Gautam, Rajeev K., and Kamal K. Kar. "Synthesis and Properties of Highly Conducting Natural Flake Graphite/Phenolic Resin Composite Bipolar Plates for Pem Fuel Cells." Advanced Composites Letters 25, no. 4 (July 2016): 096369351602500. http://dx.doi.org/10.1177/096369351602500402.

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Electrically conductive composite bipolar plates consisting of resole-typed phenol formaldehyde resin and natural flake graphite (NFG) have been fabricated by compression molding technique at room temperature. The aim of this study is to investigate the effects of NFG content, molding pressure, and nano-sized carbon black (NCB) on the properties of composite bipolar plates. The NFG/resin composite plates have been studied for various properties including electrical, mechanical, and thermal properties. It has been observed that the composite plates prepared at NFG content of 45 wt%, NCB content of 4.5 wt%, and molding pressure of 15 MPa have optimum properties. Under optimal conditions, bipolar plates showed better properties at bulk density 1.79 g/cc, electrical conductivity 358 S/cm, flexural strength 29.3 MPa, compressive strength 43.6 MPa, water absorption 0.34% and surface microhardness 72.6 HV. Additionally, the plates were thermally stable up to 300°C. Hence, NFG/resin composites successfully fulfil the DOE-2015 requirements for bipolar plates in PEM fuel cells.

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Veerappan, Balasubramani, Sudharshan Vasudevan, and B. Karthikeyan. "Numerical Deflection Analysis of Rectangular Laminated Composite Plates - Truck Bed - Case Study." Materials Science Forum 1070 (October 13, 2022): 71–87. http://dx.doi.org/10.4028/p-o2qaka.

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Transport industry plays a vital role in development of economy of countries. To increase the load carrying capacity of the truck, the weight of truck bed may be reduced using fibre reinforced composite material. In this work, a numerical investigation is performed to reduce the weight of the truck bed using different types of laminated composites. An extensive study is conducted using unidirectional and woven fibres of glass, carbon and Kevlar fibres with polyester, epoxy and vinyl ester resins. Carbon fibre laminated plates have higher stiffness than Glass and Kevlar composite plates. Asymmetrically hybrid composite plates have lower stiffness than symmetrically hybrid composite plates. It is observed that the stiffness of plate is increased when kevlar unidirectional fibres are arranged at top and bottom of the laminate. [K/Gw]S hybrid composite plates has the lowest deflection than other five hybrid composite plates. An optimization study is performed to identify the influencing parameter for deflection of the composite materials among material type, fibre volumetric fraction and the thickness of plate using Taguchi method. The results revealed that thickness of the plate has more influential than other two parameters.

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Mahieddine, Ali, and Mohammed Ouali. "Analysis of Delaminated Composite Plates." Advanced Materials Research 686 (April 2013): 104–8. http://dx.doi.org/10.4028/www.scientific.net/amr.686.104.

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A mathematical model for plates with partially delaminated layers is presented to investigate their behavior. In this formulation account is taken of lateral strains. The principal advantage of the element is that it allows the modeling of delamination anywhere in the structure. The region without delamination is modeled to carry constant peel and shear stresses; while the region with delamination is modeled by assuming that there is no peel and shear stress transfer between the top and bottom layers. Numerical results of the present model are presented and its performance is evaluated for static problems. Laminated beams and plates are often used as primary load-carrying structures. However, the mechanical properties of composite materials may degrade severely in the presence of damage. One of the common types of damage modes in laminated composites is delamination. The presence of delamination is one of the most prevalent life-limiting failure modes in laminated composite structures. Many researchers had been studying the effect of delamination. Wee and Boay [1] developed an analytical model to predict the critical load of a delaminated composite laminated beam. Lee et al. [2] investigated the buckling behavior of the beam plate with multiple delaminations under compression. Kapania and Wolfe [3] examined the buckling behavior of a beam plate with two delaminations of equal length. Wang et al. [4] improved the analytical solution by including the coupling between the flexural and axial vibrations of the delaminated sub-laminates. Lee et al. [5] studied a composite beam with arbitrary lateral and longitudinal multiple delamination. Finite-element methods have been developed using the layerwise theory by Kim et al. [6]. Tan and Tong [7] developed a dynamic analytical model for the identification of delamination embedded in a laminated composite beam. To investigate the effects of delamination of a plate layers, a finite-element model is developed. Both displacement continuity and force equilibrium conditions are imposed between the regions with and without delamination. The accuracy of the approach is verified by comparing results with previously published data.

