Relevant bibliographies by topics / Laminated composite and sandwich plates and shell

Academic literature on the topic 'Laminated composite and sandwich plates and shell'

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Published: 14 March 2023

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Journal articles on the topic "Laminated composite and sandwich plates and shell"

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Kumar, Pavan, and CV Srinivasa. "On buckling and free vibration studies of sandwich plates and cylindrical shells: A review." Journal of Thermoplastic Composite Materials 33, no. 5 (November 11, 2018): 673–724. http://dx.doi.org/10.1177/0892705718809810.

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Many review articles were published on free vibration and buckling of laminated composites, sandwich plates, and shells. The present article reviews the literature on the buckling and free vibration analysis of shear deformable isotropic and laminated composite sandwich plates and shells using various methods available for plates in the past few decades. Various theories, finite element modeling, and experimentations have been reported for the analysis of sandwich plates and shells. Few papers on functionally graded material plates, plates with smart skin (electrorheological, magnetorheological, and piezoelectric), and also viscoelastic materials were also reviewed. The scope for future research on sandwich plates and shells was also accessed.
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Dong, S. B., and C. K. Chun. "Shear Constitutive Relations for Laminated Anisotropic Shells and Plates: Part I—Methodology." Journal of Applied Mechanics 59, no. 2 (June 1, 1992): 372–79. http://dx.doi.org/10.1115/1.2899530.

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Shear constitutive relations of a first-order shear deformation theory for laminated anisotropic shells and plates are formulated following Mindlin’s procedure for homogeneous isotropic plates. Because thickness-shear motions for laminated anisotropic thickness profiles may not be polarized in planes normal to the reference surface, the concept of generalized principal shear planes is needed. These planes are established by least-squares minimization of the out-of-plane motions of infinitely long thickness-shear waves based on an elasticity analysis of the profile. Typical shear rigidities for a variety of laminated composite and sandwich profiles are given. In a companion paper, the efficacy of this form of shear constitutive relations in predicting the response of a class of laminated composite and sandwich cylindrical shells is demonstrated.
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Brischetto, Salvatore. "Analysis of natural fibre composites for aerospace structures." Aircraft Engineering and Aerospace Technology 90, no. 9 (November 14, 2018): 1372–84. http://dx.doi.org/10.1108/aeat-06-2017-0152.

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Purpose The main idea is the comparison between composites including natural fibres (such as the linoleum fibres) and typical composites including carbon fibres or glass fibres. The comparison is proposed for different structures (plates, cylinders, cylindrical and spherical shells), lamination sequences (cross-ply laminates and sandwiches with composite skins) and thickness ratios. The purpose of this paper is to understand if linoleum fibres could be useful for some specific aerospace applications. Design/methodology/approach A general exact three-dimensional shell model is used for the static analysis of the proposed structures to obtain displacements and stresses through the thickness. The shell model is based on a layer-wise approach and the differential equations of equilibrium are solved by means of the exponential matrix method. Findings In qualitative terms, composites including linoleum fibres have a mechanical behaviour similar to composites including glass or carbon fibres. In terms of stress and displacement values, composites including linoleum fibres can be used in aerospace applications with limited loads. They are comparable with composites including glass fibres. In general, they are not competitive with respect to composites including carbon fibres. Such conclusions have been verified for different structure geometries, lamination sequences and thickness ratios. Originality/value The proposed general exact 3D shell model allows the analysis of different geometries (plates and shells), materials and laminations in a unified manner using the differential equilibrium equations written in general orthogonal curvilinear coordinates. These equations written for spherical shells degenerate in those for cylinders, cylindrical shell panels and plates by means of opportune considerations about the radii of curvature. The proposed shell model allows an exhaustive comparison between different laminated and sandwich composite structures considering the typical zigzag form of displacements and the correct imposition of compatibility conditions for displacements and equilibrium conditions for transverse stresses.
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Chun, C. K., and S. B. Dong. "Shear Constitutive Relations for Laminated Anisotropic Shells and Plates: Part II—Vibrations of Composite Cylinders." Journal of Applied Mechanics 59, no. 2 (June 1, 1992): 380–89. http://dx.doi.org/10.1115/1.2899531.

