Relevant bibliographies by topics / Laminated and sandwich composite

Academic literature on the topic 'Laminated and sandwich composite'

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Published: 14 March 2023

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Journal articles on the topic "Laminated and sandwich composite"

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Sebaey, TA, and Ahmed Wagih. "Flexural properties of notched carbon–aramid hybrid composite laminates." Journal of Composite Materials 53, no. 28-30 (June 11, 2019): 4137–48. http://dx.doi.org/10.1177/0021998319855773.

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Hybrid composite laminates are currently receiving researchers’ attention due to their specific advantages in designing laminates with improved specific strength and stiffness. One of the main disadvantages of polymeric laminated composites is their high sensitivity to notches, which cannot be avoided in design. This paper presents a comparison between two common hybridization techniques, namely sandwich and intra-ply hybridization. The study adopts experimental observations to investigate the influence of hybridization method on the flexural properties of notched carbon–aramid hybrid laminates. After four-point bending tests, the results show that the damage nature in both laminates is different. A catastrophic damage is observed for intra-ply hybrid laminates, while sandwich laminates show progressive damage. In terms of the strength, sandwich specimens show 1.3 times higher specific strength, compared to intra-ply specimens. Moreover, the bottom layers of the laminate manufactured in the sandwich fashion show minimal damage due to the high capability of the aramid/epoxy core to absorb the energy in deformation and concentrate the damage at the top layers (the compression side).
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Çınar, Okan, Merve Erdal, and Altan Kayran. "Accurate equivalent models of sandwich laminates with honeycomb core and composite face sheets via optimization involving modal behavior." Journal of Sandwich Structures & Materials 19, no. 2 (August 3, 2016): 139–66. http://dx.doi.org/10.1177/1099636215613934.

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An approach is introduced for determining accurate two-dimensional equivalent laminated models of sandwich laminates with honeycomb core and composite facesheets by optimization involving modal behavior. The approach relies on minimizing the objective function which is defined as the sum of the square of the differences between the natural frequencies of the honeycomb sandwich laminate estimated by the finite element analysis of the 3D detailed model with the actual honeycomb core geometry and by the 2D equivalent laminated model with the honeycomb core replaced by the equivalent 2D orthotropic material model. Equivalent elastic constants of the 2D orthotropic model of the honeycomb core are defined as the design variables of the optimization problem, and a finite element solver and genetic algorithm-based optimizer are coupled to perform the optimization task. Results show that with the optimization-based approach, very accurate 2D equivalent models of honeycomb sandwich laminates are obtained compared to equivalent models obtained by replacing the honeycomb core with elastic constants of the 2D orthotropic material model obtained utilizing analytical models available in the literature.
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Lu, Ping, Xu Dong Liu, Xue Qiang Ma, and Wei Bo Huang. "Analysis of Damping Characteristics for Sandwich Beams with a Polyurea Viscoelastic Layer." Advanced Materials Research 374-377 (October 2011): 764–69. http://dx.doi.org/10.4028/www.scientific.net/amr.374-377.764.

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Constrained layer damping treatments such as sandwich beams are considered as the most efficient way of introducing vibration damping into a structure. The dynamic mechanical properties and damping behavior of a laminated sandwich composite beam inserted with a viscoelastic layer is investigated. A quantitative analysis of damping in the sandwich laminated composite beam has been conducted through the theoretical and experimental method. Traditional epoxy and new kind of polyurea viscoelastic layer are selected to analyze the damping properties. Results showed that the polyurea viscoelastic layer had good dumping capability. The effects of temperature, frequency of viscoelastic layer on vibration damping characteristics arc also discussed. They also demonstrate the great capability of laminated sandwich composites with embedded viscoelastic layer to considerably enhance structural damping.
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Zhu, Xiujie, Chao Xiong, Junhui Yin, Dejun Yin, and Huiyong Deng. "Bending Experiment and Mechanical Properties Analysis of Composite Sandwich Laminated Box Beams." Materials 12, no. 18 (September 12, 2019): 2959. http://dx.doi.org/10.3390/ma12182959.