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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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Hadi, Nabil Hassan, and Basim Jameel Hamood. "Vibration Analysis of a Composite Plate with Delamination." Journal of Engineering 21, no. 2 (February 1, 2015): 144–64. http://dx.doi.org/10.31026/j.eng.2015.02.09.

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The use of composite materials has vastly increased in recent years. Great interest is therefore developed in the damage detection of composites using non- destructive test methods. Several approaches have been applied to obtain information about the existence and location of the faults. This paper used the vibration response of a composite plate to detect and localize delamination defect based on the modal analysis. Experiments are conducted to validate the developed model. A two-dimensional finite element model for multi-layered composites with internal delamination is established. FEM program are built for plates under different boundary conditions. Natural frequencies and modal displacements of the intact and damaged multi-layer composite plates are subsequently analyzed for various samples. Also, composite plates are made for vibration testing and analysis and to comparison of the numerical and experimental results, shows good agreement between them.

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Krishna Murty, A. V. "Flexure of composite plates." Composite Structures 7, no. 3 (January 1987): 161–77. http://dx.doi.org/10.1016/0263-8223(87)90027-4.

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Sirajudeen, Rahima Shabeen, and Alagusundaramoorthy P. "GFRP Stiffened Plate with Square Cutout under Axial and Out-of-Plane Load." Polymers 13, no. 8 (April 7, 2021): 1185. http://dx.doi.org/10.3390/polym13081185.

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The high-strength-to-weight ratio and corrosion resistance properties of glass-fiber-reinforced polymer (GFRP) composites makes them potentially well-suited for application in ship structures, bridges and off-shore oil platforms. These structures are often formed by stiffened plates and are subjected to axial load and out-of-plane load. Cutouts and openings are provided in the plates for access and maintenance. The main objective of this study was to examine the buckling behavior of GFRP-stiffened composite plates with square cutouts under a combination of axial and out-of-plane load up to failure. Four blade-stiffened composite plates without a cutout and four with square cutout were fabricated with stiffeners as a continuous layup of the flange plate using glass fiber and epoxy resin. The initial geometric imperfections were measured, and plate imperfections (Δx), stiffener imperfections (Δsy) and overall imperfections (Δsx) were calculated from the measurements. All fabricated-stiffened composite plates were tested up to failure. The finite element model was developed in ANSYS software and validated with the experimental results. It was observed that GFRP-stiffened composite plates failed by stiffener compression/stiffener tension mode of failure. The presence of out-of-plane loads and cutouts reduced the axial load carrying capacity of the stiffened composite plates.

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Dissertations / Theses on the topic "Composite Plates"

1

Жигилій, Дмитро Олексійович, Дмитрий Алексеевич Жигилий, Dmytro Oleksiiovych Zhyhylii, Володимир Андрійович Хворост, Владимир Андреевич Хворост, and Volodymyr Andriiovych Khvorost. "Laminated composite plates." Thesis, Видавництво СумДУ, 2004. http://essuir.sumdu.edu.ua/handle/123456789/22944.

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Jeong, Han Koo. "Reliability of laminated composite plates." Thesis, University of Southampton, 1999. https://eprints.soton.ac.uk/21869/.

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This thesis deals with reliability analysis of laminated composite plates subjected to transverse lateral pressure loads. Input parameters to strengths of the plates such as applied transverse lateral pressure loads, elastic moduli, geometric and ultimate strength values of the plates are treated as basic design variables, and specific probability distributions are applied to them to take into account the variability nature of these basic design variables. Based on the statistical information on the basic design variables, these variables are pseudo-randomly generated in accordance with the corresponding probability distributions by using statistical sampling techniques. Generated random values of the basic design variables corresponding to the applied loads, elastic moduli and geometric values are substituted into various laminated plate theories which can accommodate different lamination schemes and boundary conditions to assess the probabilistic strengths of the plates. The limit state equations are developed by using maximum stress, maximum strain, Tsai-Hill, Tsai-Wu, Hoffman and Azzi-Tsai-Hill failure criteria. Calculated probabilistic plate strengths and generated random values of the ultimate strength basic design variables of the plates are substituted into the developed limit state equations to define the failure or survival state of the plates. In solving the limit state equations, structural reliability techniques are adopted and evolved appropriately for the reliability analysis of the plates. Developed reliability analysing algorithms are applied to laminated plates from experiment to check its validity. Finally, the EUROCOMP Design Code is compared with the developed reliability analysis procedures by applying the both approaches to the strengths of laminated plates.

