Journal articles: '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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Subramani, Mageshwaran, Ananda Babu Arumugam, and Manoharan Ramamoorthy. "Vibration Analysis of Carbon Fiber Reinforced Laminated Composite Skin with Glass Honeycomb Sandwich Beam Using HSDT." Periodica Polytechnica Mechanical Engineering 61, no. 3 (June 29, 2017): 213. http://dx.doi.org/10.3311/ppme.9747.

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In this paper, the vibration analysis of uniform laminated composite sandwich beam with a viscoelastic core was studied. The governing equation of motion of the laminated composite sandwich beam has been derived based on higher order shear deformation theory (HSDT) in finite element model (FEM). The developed finite element model has been validated in terms of natural frequencies with the experimental values and the available literature. Various parametric studies have been performed to examine the impact of the core thickness, ply orientation and aspect ratio of the uniform laminated composite sandwich beam in response to free vibration for various boundary conditions. From the results it was concluded that that natural frequencies could be increased with increasing the core thickness and decreased with increasing the aspect ratio.

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12

Patinha, Sérgio, Fernando Cunha, Raul Fangueiro, Sohel Rana, and Fernando Prego. "Acoustical Behavior of Hybrid Composite Sandwich Panels." Key Engineering Materials 634 (December 2014): 455–64. http://dx.doi.org/10.4028/www.scientific.net/kem.634.455.

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This paper deals with the characterization of acoustic insulation behaviour of hybridsandwich composite panels for application in modular house construction. These sandwich panelsare a sustainable, light-weight and durable solution, since are based on natural fibers structureimpregnated with a thermosetting polymer. In this way, three different types of hybrid compositepanels containing polyurethane core and laminated composite skins were produced and analyzed,varying the composition of laminates. The composite laminates of the prototypes were producedusing a vacuum infusion technique and were composed of glass and jute fibers, impregnated with apolyester resin. The solutions developed were compared with a standard, composed of plasterboardshaving different thicknesses and used for thermal and acoustic insulation. Acoustic insulationcharacterization was performed on specimens with 220x220 mm size in a sound proof acousticchamber. The tested sandwich panels showed promising results; however, their overall performancewas lower as compared to the performance of standard solutions used for comparison. Nevertheless,the specific acoustic insulation performance, i.e. sound reduction per unit mass of material for thedeveloped sandwich panels was significantly higher as compared to the standard materials,indicating better suitability of this innovative solution for light-weight construction and modularhousing.

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13

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

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In this work, the effects of variations in temperature and moisture concentrations on the static and free vibration response of sandwich laminated plates with low-density core have been studied. A higher order zigzag laminate theory is used which satisfies the continuity in transverse shear stress at the layer interfaces and zero transverse shear stress condition at the top and bottom surfaces of the laminate . The displacement field in this theory suitably allows for the quadratic distribution of transverse shear stress across the thickness and transverse compressibility effect of the core. An effective finite element formulation is carried out by employing a nine-node C0 isoparametric element for the above plate model. Numerical examples of composite and sandwich laminates with different material properties, effect of temperature and moisture variation, aspect ratios, boundary conditions, number of layers and ply orientations are considered for the analysis. Efficiency of the present plate model in predicting various responses subjected to hygrothermal loading is verified by comparing with the available published results.

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14

Abrate, Serge. "Localized Impact on Sandwich Structures With Laminated Facings." Applied Mechanics Reviews 50, no. 2 (February 1, 1997): 69–82. http://dx.doi.org/10.1115/1.3101689.

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Currently, there is strong interest in the effects of impact induced damage to composite structures as evidenced by the large number of articles on this topic that have appeared in the literature in recent years. With laminated composite structures, foreign object impacts, that are expected to occur during the life of the structure, can introduce damage that is often difficult to detect and can significantly reduce the strength of the structure. Research efforts concentrate on monolithic laminates while sandwich structures with laminated facings, which are also used extensively in aerospace and other applications, received less attention. A comprehensive review of the literature dealing with impact on sandwich structures is presented in this review article. The mechanics of contact between a rigid indentor and a sandwich structure is discussed in detail since it is very important to account for the local deformation in the contact zone in developing a model for predicting the contact force history. The mechanical behavior of foam and honeycomb core materials is reviewed along with experimental results and models for predicting the contact law between a smooth indentor and a sandwich structure. The development of mathematical models for predicting the contact force history and the overall response of the structure is also discussed. Finally we review the failure mechanisms involved in impact damage development, the parameters affecting damage size, and the residual properties of sandwich structures. This review article has 85 references.