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The failure modes, ultimate load, stiffness performance, and their influencing factors of a composite sandwich laminated box beam under three-point bending load are studied by an experiment, finite element model, and analytical method. The three-point bending experiment was carried out on three different core composite sandwich laminated box beams, and the failure modes and bearing capacity were studied. With the use of composite progressive damage analysis and the core elastoplastic constitutive model, the finite element model of the composite sandwich laminated box beam was established, and the three-point bending failure process and failure modes were analyzed. The analytical model was established based on the Timoshenko beam theory. The overall bending stiffness and shear stiffness of the composite sandwich laminated box beam were calculated by the internal force–displacement relationship. The results show that the composite sandwich laminated box beam mainly suffers from local crushing failure, and the errors between the finite element simulation and the experiment result were within 7%. The analytical model of the composite sandwich laminated box beam can approximately predict the overall stiffness parameters, while the maximum error between theoretic results and experimental values was 5.2%. For composite aluminum honeycomb sandwich laminated box beams with a ratio of span to height less than 10, the additional deflection caused by shear deformation has an error of more than 25%. With the ratio of circumferential layers to longitudinal layers increasing, the three-point bending ultimate load of the composite sandwich laminated box beam increases, but the ratio of the overall stiffness to mass reduces. The use of low-density aluminum foam and smaller-wall-thickness cell aluminum honeycombs allows for the more obvious benefits of light weight.
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Hami, B., A. Irekti, C. Aribi, B. Bezzazi, and A. Mir. "Experimental Study of Sandwich Multilayer Reinforced by Glass Fibre and Agglomerated Cork." Advanced Composites Letters 23, no. 5 (September 2014): 096369351402300. http://dx.doi.org/10.1177/096369351402300503.

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This paper presents an experimental study which is determined the mechanical properties of a composite material sandwich multilayer developed in the laboratory of mechanics of materials and composites, Materials Research Unit, process and environment. This type of sandwich is composed of four layers laminated based on an epoxy resin reinforced by woven glass fibres and mast between which three plates of agglomerated cork with stacked alternately laminated layers. Specimens for bending tests three and four points were prepared from the multilayer sandwich panels. A first series of static three-point bending tests shows a clear difference in the fracture behaviour for materials, laminate and cork. These materials have undergone a large plastic deformation without rupture achieve full sandwich, with the onset of delamination between layers laminated material and cork. In order to determine the bending stiffness modules D, the shear modulus and flexural N and the shear modulus of the soul Ga, we conducted a second test campaign four points bending. As a result, we can develop a variety of white cork produced in Algeria in order to use it in the construction and automotive industries.
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Cui, Xiao Dong, Tao Zeng, and Dai Ning Fang. "Study on Ballistic Energy Absorption of Laminated and Sandwich Composites." Key Engineering Materials 306-308 (March 2006): 739–44. http://dx.doi.org/10.4028/www.scientific.net/kem.306-308.739.

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The impact response and energy absorbing characteristics of laminated, foam sandwich and honeycomb sandwich composites under ballistic impact have been studied in this investigation. An improved model is proposed in this paper to predict the ballistic property of the laminated composites. In this model, the material structures related to fiber lamination angles are designed in terms of their anti-impacting energy absorption capability. The ballistic limit speed and energy absorption per unit thickness of the three composites under different conditions are calculated. It is shown that honeycomb sandwich composite has the best ballistic resistance capability and energy absorption property among the three composites.
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Bir, Amarpreet S., Hsin Piao Chen, and Hsun Hu Chen. "Optimum Stacking Sequence Design of Composite Sandwich Panel Using Genetic Algorithms." Advanced Materials Research 585 (November 2012): 29–33. http://dx.doi.org/10.4028/www.scientific.net/amr.585.29.

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In the present study, both critical buckling load maximization and face-sheet laminate thickness minimization problems for the composite sandwich panel, subjected to bi-axial compressive loading under various imposed constraints have been investigated using genetic algorithms. In the previously published work, the optimization of simple composite laminate panels with only even number of laminae has been considered [1, 3]. The present work allows the optimization of a composite sandwich panel with both even and odd number of laminae in the face-sheet laminates. Also, the effects of the bending-twisting coupling terms (D16and D26) in bending stiffness matrix which were neglected in the previous studies [1, 2, 3], are considered in the present work for exact solutions. In addition effect of both balanced and unbalanced face-sheet laminates on the optimum solutions have also been investigated, whereas only balanced laminates were considered in the previous studies [1, 2, 3].
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Vemuluri, Ramesh Babu, Vasudevan Rajamohan, and Ananda Babu Arumugam. "Dynamic characterization of tapered laminated composite sandwich plates partially treated with magnetorheological elastomer." Journal of Sandwich Structures & Materials 20, no. 3 (June 3, 2016): 308–50. http://dx.doi.org/10.1177/1099636216652573.