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In Part I of this paper, a system of shear constitutive relations was proposed for a first-order shear deformation theory of laminated anisotropic plates and shells. For laminated anisotropic structures, these shear constitutive equations involved the concept of generalized shear planes. Herein, an extensive parametric study is presented to assess the modeling capability of these shear constitutive relations in a class of laminated composite and sandwich cylinders. Classical theory results are also given in order to fully understand the influence of anisotropy on the accuracy and ranges of validity of both first-order shear deformation theory and classical theory. It is seen that the proposed system of shear constitutive relations provides highly accurate frequency results over the range of anisotropy considered.
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Librescu, L., W. Lin, M. DiSciuva, and U. Icardi. "Postbuckling of laminated composite and sandwich plates and shells: On the significance of the fulfillment of static interlayer continuity conditions." Computer Methods in Applied Mechanics and Engineering 148, no. 1-2 (August 1997): 165–86. http://dx.doi.org/10.1016/s0045-7825(97)00020-0.

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Mantari, J. L., A. S. Oktem, and C. Guedes Soares. "Static and dynamic analysis of laminated composite and sandwich plates and shells by using a new higher-order shear deformation theory." Composite Structures 94, no. 1 (December 2011): 37–49. http://dx.doi.org/10.1016/j.compstruct.2011.07.020.

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Sandeep, S. H., and C. V. Srinivasa. "Hybrid Sandwich Panels: A Review." International Journal of Applied Mechanics and Engineering 25, no. 3 (September 1, 2020): 64–85. http://dx.doi.org/10.2478/ijame-2020-0035.

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AbstractA high specific stiffness, high specific strength, and tailoring the properties for specific application have attracted the attention of the researchers to work in the field of laminated composites and Sandwich structures. Rapid use of these laminated composites and Sandwich structures necessitated the development of new theories that suitable for the bending, buckling and vibration analysis. Many articles were published on free vibration of beams, plates, shells laminated composites and sandwich structures. In this article, a review on free vibration analysis of shear deformable isotropic beams, plates, shells, laminated composites and sandwich structures based on various theories and the exact solution is presented. In addition to this, the literature on finite element modeling of beams, plates, shells laminated composites and sandwich structures based on classical and refined theories is also reviewed. The present article is an attempt to review the available literature, made in the past few decades on free flexural vibration response of Fiber Metal laminated Composites and Sandwich panels using different analytical models, numerical techniques, and experimental methods.
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Kim, Chun-Gon, and Eui-Jin Jun. "Impact Resistance of Composite Laminated Sandwich Plates." Journal of Composite Materials 26, no. 15 (December 1992): 2247–61. http://dx.doi.org/10.1177/002199839202601504.

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Muc, Aleksander, Justyna Flis, and Marcin Augustyn. "Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review." Materials 12, no. 24 (December 15, 2019): 4215. http://dx.doi.org/10.3390/ma12244215.

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Aeroelastic optimization has become an indispensable component in the evaluation of divergence and flutter characteristics for plated/shell structures. The present paper intends to review the fundamental trends and dominant approaches in the optimal design of engineering constructions. A special attention is focused on the formulation of objective functions/functional and the definition of physical (material) variables, particularly in view of composite materials understood in the broader sense as not only multilayered laminates but also as sandwich structures, nanocomposites, functionally graded materials, and materials with piezoelectric actuators/sensors. Moreover, various original aspects of optimization problems of composite structures are demonstrated, discussed, and reviewed in depth.
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Anish and Ajay Kumar. "Ultimate Strength Analysis of Laminated Composite Sandwich Plates." Structures 14 (June 2018): 95–110. http://dx.doi.org/10.1016/j.istruc.2018.02.004.

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Dissertations / Theses on the topic "Laminated composite and sandwich plates and shell"

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Nayak, Ajaya Kumar. "On dynamic analysis of laminated composite and sandwich plates using finite element method." Thesis, University of Southampton, 2002. https://eprints.soton.ac.uk/43633/.