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Lazarus, Kenneth B. "Induced strain actuation of composite plates." Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/41235.

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Souza, Carlos Eduardo de. "Nonlinear aeroelasticity of composite flat plates." Instituto Tecnológico de Aeronáutica, 2012. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2243.

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This work presents a study on aeroelastic analyses of composite laminated flat plates subject to large displacements through the coupling of a nonlinear corotational shell finite element (FE) with an unsteady vortex-lattice method (UVLM) formulation. A FE implemented for the analysis of flat plates has been extended to model laminated composites with different lamina orientations. An UVLM formulation that is capable of coupling with this large displacement structural model is implemented. An explicit partitioned method is evaluated for the coupling of both models, using spline functions to interpolate information from the structural operator to the aerodynamic one, inside a Generalized-? time-marching solution. The resulting aeroelastic formulation provides a framework able of performing time marching simulation of structures made of composite material allowing the characterization of their nonlinear behavior and of the limit-cycle oscillation response. Laminated flat plates designed for high flexibility and low flutter speed onset are used as investigation models. To support the numerical studies, test specimens made of carbon fiber were used in experimental modal analysis and wind tunnel aeroelastic tests. Effects of nonlinearities are easily observed in the numerical results, which are promising for expansion of the work and application to the analysis of more refined and complex composite flexible wings.

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Simelane, Philemon Sphiwe. "Thermal buckling of laminated composite plates." Thesis, Peninsula Technikon, 1998. http://hdl.handle.net/20.500.11838/1240.

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Thesis (MTech (Mechanical Engineering))--Peninsula Technikon, 1998
However, studies were also conducted for the buckling of composite laminates involving temperature distribution. Chen and Chen (1991) studied thermal buckling of laminated plates under uniform and nonuniform temperature distribution using the eight-node Serendipity finite element. Mathew, Singh and Rao (1992) investigated thermal buckling of antisymmetric cross-ply composite laminates with a onedimensional furite element having two nodes and six degrees of freedom. Chandrashekhara (1992) accounted for transverse shear flexibility by using the thermo-elastic version of the first-order shear deformation theory. This will also be the case in this report. Literature on buckling and laminated composites abounds. Brush and Aimroth (1975) published a book on Buckling of Bars, Plates, and Shells, while Bushnell (1985) surveyed the Methods and Modes of Behaviour in Static Collapse. The foundation for the study of composite materials was based on the references [8], [10], [15] and [18]. The use of the Finite Element Method to analyse the buckling behaviour of laminated structures comes from references [I], [4]. [I2]. [16], [24] and [32]. Reference [14] provided the basis for the formulation of the variation of the governing equations. Most of the ideas in this report are based on these publications and references. Chapter I of this report introduces the concept of a composite. the formation of a composite and a brief overview of the elements of a composite material. This chapter also presents the concept of buckling that will form the basis of the development of this project. At the end of this chapter the choice of the element that is used in this study is justified. Chapter 2 provides the fundamentals of elasticity that relate to the deformation of a loaded body. In this Chapter the stresses and strains are defined and the temperature terms are introduced. In Chapter 3 the Mindlin plate theory is presented with a view to laying the foundation for the analysis of laminated plates, and as a starting point in the formulation of thermal buckling behaviour of laminated plates. In Chapter 4 the elements of a composite material are discussed and the constitutive equations of a laminated composite plate are built. Also the idea of lamination is introduced and the various simplifications that can be introduced as a result of lamination are discussed. The non-linear equilibrium equations and the stability analysis of a composite plate are formulated in Chapter 5 using the conventional anal}1ical method. The resulting equations justify the use of the Finite Element Method as introduced in Chapter 6 and it is the method by which the governing equations will be solved in ABAQUS computer analysis. The results for various computer runs are presented for a normal plate, a plate with a square hole, and the plate ""ith a circular cut-out in Chapter 7. Also in chapter 7 a comparison is made between the laminate "ith a central hole and a normal plate to study the effect of a cut-out on a critical buckling temperature. Appendices A deals the transverse shear in plates, and Appendix B deals with the transformation of the laminate elastic constants form the principal material direction to the general Cartesian co-ordinates. Also in Appendix B the laminate stiffness matrices and these matrices are briefly evaluated analytically. Appendix C is about the governing equations of laminated composites, while Appendix D gives a full representation of the abbreviated finite element equations of Chapter 6. Appendix E presents the list of ABAQUS input files that were used in the computer simulation of Chapter 7.