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This study investigates the dynamic performance of the partially treated magnetorheological elastomer tapered composite sandwich plates. Various partially treated tapered magnetorheological elastomer laminated composite sandwich plate models are formulated by dropping-off the plies longitudinally in top and bottom composite face layers to yield tapered plates as the face layers. The uniform rubber and magnetorheological elastomer materials are considered as the core layer. The governing differential equations of motion of the various partially treated magnetorheological elastomer tapered composite sandwich plate configurations are derived using classical laminated plate theory and solved numerically. Further, silicon-based magnetorheological elastomer and natural rubber are being fabricated and tested to identify the various mechanical properties. The effectiveness of the developed finite element formulation is demonstrated by comparing the results obtained with experimental tests and available literature. Also, various partially treated magnetorheological elastomer tapered laminated composite sandwich plates are considered to the study the effect of location and size of magnetorheological elastomer segment on various dynamic properties under various boundary conditions. The effects of magnetic field on the variation of natural frequencies and loss factors of the various partially treated magnetorheological elastomer tapered laminated composite sandwich plate configurations are analysed at different boundary conditions. Also, the effect of taper angle of top and bottom layers, aspect ratio, ply orientations on the natural frequencies of different configurations are analysed. Further, the transverse vibration responses of three different partially treated magnetorheological elastomer tapered laminated composite sandwich plate configurations under harmonic excitation are analysed at various magnetic fields. This analysis suggests that the location and size of the magnetorheological elastomer segments strongly influence the natural frequency, loss factor and transverse displacements of the partially treated magnetorheological elastomer tapered laminated composite sandwich plates apart from the intensities of the applied magnetic field. This shows the applicability of partial treatment to critical components of a large structure to achieve a more efficient and compact vibration control mechanism with variable damping.
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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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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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Dissertations / Theses on the topic "Laminated and sandwich composite"

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Zhao, Huyue. "Stress Analysis of Tapered Sandwich Panels with Isotropic or Laminated Composite Facings." Fogler Library, University of Maine, 2002. http://www.library.umaine.edu/theses/pdf/ZhaoH2002.pdf.

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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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Kilic, Yavuz S. M. Massachusetts Institute of Technology. "Impact and energy absorption of laminated and sandwich composites." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/44883.

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Thesis (S.M. in Naval Architecture and Marine Engineering)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2008.
Includes bibliographical references (p. 115-131).
Advanced fiber reinforced composites combine high specific strength and stiffness. Advanced composites are currently being introduced into modern U.S. Navy ships to achieve weight savings, maintenance reduction, and signature reduction. These advancements manifest themselves in Naval ships as increases in survivability, payload, range, speed, and weapon systems performance. In this thesis, vinyl ester resin matrix laminates and sandwich composites are emphasized since they are increasingly being used in naval applications. Impact damage of laminated and sandwich composites under low-velocity and high-velocity impact are investigated. Delamination damage is explored in detail since delamination is one of the major failure modes of many advanced composites structures. Delamination initiation loads for various laminates having different stacking sequences are compared. In many laminates containing various stacking sequences, placing the 900 laminae on the outside (as opposed to the inside) will reduce the delamination initiation load under impact. Moreover, an open literature survey of numerous laminated and sandwich composites having different stacking sequences and thicknesses and subjected to low-velocity impact is undertaken. The failure mode, failure load, and displacement at failure of these composites are summarized. Other topics investigated include (1) effects of a composite's constituents on damage susceptibility, (2) post-impact residual characterization and strength, and (3) nondestructive testing techniques. Prediction methods for residual strength are tabulated based on the impact damage type for laminated and sandwich composites. Further, NASA and Boeing compression-after-impact tests are summarized for laminated composites after low-energy impacts.
(cont.) Damage and residual strength are analyzed for epoxy and PEEK resin laminates. An initial sorting for the selection of nondestructive testing methods for specific composite discontinuities is summarized. Extensive presentations of tables and figures are used to summarize the results of the literature surveys on impact resistance and energy absorbing capabilities of composites. Particular attention is given to methods for impact resistance improvement. Impact resistance improvement methods are compared according to increases in interlaminar Mode I and Mode II fracture toughness and in residual strength. These comparisons support data for the selection of impact resistance improvement. Numerous laminates having different lamina orientations are compared to understand the influence of stacking sequence on impact damage resistance and energy absorption capability. Matrix properties are investigated for many laminates and it is noted that higher interlaminar fracture toughness of matrix materials will increase energy absorption capability. The effects of other constituents of a laminate on impact resistance and energy absorbing capability are also summarized. Among the types of composites investigated in this thesis, carbon fiber/PEEK laminates exhibited the highest specific energy absorption. Recommendations for further studies are offered based on these summaries.
by Yavuz Kilic.
S.M.in Naval Architecture and Marine Engineering
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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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Ghoor, Ismail B. "The response of concave singly curved fibre reinforced moulded sandwich and laminated composite panels to blast loading." Master's thesis, University of Cape Town, 2018. http://hdl.handle.net/11427/27811.