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Two new multi-layered plate bending elements (DKT/CST and DKT/LST) are developed based on a combination of the three model Discrete Kirchhoff theory (DKT) triangular plate bending element, the three model constant strain triangle (CST) and the six noded linear strain triangle (LST). Both frequency independent and frequency dependent damping of viscoelastic materials are considered. An iterative complex eigensolver is used to compute the natural frequencies and model loss factors. Several bench mark problems are solved using these new multi-layer plate elements. As the plate bending elements previously developed on the basis of Kirchhoff's theory are inadequate for thick plate analysis, several quadrilateral Mindlin plate bending elements are developed to study the behaviour of Mindlin plates. The plate bending elements based on Mindlin theory require shear correction factors in their formulations. Hence two new Co assumed strain finite element formulations of a refined third order theory which does not require shear correction factors, are developed and used to analyse isotropic, orthotropic, and layered anisotropic composite and sandwich plates under free vibration, damping and transient loading conditions. Parametric effects of plate aspect ratio, length to thickness ratio, degree of orthotropy, number of layers and lamination scheme on the natural frequencies (free vibration), model loss factors (damping) and dynamic (transient) responses have been shown. The results presented in this investigation could be useful in better understanding the behaviour of sandwich laminates under dynamic conditions and potentially beneficial for designers of sandwich structures.
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Monge, J. C., J. L. Mantari, and R. A. Arciniega. "Computational semi-analytical method for the 3D elasticity bending solution of laminated composite and sandwich doubly-curved shells." Elsevier Ltd, 2020. http://hdl.handle.net/10757/656405.

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El texto completo de este trabajo no está disponible en el Repositorio Académico UPC por restricciones de la casa editorial donde ha sido publicado.
In this paper, a three-dimensional numerical solution for the bending study of laminated composite doubly-curved shells is presented. The partial differential equations are solved analytically by the Navier summation for the midsurface variables; this method is only valid for shells with constant curvature where boundary conditions are considered simply supported. The partial differential equations present different coefficients, which depend on the thickness coordinates. A semi-analytical solution and the so-called Differential Quadrature Method are used to calculate an approximated derivative of a certain function by a weighted summation of the function evaluated in a certain grin domain. Each layer is discretized by a grid point distribution such as: Chebyshev-Gauss-Lobatto, Legendre, Ding and Uniform. As part of the formulation, the inter-laminar continuity conditions of displacements and transverse shear stresses between the interfaces of two layers are imposed. The proper traction conditions at the top and bottom of the shell due to applied transverse loadings are also considered. The present results are compared with other 3D solutions available in the literature, classical 2D models, Layer-wise models, etc. Comparison of the results show that the present formulation correctly predicts through-the-thickness distributions for stresses and displacements while maintaining a low computational cost.
Consejo Nacional de Ciencia, Tecnología e Innovación Tecnológica
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Liu, Chorng-Fuh. "Geometrically nonlinear analysis of composite laminates using a refined shear deformation shell theory." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/54453.

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The theory is based on an assumed displacement field, in which the surface displacements are expanded in powers of the thickness coordinate up to the third order. The theory allows parabolic description of the transverse shear stresses, and therefore the shear correction factors of the usual shear deformation theory are not required in the present theory. The theory accounts for small strains but moderately large displacements (i.e., von Karman strains). Exact solutions for certain cross-ply shells and finite-element models of the theory are also developed. The finite-element model is based on independent approximations of the displacements and bending moments (i.e., mixed formulation), and therefore only C°-approximations are required. Further, the mixed variational formulations developed herein suggest that the bending moments can be interpolated using discontinuous approximations (across inter-element boundaries). The finite element is used to analyze cross-ply and angle-ply laminated shells for bending, vibration, and transient response. Numerical results are presented to show the effects of boundary conditions, lamination scheme (i.e., bending-stretching coupling and material anisotropy) shear deformation, and geometric nonlinearity on deflections and frequencies. Many of the numerical results presented here for laminated shells should serve as references for future investigations.
Ph. D.
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Chao, Ting-Mao, and 趙庭懋. "Mechanical Behavior of Laminated Composite Sandwich Plates." Thesis, 1996. http://ndltd.ncl.edu.tw/handle/29336414269156617733.