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Manoharan, R., R. Vasudevan, and P. Edwin Sudhagar. "Semi-Active Vibration Control of Laminated Composite Sandwich Plate – An Experimental Study." Archive of Mechanical Engineering 63, no. 3 (September 1, 2016): 367–77. http://dx.doi.org/10.1515/meceng-2016-0021.

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Abstract In this study, the vibration analysis of fully and partially treated laminated composite Magnetorheological (MR) fluid sandwich plates has been investigated experimentally. The natural frequencies of fully and partially treated laminated composite MR fluid sandwich plates have been measured at various magnetic field intensities under two different boundary conditions. The variations of natural frequencies with applied magnetic field, boundary conditions and location of MR fluid pocket have been explored. Further, a comparison of natural frequencies of fully and partially treated MR fluid sandwich structure has been made at various magnetic field intensities.

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Leissa, Arthur W. "A Review of Laminated Composite Plate Buckling." Applied Mechanics Reviews 40, no. 5 (May 1, 1987): 575–91. http://dx.doi.org/10.1115/1.3149534.

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A brief overview is presented of considerations involved in the buckling of composite plates made of laminae having continuous, parallel fibers. Such plates are governed by orthotropic or anisotropic plate buckling theory for laminates which are symmetrically stacked with respect to the plate midplane. Unsymmetric laminates require a more complicated theory with bending-stretching coupling. Additional complicating factors are considered, including: interior holes, shear deformation, sandwich construction involving other materials, local effects, nonlinear stress-strain relationships, hygrothermal effects, and external stiffeners. Postbuckling behavior and the effects of initial imperfections are also described. Some representative results from the extensive literature (352 references) are included to aid in describing the various effects.

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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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Sarangi, S. K., and B. Basa. "Nonlinear finite element analysis of smart laminated composite sandwich plates." International Journal of Structural Stability and Dynamics 14, no. 03 (February 16, 2014): 1350075. http://dx.doi.org/10.1142/s0219455413500752.

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This paper deals with the nonlinear dynamic analysis of smart laminated composite sandwich plates. A three dimensional energy based finite element (FE) model has been developed for the composite sandwich plates integrated with the patches of active constrained layer damping (ACLD) treatment. Von Kármán type nonlinear strain–displacement relations and the first-order shear deformation theory (FSDT) are adopted individually for each layer of the sandwich plate in developing the FE model. The constraining layer of the ACLD treatment is considered to be made of active fiber composite (AFC) material. The Golla–Hughes–McTavish (GHM) method is used to model the constrained viscoelastic layer of the ACLD treatment in the time domain. Sandwich plates with symmetric and antisymmetric laminated faces separated by HEREX core are considered for evaluation of the numerical results. The numerical results indicate that the ACLD patches significantly improve the damping characteristics of the composite sandwich plates for suppressing their geometrically nonlinear transient vibrations. The effect of variation of piezoelectric fiber orientation angle in the AFC material on the control authority of the ACLD patches is also investigated.

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Selvaraj, Rajeshkumar, Kamesh Gupta, Shubham Kumar Singh, Ankur Patel, and Manoharan Ramamoorthy. "Free vibration characteristics of multi-core sandwich composite beams: Experimental and numerical investigation." Polymers and Polymer Composites 29, no. 9_suppl (November 2021): S1414—S1423. http://dx.doi.org/10.1177/09673911211057679.

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This study investigates the free vibration responses of laminated composite sandwich beam with multi-cores using experimental and numerical methods. The laminated composite face sheets are made by using hand layup method. An experimental modal test has been carried for different configurations of multi-core sandwich beams under different end conditions. The single-core and multi-core sandwich beams has been modeled and the natural frequencies of sandwich beams are determined using ANSYS software. The numerical model is verified by comparing the obtained natural frequencies with experimental results. The numerical and experimental results indicate that the multi-core sandwich beam greatly influences the structural stiffness compared with single-core sandwich beam under different end conditions. Furthermore, the influence of several parameters such as the end conditions, thickness of the core layer, and stacking sequence on the natural frequencies of the various configurations of the multi-core sandwich beams are presented.

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Singh, Sandeep, Jeeoot Singh, and Karunesh Kumar Shula. "Buckling of Laminated Composite and Sandwich Plates Using Radial Basis Function Collocations." International Journal of Structural Stability and Dynamics 15, no. 01 (January 2015): 1540002. http://dx.doi.org/10.1142/s0219455415400027.