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Composite materials are increasingly being used in a wide range of structural applications. These applications range from bicycle frames and building facades to hulls of marine ships. Their popularity is due to the high specific strength and stiffness properties, corrosion resistance, and the ability to tailor their properties to a required application. With the increasing use of composites, there is a need to better understand the material and damage behaviour of these structures. In recent years, the increased frequency of wars and terror attacks have prompted investigations into composite failure processes resulting from air-blast. Most of the research has been focused on flat panels, whereas there is relatively little on curved structures. This dissertation reports on the effect of air-blast loading on concave, singly curved fibre reinforced sandwich and composite panels. Sandwich panels and equivalent mass glass fibre laminates were manufactured and tested. Three types of curvature namely a flat panel (with infinite curvature), a curvature of 1000 mm radius and a curvature of 500 mm radius were produced, to determine the influence of curvature on panel response. The laminates were made from 16 layers of 400 g/m² plain weave glass fibre infused with Prime 20 LV epoxy resin. The sandwich panels consisted of a 15 mm thick Airex C70:75 core sandwiched between the 12 layers of 400 g/m² plain weave glass fibre and infused with Prime 20 LV epoxy resin. This arrangement produced a balanced sandwich panel with 6 layers of glass fibre on the front and back respectively. For all panels, vacuum infusion was used to manufacture in a single shot process. Mechanical properties of samples were tested for consistency in manufacturing. It was found that mechanical properties of the samples tested were consistent with low standard deviations on tensile and flexural strength. The panels were tested in the blast chamber flat the University of Cape Town. Blast specimens were clamped onto a pendulum to facilitate impulse measurement. Discs of plastic explosive, with charge masses ranging from 10 g to 25 g, were detonated. After blast testing, a post-mortem analysis of the damaged panels was conducted. Post-mortem analysis revealed that the failure progression was the same irrespective of curvature for both the sandwich panels and the laminates. Sandwich panels exhibited the following failure progression: delamination, matrix failure, core crushing, core shear, core fragmentation, core penetration and fibre fracture. The laminates displayed the following progression: delamination, matrix failure and fibre fracture. Curved panels exhibited failure initiation at lower charge masses than the flat panels. As the curvature increased, the failure modes initiated at lower charge masses. For example, as the charge mass was increased to 12.5 g the front face sheets of the flat and the 1000 mm radius sandwich panels exhibited fibre fracture, but the 500 mm radius sandwich panel exhibited fibre fracture and rupture through the thickness of the front face sheet. The 500 mm radius laminate exhibited front face failure earlier (15 g) than the 1000 mm radius (22.5 g) and flat panel (20 g). Curved laminates exhibited a favoured delamination pattern along the curved edges of the panel for both 1000 mm and 500 mm radii laminates. As the curvature increased, more delamination was evident on the curved edges. The curved panels displayed more severe damage than flat panels at identical charge masses. Curved sandwich panels experienced through thickness rupture at 20 g charge mass whereas the curved laminates did not exhibit rupture at 25 g charge mass. The flat laminates were the most blast resistant, showing no through-thickness penetration at 25 g (the highest charge mass tested) and initiated failure modes at higher charge masses when compared to the other configurations.
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Ghinet, Sebastian. "Statistical energy analysis of the transmission loss of sandwich and laminate composite structures." Thèse, Université de Sherbrooke, 2005. http://savoirs.usherbrooke.ca/handle/11143/1770.

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The present study emerges from a present industry need for accurate and fast numerical modeling approaches to estimate the vibro-acoustic behaviours of multilayered composite and viscoelastic treatments configurations.The structure is modeled using a wave approach applied to various multilayer configurations such as: symmetrical laminate composite, symmetrical sandwich composite and general symmetrical or unsymmetrical laminate or sandwich composite as well as viscoelastic treatments. Three behavioural modeling approaches are investigated: smeared laminate, discrete layer sandwich and general discrete layer laminate. Smeared laminate approach is devoted to symmetrical laminate composite panels and uses equivalent elastic properties computed by smearing out the layers' properties through the panel's thickness. Discrete layer sandwich approach is devoted to symmetrical sandwich composite panels and uses individual displacement fields for each layer. Classical assumptions of thick skins sandwich panels are adopted. General discrete laminate approach accommodates both laminate and sandwich composite panels of symmetrical or unsymmetrical layout. Individual displacement fields are used for each layer. These three behavioural modeling approaches are applied in the present work to flat and curved panel configurations as well as laminated beams. Dispersion relations are developed for each configuration and solved in a generalized polynomial eigenvalue problem context. These solutions are used in a SEA framework to compute the group velocity, the modal density, the radiation efficiency as well as the resonant and non-resonant contributions to the transmission coefficient. Moreover, the dispersion relations are used to develop general expressions to compute the ring frequency and the critical frequencies. In the context of viscoelastic treatments modeling the mechanical impedance, the input mobility, the deformation energy as well as the equivalent loss factor are computed for several boundary conditions.The presented approaches are successfully validated with experimental results and previously published theories. In addition to their proven accuracy, the proposed approaches are quick and general.
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Shah, Priyal. "Computational Analysis of Elastic Moduli of Covalently Functionalized Carbon Nanomaterials, Infinitesimal Elastostatic Deformations of Doubly Curved Laminated Shells, and Curing of Laminates." Diss., Virginia Tech, 2017. http://hdl.handle.net/10919/77034.