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Tiwari, Nachiketa. "Secondary Buckling of Laminated Composite Plates." Diss., Virginia Tech, 1999. http://hdl.handle.net/10919/37789.

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The postbuckling load carrying capacity of composite plates offers immense potential to their applications for loads exceeding their primary buckling load. However, such an efficient and economical usage of these plates can be reliable only if the nonlinear postbuckling behavior of these plates, which includes a good understanding of secondary buckling, is understood thoroughly. The present investigation is an attempt to understand secondary buckling of almost square composite clamped-simply supported plates, both unstiffened as well as stiffened, in some detail. With the help of the finite element method, a large number of numerical studies have been conducted to understand the secondary buckling characteristics. The sensitivity of these characteristics to variations in boundary conditions, lamination sequence, imperfections, and stiffener geometry has been considered. It has been found that the occurrence of secondary buckling in clamped-simply supported plates under uniform end shortening critically depends on the intensity of restrictions imposed on the inplane normal displacements along the unloaded simply supported edges of the plate. These restrictions could be due to the actual boundary conditions at these edges, or due to the presence of stiffeners along these edges. It has also been found that the presence of imperfections significantly delays the event of secondary buckling. Finally, it has been found that changes in lamination sequence of the plate alter its secondary buckling characteristics in ways that are, in general, quantitative in nature. The numerical investigations were followed by a limited number of experiments involving the testing of unstiffened as well as stiffened composite plates with the intent of augmenting the confidence in the numerical predictions made. Three different lamination sequences were considered during the testing phase of this investigation. It was found that the agreement between experimental data and numerical predictions was quite good. The occurrence of secondary buckling followed the predictions closely.
Ph. D.

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Moorthy, Jayashree. "Dynamic instability of composite laminated plates." Thesis, Virginia Polytechnic Institute and State University, 1989. http://hdl.handle.net/10919/52090.

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Dynamic instability in a laminated composite plate is studied using the finite element technique. The governing equations are derived based on the first order shear deformation theory with a linear strain-displacement relationship. The regions of instability for the resulting set of coupled Mathieu equations are obtained using a method of simultaneous diagonalization. Boundary frequencies generated using a first subdeterminant approximation to the infinite determinant are compared with those obtained by using the more accurate second subdeterminant as well as with frequencies from an analytical solution. These values are verified by checking the nature of responses near the boundaries between stability and instability. Results are presented for plates with different laminations, boundary conditions, thicknesses, number of layers, etc. Some unstable regions for a damped plate are also shown. Results from the first order plate theory are compared with those from a higher order shear deformation theory.
Master of Science

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8

Olsson, Robin. "Impact response and delamination of composite plates /." Stockholm, 1998. http://www.lib.kth.se/abs98/olss0528.pdf.

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Tippetts, Trevor 1977. "Modeling impact damage in laminated composite plates." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/82782.

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Abdelnaser, Ahmad Shehadeh. "Random vibrations of composite beams and plates." Diss., Virginia Tech, 1992. http://hdl.handle.net/10919/37691.