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Chan, Tung-An, and 詹東恩. "Vibration and Sound Radiation of Laminated Composite Sandwich Plates." Thesis, 2003. http://ndltd.ncl.edu.tw/handle/24918386418951555711.

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碩士
國立交通大學
機械工程系
91
In this thesis, vibration characteristics of laminated composite sandwich plates are studied via experimental and theoretical approaches. Sound pressure responses of laminated composite sandwich plates with different vibration characteristics are also studied experimentally and theoretically. In the theoretical study, the vibration analysis of laminated composite sandwich plates is achieved via the use of the Rayliegh-Ritz Method. In sound pressure analysis, the modal and harmonic analyses of laminated plates are performed using the finite element code ANSYS. The amplitude and phase angle obtained from the harmonic analysis together with sound pressure equation are used to construct the sound pressure level (SPL) curves. The SPL curves change for different sizes of laminated composite sandwich plates in the sound pressure analysis. In the experiment approach, above all, the measured natural frequencies of laminated composite sandwich plates are used to verify the theoretical results. Furthermore, sound pressure responses of different sandwich plates are measured and used to verify the theoretical results. The comparison between the experimental and theoretical results shows that the present method can produce satisfactory results for both natural frequencies and SPL curves.
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Yang, Tz-Ya, and 楊慈雅. "Impact Analysis and Experiment of Laminated Composite Sandwich Plates." Thesis, 1997. http://ndltd.ncl.edu.tw/handle/38715647982356876130.

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碩士
國立交通大學
機械工程研究所
85
A finite element method, which is formulated on the basis of the layerwise linear displacement theory, is used to study the mechanical behavior of laminated composite sandwich plates subjected to impact. Two types of finite elements, namely, three-node isoparametric triangular finite element and nine-node plate element, in conjunciton with an empirical contact law derived from the statical indentation test of laminated composite sandwich plates are used for the theoretical investigation. The impace problem is solved via the use of Newmark''s integration scheme and Newton-Raphson method. The proposed method is then used to evaluate the contact force and strains of the plates during impact. A number of examples of laminated composite sandwich plates with different length-to-thickness ratios, fiber angles and number of layer groups striked by an impactor with different velocities are studied. Results obtained via various theories are compared with experimental results. The suitability and accuracy of the proposed method are illustrated by means of the examples.
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CHEN, WEN-JI, and 陳文吉. "Analysis of laminated composite plates and shell panels:vibration, buckling, and thermal buckling." Thesis, 1992. http://ndltd.ncl.edu.tw/handle/43436673787665819682.

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Veenaranjini, S. M. "Low-Order Laminated Lock-Free Beam And Plate Elements Based On Coupled Displacement Field." Thesis, 2004. http://hdl.handle.net/2005/313.

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This study aims to investigate the behaviour of low-order beam and plate elements especially for their application to laminated structures. The merits and dements of the existing elements are brought out and new low-order elements with better interpolation polynomials are proposed. Two new beam elements are proposed for laminated composite beams that yield better representation of twist due to material coupling. Out of the two elements developed, one is based on the conventional formulation and the other on the coupled-field formulation, both capturing material induced coupling. The beam developed using coupled field formulation shows a novel way of obtaining a fully coupled interpolation function for field variables using the complete set of equilibrium equations for the composite beams. The element has shown a superior coarse mesh performance. These elements can practically capture plate behaviour in beam elements for a wide range of plate thickness. The locking problems in conventional 4-node quadrilateral elements, such as shear locking and geometric locking are studied. Various techniques available in literature to remedy these problems are also studied. A suite of QUAD4 with conventional techniques such as. Reduced Integration, Field Consistency, Mixed Interpolation of Tensorial strain Components, Assumed Natural Strain, Discrete Shear Gap, Incompatible modes Q6 and QM6 is developed. An effort is made to combine these techniques to develop new element that yields improved performance. The element is shown to exhibit improved performance for certain cases. Several four-node rectangular elements are developed based on the coupled-field techniques. First two new-coupled elements are formulated that employ Sabir's [101] plane bending formulation with drilling degree of freedom, and the plate bending rotations are generated using equilibrium equations. However, since Sabir's plane bending interpolation polynomials yielded inaccurate performance for composites, it led to development of elements with fully coupled field formulations. Finally, two new 4-node rectangular elements are developed using coupled-field formulations with six and seven dof freedom per node respectively. Here the interpolation polynomials are derived using the complete equilibrium equations. The elements are extensively tested for static deflection, dynamics and buckling of isotropic and laminated plates/beams. The elements show superior coarse mesh convergence. Several problems pertaining to vibration and buckling of composite plates/beams are solved using the elements developed in this work.
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Books on the topic "Laminated composite and sandwich plates and shell"