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We numerically analyze three mechanics problems described below. For each problem, the developed computational model is verified by comparing computed results for example problems with those available in the literature. Effective utilization of single wall carbon nanotubes (SWCNTs) and single layer graphene sheets (SLGSs) as reinforcements in nanocomposites requires their strong binding with the surrounding matrix. An effective technique to enhance this binding is to functionalize SWCNTs and SLGSs by covalent attachment of appropriate chemical groups. However, this damages their pristine structures that may degrade their mechanical properties. Here, we delineate using molecular mechanics simulations effects of covalent functionalization on elastic moduli of these nanomaterials. It is found that Young's modulus and the shear modulus of an SWCNT (SLGS), respectively, decrease by about 34% (73%) and 43% (42%) when 20% (10%) of carbon atoms are functionalized for each of the four functional groups of different polarities studied. A shell theory that gives results close to the solution of the corresponding 3-dimensional problem depends upon the shell geometry, applied loads, and initial and boundary conditions. Here, by using a third order shear and normal deformable theory and the finite element method (FEM), we delineate for a doubly curved shell deformed statically with general tractions and subjected to different boundary conditions effects of geometric parameters on in-plane and transverse stretching and bending deformations. These results should help designers decide when to consider effects of these deformation modes for doubly curved shells. Composite laminates are usually fabricated by curing resin pre-impregnated fiber layers in an autoclave under prescribed temperature and pressure cycles. A challenge is to reduce residual stresses developed during this process and simultaneously minimize the cure cycle time. Here, we use the FEM and a genetic algorithm to find the optimal cycle parameters. It is found that in comparison to the manufacturer's recommended cycle, for a laminate with the span/thickness of 12.5, one optimal cycle reduces residual stresses by 47% and the total cure time from 5 to 4 hours, and another reduces the total cure time to 2 hours and residual stresses by 8%.
Ph. D.
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Alanbay, Berkan. "Free Vibrations and Static Deformations of Composite Laminates and Sandwich Plates using Ritz Method." Diss., Virginia Tech, 2020. http://hdl.handle.net/10919/103087.