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The response characteristics of beams and plates made from composite laminates are strongly affected by the shear deformations of their layers. However, incorporation of the shear deformation further complicates the equations of motion and their analysis. As a result the vibration analysis of such structures have been limited to simple free vibration studies such as determination of their frequencies. The forced vibration problems of these structures have been solved by exact methods for only some very simple cases. In this study, a generalized modal approach is presented to solve more general vibration problems of composite beams and plates. The coupled systems of partial differential equations, representing the equations of motion, are uncoupled into modal equations by utilizing the eigenfunctions of the system and its adjoint. A method is presented to obtain these eigenfunctions for beams with arbitrary boundary conditions and for plates with Levy-type boundary conditions. The forced vibration solutions obtained by this method are then used to calculate the random response characteristics of beams and plates subjected to spatially and temporally correlated random loads. In the analysis of beams, both symmetric cross-ply and angle-ply configurations have been considered. In the symmetric cross-ply configuration with no torsional loads, of course, the warping effects are absent. The angle-ply case, however, includes torsion-warping effects and coupled bending-torsion motions. A simple displacement field is introduced to reflect warping in the third-order shear deformation theory. In the analysis of plates also two configurations of the laminates have been considered: symmetric cross-ply and antisymmetric angle-ply. At this time, these are the only two configurations which can be solved by the closed-form modal analysis approach for the Levy-type boundary conditions. In both cases of the beams and plates, the numerical results with and without shear deformations are obtained and compared. The results for no shear deformation are obtained with the classical lamination theory. The results have also been obtained for the first-order shear deformation theory with a somewhat simpler displacement field which has been commonly used in the past by several investigators. The numerical results are obtained for the global response quantities such as frequencies, displacements and crossing rates as well as for the local response quantities such as normal and shear stresses across a cross section. The numerical results obtained with various deformation theories for the frequencies as well as response quantities are compared to evaluate the effect of the shear deformations. For thicker and rigid beams and plates, one observes large differences in the frequencies and responses obtained with (the first- and third-order shear deformation theories) and without consideration of shear deformations (classical theory). For the frequencies and global responses both the first- and third-order theories give about the same results. But for the local response quantities, the results obtained with the two shear deformation theories can also be quite different in some cases. In any case, the results clearly point out the importance of including the shear deformations in thick and rigidly constrained composite beams and plates. Although, in this study only uniform cross section or uniform thickness beams and plates have been considered, it is felt that the eigenfunctions developed herein can also be conveniently utilized with advantage as comparison functions in approximate Rayleigh-Ritz type of approaches to analyze non uniform structures.
Ph. D.

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Books on the topic "Composite Plates"

1

Ye, Jianqiao. Laminated Composite Plates and Shells. London: Springer London, 2003. http://dx.doi.org/10.1007/978-1-4471-0095-9.

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2

J, Turvey G., and Marshall I. H, eds. Buckling and postbuckling of composite plates. London: Chapman & Hall, 1995.

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3

Dong, S. B. Edge vibrations in laminated composite plates. New York: American Society of Mechanical Engineers, 1985.

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4

Turvey, G. J., and I. H. Marshall, eds. Buckling and Postbuckling of Composite Plates. Dordrecht: Springer Netherlands, 1995. http://dx.doi.org/10.1007/978-94-011-1228-4.

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5

Composite panels/plates: Analysis and design. Lancaster, Pa: Technomic Pub. Co., 1986.

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Finn, Scott R. Composite plates impact damage: An atlas. Lancaster, Pa: Technomic Pub. Co., 1991.

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Nettles, A. T. Basic mechanics of laminated composite plates. Washington D.C: National Aeronautics andSpace Administration, 1994.

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S, Springer George, and United States. National Aeronautics and Space Administration., eds. Compression behavior of delaminated composite plates. Stanford, Calif: Department of Aeronautics and Astronautics, Stanford University, 1989.

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Hussein, Raafat M. M. Composite panels/plates: Analysis and design. Lancaster, Pa: Technomic Pub., 1986.

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George C. Marshall Space Flight Center, ed. Basic mechanics of laminated composite plates. MSFC, Ala: Marshall Space Flight Center, National Aeronautics and Space Administration, 1994.

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Book chapters on the topic "Composite Plates"

1

Oñate, Eugenio. "Composite Laminated Plates." In Structural Analysis with the Finite Element Method Linear Statics, 382–437. Dordrecht: Springer Netherlands, 2013. http://dx.doi.org/10.1007/978-1-4020-8743-1_7.

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Gay, Daniel. "Transverse Shear Behavior of Multilayered Plates." In Composite Materials, 387–422. 4th ed. Boca Raton: CRC Press, 2022. http://dx.doi.org/10.1201/9781003195788-21.

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Gay, Daniel. "Mechanical Behavior of Thin Laminated Plates." In Composite Materials, 247–69. 4th ed. Boca Raton: CRC Press, 2022. http://dx.doi.org/10.1201/9781003195788-14.

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Birman, Victor. "Mechanics of Composite Plates." In Plate Structures, 173–223. Dordrecht: Springer Netherlands, 2010. http://dx.doi.org/10.1007/978-94-007-1715-2_5.

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Gdoutos, E. E. "Crack Growth in Duplex Plates." In Composite Structures 3, 596–605. Dordrecht: Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-4952-2_42.

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GangaRao, Hota V. S., and Woraphot Prachasaree. "Analysis of FRP Composite Plates." In FRP Composite Structures, 205–26. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003196754-6.