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F, Lung S., Gupta K. K, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. A three-node C ̊element for analysis of laminated composite sandwich shells. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

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F, Lung S., Gupta K. K, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. A three-node C ̊element for analysis of laminated composite sandwich shells. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

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Yu, Yi-Yuan. Vibrations of Elastic Plates: Linear and Nonlinear Dynamical Modeling of Sandwiches, Laminated Composites, and Piezoelectric Layers. New York, NY: Springer New York, 1996.

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Vibrations of elastic plates: Linear and nonlinear dynamical modeling of sandwiches, laminated composites, and piezoelectric layers. New York: Springer, 1996.

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Vibrations of Elastic Plates: Linear and Nonlinear Dynamical Modeling of Sandwiches, Laminated Composites, and Piezoelectric Layers. Springer, 2011.

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Book chapters on the topic "Laminated composite and sandwich plates and shell"

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Kulikov, Gennady M., and Svetlana V. Plotnikova. "Three-Dimensional Exact Analysis of Functionally Graded Laminated Composite Plates." In Shell and Membrane Theories in Mechanics and Biology, 223–41. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-02535-3_13.

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"Part 13: Plates, shells, laminated composite structures, sandwich structures." In Research and Applications in Structural Engineering, Mechanics and Computation, 349–50. CRC Press, 2013. http://dx.doi.org/10.1201/b15963-162.

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"Plates, shells, pipes, laminated composites, sandwich structures." In Advances and Trends in Structural Engineering, Mechanics and Computation. CRC Press, 2010. http://dx.doi.org/10.1201/b10557-8.

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"A new trigonometric shear deformation theory for sandwich and composite laminated plates." In Maritime Engineering and Technology, 331–36. CRC Press, 2012. http://dx.doi.org/10.1201/b12726-48.

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Conference papers on the topic "Laminated composite and sandwich plates and shell"

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Katariya, Pankaj, and Subrata Kumar Panda. "Simulation Study of Transient Responses of Laminated Composite Sandwich Plate." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4846.

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In this article, the transient responses of the laminated composite sandwich plate structure are obtained numerically using the commercial finite element package to reduce the computational cost without hampering the accuracy. The plate structure is discretized using the available shell element (SHELL281) from ANSYS library. In order to compute the responses, an ANSYS parametric design language code has been developed based on the finite element steps and Newmark integration technique. The model accuracy and stability have been checked and few numerical examples have been solved. Finally, the effect of different parameters like side-to-thickness ratios, core-to-face thickness ratios, and lamination schemes are computed to show the necessary influences on the time-dependent deflection of the laminated composite sandwich structure.
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Librescu, Liviu. "Implication of Anisotropy of Face-Sheets and Core Layer Materials on the Load Carrying Capacity of Advanced Sandwich Panels: Linear and Nonlinear Responses." In ASME 2000 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/imece2000-2039.

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Abstract This paper deals with a comprehensive geometrically nonlinear theory of shallow sandwich shells that includes also the effect of the initial geometric imperfections. It is assumed that the face-sheets of the sandwich structure are built-up from anisotropic materials layers, whereas the core layer from an orthotropic material. As a result of its features the structural model can provide important information related to the load carrying capacity of sandwich structures in the pre- and postbuckling ranges. Moreover, by using the directionality properties of face-sheets materials, possibilities of enhancing the load carrying capacity of sandwich shells/plates are reached. Selected numerical illustrations emphasizing these features are presented and pertinent conclusions on the beneficial implications of anisotropy of face-sheets and core layer materials upon the load-carrying capacity of sandwich panels are emphasized. Under the present study, the sandwich structure consists of a thick core-layer bonded by the face-sheets that consist of composite anisotropic materials, symmetrically laminated with respect to the mid-surface of the core-layer. The initial geometric imperfection consisting of a stress free initial transversal deflection, will be also incorporated in the study. The loads under which the nonlinear response will be analyzed consist basically of uniaxial/biaxial compressive edge and lateral loads.
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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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Wang, C. M., K. K. Ang, and C. Wang. "Vibration of Skew Sandwich Plates With Laminated Facings." In ASME 1997 Turbo Asia Conference. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-aa-050.