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In this study, Ritz method has been employed to analyze the following problems: free vibrations of plates with curvilinear stiffeners, the lowest 100 frequencies of thick isotropic plates, free vibrations of thick quadrilateral laminates and free vibrations and static deformations of rectangular laminates, and sandwich structures. Admissible functions in the Ritz method are chosen as a product of the classical Jacobi orthogonal polynomials and weight functions that exactly satisfy the prescribed essential boundary conditions while maintaining orthogonality of the admissible functions. For free vibrations of plates with curvilinear stiffeners, made possible by additive manufacturing, both plate and stiffeners are modeled using a first-order shear deformation theory. For the thick isotropic plates and laminates, a third-order shear and normal deformation theory is used. The accuracy and computational efficiency of formulations are shown through a range of numerical examples involving different boundary conditions and plate thicknesses. The above formulations assume the whole plate as an equivalent single layer. When the material properties of individual layers are close to each other or thickness of the plate is small compared to other dimensions, the equivalent single layer plate (ESL) theories provide accurate solutions for vibrations and static deformations of multilayered structures. If, however, sufficiently large differences in material properties of individual layers such as those in sandwich structure that consists of stiff outer face sheets (e.g., carbon fiber-reinforced epoxy composite) and soft core (e.g., foam) exist, multilayered structures may exhibit complex kinematic behaviors. Hence, in such case, Cz0 conditions, namely, piecewise continuity of displacements and the interlaminar continuity of transverse stresses must be taken into account. Here, Ritz formulations are extended for ESL and layerwise (LW) Nth-order shear and normal deformation theories to model sandwich structures with various face-to-core stiffness ratios. In the LW theory, the C0 continuity of displacements is satisfied. However, the continuity of transverse stresses is not satisfied in both ESL and LW theories leading to inaccurate transverse stresses. This shortcoming is remedied by using a one-step well-known stress recovery scheme (SRS). Furthermore, analytical solutions of three-dimensional linear elasticity theory for vibrations and static deformations of simply supported sandwich plates are developed and used to investigate the limitations and applicability of ESL and LW plate theories for various face-to-core stiffness ratios. In addition to natural frequency results obtained from ESL and LW theories, the solutions of the corresponding 3-dimensional linearly elastic problems obtained with the commercial finite element method (FEM) software, ABAQUS, are provided. It is found that LW and ESL (even though its higher-order) theories can produce accurate natural frequency results compared to FEM with a considerably lesser number of degrees of freedom.
Doctor of Philosophy
In everyday life, plate-like structures find applications such as boards displaying advertisements, signs on shops and panels on automobiles. These structures are typically nailed, welded, or glued to supports at one or more edges. When subjected to disturbances such as wind gusts, plate-like structures vibrate. The frequency (number of cycles per second) of a structure in the absence of an applied external load is called its natural frequency that depends upon plate's geometric dimensions, its material and how it is supported at the edges. If the frequency of an applied disturbance matches one of the natural frequencies of the plate, then it will vibrate violently. To avoid such situations in structural designs, it is important to know the natural frequencies of a plate under different support conditions. One would also expect the plate to be able to support the designed structural load without breaking; hence knowledge of plate's deformations and stresses developed in it is equally important. These require mathematical models that adequately characterize their static and dynamic behavior. Most mathematical models are based on plate theories. Although plates are three-dimensional (3D) objects, their thickness is small as compared to the in-plane dimensions. Thus, they are analyzed as 2D objects using assumptions on the displacement fields and using quantities averaged over the plate thickness. These provide many plate theories, each with its own computational efficiency and fidelity (the degree to which it reproduces behavior of the 3-D object). Hence, a plate theory can be developed to provide accurately a quantity of interest. Some issues are more challenging for low-fidelity plate theories than others. For example, the greater the plate thickness, the higher the fidelity of plate theories required for obtaining accurate natural frequencies and deformations. Another challenging issue arises when a sandwich structure consists of strong face-sheets (e.g., made of carbon fiber-reinforced epoxy composite) and a soft core (e.g., made of foam) embedded between them. Sandwich structures exhibit more complex behavior than monolithic plates. Thus, many widely used plate theories may not provide accurate results for them. Here, we have used different plate theories to solve problems including those for sandwich structures. The governing equations of the plate theories are solved numerically (i.e., they are approximately satisfied) using the Ritz method named after Walter Ritz and weighted Jacobi polynomials. It is shown that these provide accurate solutions and the corresponding numerical algorithms are computationally more economical than the commonly used finite element method. To evaluate the accuracy of a plate theory, we have analytically solved (i.e., the governing equations are satisfied at every point in the problem domain) equations of the 3D theory of linear elasticity. The results presented in this research should help structural designers.
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Taetragool, Unchalisa. "Optimal Parameters for Doubly Curved Sandwich Shells, Composite Laminates, and Atmospheric Plasma Spray Process." Diss., Virginia Tech, 2018. http://hdl.handle.net/10919/81978.

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Optimization is a decision making process to solve problems in a number of fields including engineering mechanics. Bio-inspired optimization algorithms, including genetic algorithm (GA), have been studied for many years. There is a large literature on applying the GA to mechanics problems. However, disadvantages of the GA include the high computational cost and the inability to get the global optimal solution that can be found by using a honeybee-inspired optimization algorithm, called the New Nest-Site Selection (NeSS). We use the NeSS to find optimal parameters for three mechanics problems by following the three processes: screening, identifying relationships, and optimization. The screening process identifies significant parameters from a set of input parameters of interest. Then, relationships between the significant input parameters and responses are established. Finally, the optimization process searches for an optimal solution to achieve objectives of a problem. For the first two problems, we use the NeSS algorithm in conjunction with a third order shear and normal deformable plate theory (TSNDT), the finite element method (FEM), a one-step stress recovery scheme (SRS) and the Tsai-Wu failure criterion to find the stacking sequence of composite laminates and the topology and materials for doubly curved sandwich shells to maximize the first failure load. It is followed by the progressive failure analysis to determine the ultimate failure load. For the sandwich shell, we use the maximum transverse shear stress criterion for delineating failure of the core, and also study simultaneously maximizing the first failure load and minimizing the mass subject to certain constraints. For composite laminates, it is found that the first failure load for an optimally designed stacking sequence exceeds that for the typical [0°/90°]₅ laminate by about 36%. Moreover, the design for the optimal first failure load need not have the maximum ultimate load. For clamped laminates and sandwich shells, the ultimate load is about 50% higher than the first failure load. However, for simply supported edges the ultimate load is generally only about 10% higher than the first failure load. For the atmospheric spray process, we employ the NeSS algorithm to find optimal values of four process input parameters, namely the argon flow rate, the hydrogen flow rate, the powder feed rate and the current, that result in the desired mean particle temperature and the mean particle velocity when they reach the substrate. These optimal values give the desired mean particle temperature and the mean particle velocity within 5% of their target values.
Ph. D.
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Elmushyakhi, Abraham. "In-Plane Fatigue Characterization of Core Joints in Sandwich Composite Structures." University of Dayton / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1510678155755824.