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Si-Wei, Cai, and Cai Min. "A Refined Theory for Laminated Anisotropic Plates." In Composite Structures, 383–96. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3662-4_30.

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Bhaskar, K., T. K. Varadan, and S. Savithri. "Analysis of Thick Laminated Shells and Plates." In Composite Structures, 354–60. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-662-11345-5_17.

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Altenbach, Holm, Johannes Altenbach, and Wolfgang Kissing. "Differential Operators for Rectangular Plates (Classical Plate Theory)." In Mechanics of Composite Structural Elements, 443–44. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-662-08589-9_14.

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Pyrz, Ryszard. "Qualitative Flutter Analysis of Composite Plates." In Composite Structures 3, 692–702. Dordrecht: Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-4952-2_49.

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Conference papers on the topic "Composite Plates"

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Auad, Samir P., Jamires S. C. Praciano, Elias S. Barroso, João B. M. Sousa Jr., and Evandro Parente Jr. "Isogeometric analysis of fgm plates." In Brazilian Conference on Composite Materials. Pontifícia Universidade Católica do Rio de Janeiro, 2018. http://dx.doi.org/10.21452/bccm4.2018.16.09.

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Sorohan, Stefan, Ioan Parausanu, Adrian Motomancea, and Dumitru I. Caruntu. "Dynamic Analysis of Composite Plates." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-82252.

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The paper presents comparatively the measured and estimated natural frequencies and mode shapes of a rectangular orthotropic panel. The experimental tests were performed using a shaker. The plate was fixed in horizontal position directly on the shaker armature using a rigid rod. The experimental modes shapes were visualized using sand particles. The measured natural frequencies and also the modes shapes correspond to the whole system in motion. So, the analytic model of the plate must include the effect of the vibrator connected to the plates. The purpose of this experimental measurements and analytic modeling of such plates is to further developing a methodology to estimate the material properties of the composite panels. At this research stage, an orthotropic plate with unknown material properties was investigated. Using an adequate finite element model, the mechanical properties of the material were estimated. Using these properties it is possible to numerically estimate the dynamic behavior of the plate for additional sets of boundary conditions.

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Chen, J. K., and J. E. Beraun. "Three-Dimensional Penetration Modelling of Composite Plates." In ASME 1996 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/imece1996-0606.

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Abstract The smoothed particle hydrodynamics (SPH) technique in conjunction with the macro-mechanics approach for fiber composites was developed to predict impact damage of composite structures. For investigating the detailed perforation process and damage progression, 3-D simulations of a graphite/epoxy composite laminate struck by a steel projectile were performed. The predicted damage in the composite target agrees well qualitatively with the experimental results. This study has demonstrated that SPH can be a robust and viable analytical tool for predicting the accurate response of fiber-reinforced composite structures subjected to high-velocity impact.

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Ari-Gur, Judah, and Samuel Simonetta. "Pulse buckling of composite plates." In 35th Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-1435.

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Aygun, A. "SOUND RADIATION FROM COMPOSITE PLATES." In ACOUSTICS 2021. Institute of Acoustics, 2021. http://dx.doi.org/10.25144/13765.

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Jia, Hongyu, and Craig A. Rogers. "The Effect of Toughened Composites on the Static Buckling Load and Buckled Position of Composite Laminated Plates." In ASME 1997 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/imece1997-1038.

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Abstract A nonlinear analysis of the buckling and post-buckling responses of a simply supported laminated composite plate under an axial in-plane compressive load is presented. The model for symmetric cross-ply laminated composite plates made from various composite materials, such as, Graphite/Epoxy, Graphite/PEKK, Graphite/PEEK, and Kevlar/PEKK is given here. The governing equations of post-buckling composite plates with large strains are obtained by using the minimum total potential energy principle. The post-buckling behaviors of Graphite/Epoxy composite plate and toughened composite plates are studied by using this model. The critical buckling load and buckled position are determined. The stress and strain fields of the buckled composite plates are also determined. Buckling analysis is combined with failure analysis by applying Tsai-Hill theory. The effect of the toughened composites (matrix, or fibers or both) on the critical buckling load, post buckling behavior of the laminated composite plates are evaluated.

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Yu, Wenbin, and Lin Liao. "Fully-Coupled Modeling of Composite Piezoelectric Plates." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-80900.