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A Rayleigh-Ritz analysis is presented for the free vibration of skew sandwich plates composed of an orthotropic core and laminated facings. By proposing a set of Ritz functions consisting of the product of mathematically complete polynomial functions and the the boundary equations raised to appropriate powers, the Rayleigh-Ritz method can be automated to handle such composite plates with any combination of edge conditions. For convenience and better accurarcy, the Ritz formulation was derived in the skew coordinate system. Vibration frequencies of rectangular plates (a special case of skew plates) obtained via this method have been found to be in good agreement with previous researchers results. Owing to length limitation, only sample vibration frequencies for skew sandwich plates are presented.
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Albernaz, Jessica. "Bending Analysis of Laminated Composite Sandwich Plates Reinforced with Carbon Nanotube Forests." In 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-200.

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Kallannavar, Vinayak, and Subhaschandra Kattimani. "Modal analysis of laminated composite and sandwich plates using finite element method." In ADVANCES IN MECHANICAL DESIGN, MATERIALS AND MANUFACTURE: Proceeding of the Second International Conference on Design, Materials and Manufacture (ICDEM 2019). AIP Publishing, 2020. http://dx.doi.org/10.1063/5.0004159.

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YU, YI-YUAN. "Dynamics and vibration of layered plates and shells - A perspective from sandwiches to laminated composites." In 30th Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-1419.

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Barut, Atila, Erdogan Madenci, and Alexander Tessler. "A Refined Zigzag Theory for Laminated Composite and Sandwich Plates Incorporating Thickness Stretch Deformation." In 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
20th AIAA/ASME/AHS Adaptive Structures Conference
14th AIAA. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-1705.

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Diveyev, Bohdan M., Ihor B. Butyter, and Natalie N. Shcherbyna. "High Order Theories for Elastic Modules Identification of Composite Plates." In ASME 2008 9th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2008. http://dx.doi.org/10.1115/esda2008-59278.

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The study aims to predict elastic and damping properties of composite laminated plates from the measured dynamical properties. Elastic constants of laminates and damping properties have been determined by using an identification procedure based on experiment design, and multi-level theoretical approach. The present paper is the first attempt at proposing a novel adaptive procedure to derive stiffness parameters from forced sandwich plate’s vibration experiments.
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Carminelli, Antonio, and Giuseppe Catania. "B-Spline Finite Element Formulation for Laminated Composite Shells." In ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-67420.

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This paper presents a finite element formulation for the dynamical analysis of general double curvature laminated composite shell components, commonly used in many engineering applications. The Equivalent Single Layer theory (ESL) was successfully used to predict the dynamical response of composite laminate plates and shells. It is well known that the classic shell theory may not be effective to predict the deformational behavior with sufficient accuracy when dealing with composite shells. The effect of transverse shear deformation should be taken into account. In this paper a first order shear deformation ESL laminated shell model, adopting B-spline functions as approximation functions, is proposed and discussed. The geometry of the shell is described by means of the tensor product of B-spline functions. The displacement field is described by means of tensor product of B-spline shape functions with a different order and number of degrees of freedom with respect to the same formulation used in geometry description, resulting in a non-isoparametric formulation. A solution refinement method, making it possible to increase the order of the displacement shape functions without using the well known B-spline “degree elevation” algorithm, is also proposed. The locking effect was reduced by employing a low-order integration technique. To test the performance of the approach, the static solution of a single curvature shell and the eigensolutions of composite plates were obtained by numerical simulation and are then compared with known solutions. Discussion follows.
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