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Books on the topic "Laminated and sandwich composite"

1

Center, Langley Research, ed. A higher-order bending theory for laminated composite and sandwich beams. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Center, Langley Research, ed. A higher-order bending theory for laminated composite and sandwich beams. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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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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Chamis, C. C. Fiber composite sandwich thermostuctural behavior, computationalsimulation. [Washington, DC]: National Aeronautics and Space Administration, 1986.

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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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Martin, C. Wayne. A three-node C(superscript)0 element for analysis of laminated composite sandwich shells. Edwards, Calif: Ames Research Center, 1989.

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R, Tullos Thomas, ed. Handbook of adhesive bonded structural repair. Park Ridge, N.J., U.S.A: Noyes Publications, 1992.

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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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Nettles, A. T. (Alan T.), Jackson J. R, and George C. Marshall Space Flight Center, eds. Comparison of open-hole compression strength and compression after impact strength on carbon fiber/epoxy laminates for the Ares I composite interstage. Huntsville], Ala: National Aeronautics and Space Administration, Marshall Space Flight Center, 2011.

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Book chapters on the topic "Laminated and sandwich composite"

1

Vaidya, Uday K. "Impact Response of Laminated and Sandwich Composites." In Impact Engineering of Composite Structures, 97–191. Vienna: Springer Vienna, 2011. http://dx.doi.org/10.1007/978-3-7091-0523-8_4.

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Manalo, Allan, Thiru Aravinthan, and Warna Karunasena. "Shear Behavior of Glue-Laminated Composite Sandwich Beams." In Advances in FRP Composites in Civil Engineering, 139–43. Berlin, Heidelberg: Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-17487-2_29.

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Dey, Sudip, Tanmoy Mukhopadhyay, and Sondipon Adhikari. "Uncertainty Quantification for Skewed Laminated Soft-core Sandwich Panels." In Uncertainty Quantification in Laminated Composites, 220–49. Boca Raton, FL : CRC Press, Taylor & Francis Group, [2018] | “A science publishers book.”: CRC Press, 2018. http://dx.doi.org/10.1201/9781315155593-10.

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Kerr-Anderson, Eric, Selvum Pillay, Basir Shafiq, and Uday K. Vaidya. "Compressively Pre-stressed Navy Relevant Laminated and Sandwich Composites Subjected to Ballistic Impact." In Dynamic Failure of Composite and Sandwich Structures, 151–76. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5329-7_4.

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Altenbach, Holm, Johannes Altenbach, and Wolfgang Kissing. "Elastic Behavior of Laminate and Sandwich Composites." In Mechanics of Composite Structural Elements, 91–160. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-662-08589-9_4.

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Altenbach, Holm, Johannes Altenbach, and Wolfgang Kissing. "Elastic Behavior of Laminate and Sandwich Composites." In Mechanics of Composite Structural Elements, 103–76. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-10-8935-0_4.

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Zhu, Shengqing, and Gin Boay Chai. "Impact of Aluminum, CFRP Laminates, Fibre-Metal Laminates and Sandwich Panels." In Composite Materials and Joining Technologies for Composites, Volume 7, 199–205. New York, NY: Springer New York, 2013. http://dx.doi.org/10.1007/978-1-4614-4553-1_21.

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Baier, H. J. "Composite Laminate and Sandwich Optimization with Applications." In Optimization of Large Structural Systems, 997–1009. Dordrecht: Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-010-9577-8_51.

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Jonna, Naresh, and J. Srinivas. "Aeroelastic Instability Characterization of Magnetorheological Fluid Filled-Core Laminated Composite Sandwich Beams." In Lecture Notes in Mechanical Engineering, 63–72. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2188-9_6.

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García-Castillo, Shirley Kalamis, Sonia Sánchez-Sáez, Carlos Santiuste, Carlos Navarro, and Enrique Barbero. "Perforation of Composite Laminate Subjected to Dynamic Loads." In Dynamic Failure of Composite and Sandwich Structures, 291–337. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5329-7_7.