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A fully coupled model considering both sensing and actuation for composite plates with embedded piezoelectrics is constructed using the variational asymptotic method. Without invoking any ad hoc kinematic assumptions, we take advantage of the geometric small parameter inherent in the structure to mathematically split the original three-dimensional, geometrically nonlinear, piezoelectricity problem into: a coupled, linear, one-dimensional piezoelectric through-the-thickness analysis and a coupled, geometrically nonlinear, two-dimensional piezoelectric plate analysis. Two asymptotically correct models of multi-layer plates are developed for two different types of electrode arrangements. The constructed models are of the form of classical plate theory having a layerwise displacement and electric potential distribution. The present theory is implemented using the finite element method into the computer program VAPAS (variational-asymptotic plate and shell analysis). Simple examples are used to demonstrate the application of the present theory.

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Jia, Hongyu, and Craig A. Rogers. "The Effect of Toughened Composites on Dynamic Behaviors of Composite Laminates Under the In-Plane Dynamic Load." In ASME 1997 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/imece1997-1053.

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Abstract In order to investigate the effect of toughened composites on the dynamic behavior of the laminated composite plates under in-plane loading, a simply supported laminated composite plate under the axial in-plane dynamic load is studied. A model for symmetric cross-ply laminated composite plate is presented here. The gorvening equations of motion are obtained by using Lagrange equations. The laminated composite plates are made from various composite materials, such as, Graphite/Epoxy, Graphite/PEKK, Graphite/PEEK, and Kevlar/PEKK. This model considers the large strain, transverse inertia, and neglects the in-plane inertia. The static critical buckling load is determined. The static part and the amplitude of dynamic part of the load are less than the static critical buckling load. Dynamic buckling of the laminated composite plates is studied for dynamic instability regions and primary responses. Linear solution for dynamic instability region is obtained. Also, the linear natural frequencies are determined for different compressive loads and materials. Nonlinear solution for primary responses is also obtained. The effects of the toughened composites on the dynamic buckling responses of the plates are evaluated.

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Dvorak, George J., Jian Zhang, and Olcay Canyurt. "Adhesive Joints for Composite Sandwich Structures." In ASME 2000 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/imece2000-2034.

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Abstract A new approach is explored for joining of thick, woven E-glass/vinyl ester composite laminated plates to steel or composite plates, with applications in naval ship structures. Adhesive is applied along through-the-thickness contoured interfaces, employing tongue-and-groove geometry. Both experimental and finite element modeling results are presented. They show that adhesively bonded tongue-and-groove joints between steel and composite plates loaded in monotonically increasing longitudinal tension, are stronger than conventional strap joints even in relatively thin plates. In particular, a single 0.25 in. wide and 8 or 12 in. long steel tongue, bonded by the Dexter- Hysol 9339 adhesive to a groove in a 0.5 in. thick laminated plate, can support a 20,000 lbs tension force. This force is expected to increase in proportion to plate thickness. Simple design rules indicate that high joint efficiency can be achieved for any thickness of the joined plates.

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Shih, Frank J., Sauvik Banerjee, and Ajit K. Mal. "Impact Damage Monitoring in Composite Plates." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-61868.

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This paper is concerned with the real-time detection of internal damage in composite structural components during impact using the far-field surface motion generated by these events. Impact tests are carried out on graphite epoxy composite plates using an instrumented impact testing system. Contact force and surface motion are measured at several locations on the plate surface. The far-field surface motions, both flexural and extensional waves in the composite plate, are modeled using both approximate and exact solution methods. Postimpact test were performed to determine the extent of internal damage caused by the impact load. Further research on the detection method can lead to the development of a viable impact monitoring system for composite aerospace structures using distributed sensors.

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Reports on the topic "Composite Plates"

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Nayfeh, Adnan H. Interaction of Ultrasonic Waves with Composite Plates. Fort Belvoir, VA: Defense Technical Information Center, December 1987. http://dx.doi.org/10.21236/ada191879.

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Folias, E. S. Failure in Laminated Composite Plates Containing a Hole. Fort Belvoir, VA: Defense Technical Information Center, July 1990. http://dx.doi.org/10.21236/ada227307.

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Trinh, K. V. Modeling the in-plane tension failure of composite plates. Office of Scientific and Technical Information (OSTI), November 1997. http://dx.doi.org/10.2172/563207.

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Reddy, J. N. A Refined Nonlinear Analysis of Laminated Composite Plates and Shells. Fort Belvoir, VA: Defense Technical Information Center, August 1987. http://dx.doi.org/10.21236/ada184436.

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Jha, Ratneshwar. Wavelet Spectral Finite Elements for Wave Propagation in Composite Plates. Fort Belvoir, VA: Defense Technical Information Center, February 2012. http://dx.doi.org/10.21236/ada565193.

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Norgard, John D., Randall Mussellman, Michael C. Wicks, Gerard J. Genello, Douglas E. Lynch, Justin E. Bracken, James M. VanDamme, and Russell D. Brown. Modeling of Composite Scenes Using Wires, Plates and Dielectric Parallelized (WIPL-DP). Fort Belvoir, VA: Defense Technical Information Center, June 2006. http://dx.doi.org/10.21236/ada455065.

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Steinzig, Michael, and Filipe Broetto. Residual Stress measurements in thin composite plates using the hole drilling technique. Office of Scientific and Technical Information (OSTI), August 2014. http://dx.doi.org/10.2172/1159052.

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Colonna, Martino, Lorenzo Crosetta, Alessandro Nanni, Daniel Colombo, and Tommaso Maria Brugo. Carbon composite plates for running shoes: a novel testing method for the measure of flexural stiffness, rebound and damping. Purdue University, 2022. http://dx.doi.org/10.5703/1288284317544.

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Thornell, Travis, Charles Weiss, Sarah Williams, Jennifer Jefcoat, Zackery McClelland, Todd Rushing, and Robert Moser. Magnetorheological composite materials (MRCMs) for instant and adaptable structural control. Engineer Research and Development Center (U.S.), November 2020. http://dx.doi.org/10.21079/11681/38721.

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Magnetic responsive materials can be used in a variety of applications. For structural applications, the ability to create tunable moduli from relatively soft materials with applied electromagnetic stimuli can be advantageous for light-weight protection. This study investigated magnetorheological composite materials involving carbonyl iron particles (CIP) embedded into two different systems. The first material system was a model cementitious system of CIP and kaolinite clay dispersed in mineral oil. The magnetorheological behaviors were investigated by using parallel plates with an attached magnetic accessory to evaluate deformations up to 1 T. The yield stress of these slurries was measured by using rotational and oscillatory experiments and was found to be controllable based on CIP loading and magnetic field strength with yield stresses ranging from 10 to 104 Pa. The second material system utilized a polystyrene-butadiene rubber solvent-cast films with CIP embedded. The flexible matrix can stiffen and become rigid when an external field is applied. For CIP loadings of 8% and 17% vol %, the storage modulus response for each loading stiffened by 22% and 74%, respectively.

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Hoitink, Harry A. J., Yitzhak Hadar, Laurence V. Madden, and Yona Chen. Sustained Suppression of Pythium Diseases: Interactions between Compost Maturity and Nutritional Requirements of Biocontrol Agents. United States Department of Agriculture, June 1993. http://dx.doi.org/10.32747/1993.7568755.bard.

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Several procedures were developed that predict maturity (stability) of composts prepared from municipal solid wastes (MSW). A respirometry procedure, based O2 uptake by compost, predicted (R2=0.90) the growth response of ryegrass in composts and an acceptable level of maturity. Spectroscopic methods (CPMAS13-NMR and DRIFT spectroscopy) showed that the stabilizing compost contained increasing levels of aromatic structures. All procedures predicted acceptable plant growth after approximately 110 days of composting. MSW compost suppressed diseases caused by a broad spectrum of plant pathogens including Rhizoctonia solani, Pythium aphanidermatum and Fusarium oxysporum. A strain of Pantoea agglomerans was identified that caused lysis of hyphae of R. solani. Evidence was obtained, suggesting that thermophilic biocontrol agents also might play a role in suppression. 13C-NMR spectra revealed that the longevity of the suppressive effect against Pythium root rot was determined by the concentration of readily biodegradable carbohydrate in the substrate, mostly present as cellulose. Bacterial species capable of inducing biocontrol were replaced by those not effective as suppression was lost. The rate of uptake of 14C-acetate into microbial biomass in the conducive substrate was not significantly different from that in the suppressive substrate although specific activity was higher. The suppressive composts induced systemic acquired resistance in cucumjber roots to Pythium root rot and to anthracnose in the foliage. Composts also increased peroxidase activity in plants by the conducive substrate did not have these effects. In summary, the composition of the organic fraction determined bacterial species composition and activity in the substrate, which in turn regulated plant gene expression relative to biological control.

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