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Conference papers on the topic "Laminated and sandwich composite"

1

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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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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Araújo, A. L., C. M. Mota Soares, C. A. Mota Soares, J. Herskovits, Jane W. Z. Lu, Andrew Y. T. Leung, Vai Pan Iu, and Kai Meng Mok. "Parameter Estimation in Hybrid Active-Passive Laminated Sandwich Composite Structures." In PROCEEDINGS OF THE 2ND INTERNATIONAL SYMPOSIUM ON COMPUTATIONAL MECHANICS AND THE 12TH INTERNATIONAL CONFERENCE ON THE ENHANCEMENT AND PROMOTION OF COMPUTATIONAL METHODS IN ENGINEERING AND SCIENCE. AIP, 2010. http://dx.doi.org/10.1063/1.3452037.

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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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Vaidya, Uday K., Anthony N. Palazatto, and L. N. B. Gummadi. "Low Velocity Impact Response and Nondestructive Evaluation of Sandwich Composite Structures." In ASME 1997 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/imece1997-1045.

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Abstract Composite sandwich constructions offer light weight and high bending stiffness advantages for aerospace and automotive applications among other structures. The use of a hollow truss core or z-fiber pin core is a new concept in sandwich composites, where the core is hollow and accessible, thereby providing space advantages for fuel cells and/or electronic assemblies besides from possessing high shear and axial stiffness. The z-fiber pins are oriented at predetermined geometry’s and penetrate into the laminated facesheets making-up the sandwich composite. In the reference (Palazatto et. al, 1997), the low velocity response of hollow truss core composites with z-fiber pins oriented at 10 degree and 20 degree angles with respect to the facesheets were investigated by us. The current paper presents the post-impact microstructure, ultrasonic and vibration based nondestructive evaluation (NDE) studies and compression-after-impact response accompanied by acoustic emission (AE) testing of these composites.
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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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Birman, Victor, and Larry W. Byrd. "On the Prediction of Damping in Composite and Sandwich Structures." In ASME 2001 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/imece2001/amd-25409.

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Abstract The paper outlines two methodologies for the analytical evaluation of the loss factor in composite laminates and in sandwich structures. One of these methods is based on the analysis of free vibrations, while the second approach utilizes mechanics of materials. The loss factor can be predicted both for specially orthotropic as well as for generally orthotropic laminae, subjected to axial stresses and/or transverse shear. The results for the loss factor of the laminae are in good agreement with available experimental data. As follows from numerical examples, the loss factor of polymer-matrix composites increases with the lamination angle and experiences relatively small variations at large values of these angles.
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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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Gantovnik, Vladimir, Zafer Gurdal, and Layne Watson. "A Genetic Algorithm with Memory for Optimal Design of Laminated Sandwich Composite Panels." In 43rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-1221.

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Reports on the topic "Laminated and sandwich composite"

1

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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Spera, D. A., J. B. Esgar, M. Gougeon, and M. D. Zuteck. Structural properties of laminated Douglas fir/epoxy composite material. Office of Scientific and Technical Information (OSTI), May 1990. http://dx.doi.org/10.2172/6492500.

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Barton, Oscar, Ratcliffe Jr., and Colin P. Fundamental Frequency of a Composite Sandwich Plate Containing Woven Layers. Fort Belvoir, VA: Defense Technical Information Center, August 1997. http://dx.doi.org/10.21236/ada359126.

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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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Blake, H. W., and J. M. Starbuck. Hydrostatic testing of thick laminated composite cylinders for performance model validation. Office of Scientific and Technical Information (OSTI), March 1993. http://dx.doi.org/10.2172/10151163.

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Hammerand, Daniel Carl. Critical time step for a bilinear laminated composite Mindlin shell element. Office of Scientific and Technical Information (OSTI), June 2004. http://dx.doi.org/10.2172/919205.

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Sandhu, R. S., W. E. Wolfe, R. L. Sierakowski, C. C. Chang, and H. R. Chu. Finite Element Analysis of Free-Edge Delamination in Laminated Composite Specimens. Fort Belvoir, VA: Defense Technical Information Center, June 1991. http://dx.doi.org/10.21236/ada251659.

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Blake, H. W., and J. M. Starbuck. Hydrostatic testing of thick laminated composite cylinders for performance model validation. Office of Scientific and Technical Information (OSTI), March 1993. http://dx.doi.org/10.2172/6855310.

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Stephens, Max. Numerical and Experimental Analysis of Composite Sandwich Links for the LCF System. Portland State University Library, January 2000. http://dx.doi.org/10.15760/etd.579.

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Groves, S. E. Preliminary evaluation of the strength of pin-joints in laminated composite materials. Office of Scientific and Technical Information (OSTI), March 1989. http://dx.doi.org/10.2172/7072288.

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