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In this paper, buckling analysis of isotropic, orthotropic, laminated composite and sandwich plates utilizing trigonometric shear deformation theory and meshless method based on the finite point formulation using thin plate, polynomial and inverse multiquadric radial basis function is presented. The convergence of the present method is studied for isotropic and laminated composite plates for different radial basis functions with optimal value of shape parameter. Numerical examples of laminated and sandwich plates subjected to various types of in-plane loads are solved to demonstrate accuracy and applicability of present method. Several new results for variety of composite and sandwich plates are presented. The present results are observed to be in good agreement with those available in literature. The effects of orthotropy ratio of material, span to thickness ratio, number of layers, core thickness and lamination scheme on the critical load of plates are also presented.

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Ahmadi, Isa. "Edge stresses analysis in laminated thick sandwich cylinder subjected to distributed hygrothermal loading." Journal of Sandwich Structures & Materials 20, no. 4 (July 13, 2016): 425–61. http://dx.doi.org/10.1177/1099636216657681.

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The boundary layer hygrothermal stresses in the thick sandwich cylinder with laminated face are investigated. Uniform and through the thickness steady-state distribution for temperature and moisture content can be considered in the analysis. A displacement based layer-wise formulation is presented for analysis of thick sandwich composite cylinders subjected to hygrothermal loading conditions. Considering a general displacement field and employing a displacement based layer-wise theory, the governing equations of thick laminated sandwich cylinder are obtained. The displacement based formulation is derived for thick sandwich cylinder, which is subjected to non-uniform hygrothermal loading conditions. The faces of the sandwich cylinder are made of laminated composite with general layer stacking. The governing equations of the system include a set of coupled differential equations on the displacement components of the numerical surfaces. A semi-analytical solution is developed and the governing equations are solved for free edge boundary conditions. The accuracy of the numerical results is validated by the results of the finite element simulation and good agreements are seen between the predicted results. The free edge interlaminar stresses distributions are presented for thin and thick sandwich composite cylinders for uniform and non-uniform loading conditions. It is concluded that the presented layer-wise formulation is efficient and accurate method for analysis of thermal and hygroscopic stresses in thick and thin sandwich cylinders with general layer stacking.

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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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Zhu, Xiujie, Chao Xiong, Junhui Yin, Dejun Yin, and Huiyong Deng. "Transverse Bending and Axial Compressing Mechanical Characteristics of Carbon Fiber Reinforced Plastic Sandwich Laminated Square Tubes." Science of Advanced Materials 12, no. 9 (September 1, 2020): 1289–99. http://dx.doi.org/10.1166/sam.2020.3765.

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The transverse bending and axial compressing mechanical properties of carbon fiber reinforced plastic (CFRP) sandwich laminated square tubes with two kinds of cores, aluminum honeycomb and aluminum foam, respectively, were studied. The failure mechanism and damage processes of the two different CFRP sandwich laminated square tubes were studied by three-point bending and axial compressing experiments, comparing to CFRP hollow laminated square tube. The three-point bending process of CFRP sandwich laminated square tubes were also simulated in ABAQUS/Explicit and the failure mechanism and modes were deeply analyzed. The analytical model of composite laminated box beam using shear-deformable beam theory was extended to calculate the stiffness characteristics of CFRP sandwich laminated square tubes. The variation of bending, axial and shear stiffness in the linear elastic range were predicted. The results show that, after reaching the peak of three-point bending load, the bearing capacity of CFRP hollow laminated square tube reduced greatly due to the buckling instability of the two vertical sides, while that of the CFRP sandwich laminated square tubes were still considerable. A sudden strength damage occurred in the CFRP sandwich laminated tubes under the axial load, and the sandwich panels could slow down the drop of bearing capacity and increase the energy absorption. The load–displacement histories of numerical simulation and experimental result were in good agreement. The differences between analytically calculated and experimental measured stiffness characteristics were within 6.5%. The bending stiffness and axial stiffness of CFRP sandwich laminated tubes are large when the ply angle in the range from 0 to 45 degrees. Compared with the CFRP aluminum foam sandwich square tube, the specific stiffness and specific energy absorption of CFRP aluminum honeycomb sandwich square tube were higher but the energy absorbed was inferior.

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CHAKRABARTI, ANUPAM, and ABDUL HAMID SHEIKH. "DYNAMIC INSTABILITY OF COMPOSITE AND SANDWICH LAMINATES WITH INTERFACIAL SLIPS." International Journal of Structural Stability and Dynamics 10, no. 02 (June 2010): 205–24. http://dx.doi.org/10.1142/s0219455410003324.

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The dynamic instability of composite and sandwich laminates with interfacial slips is studied in this paper. An efficient finite element model recently developed by the authors is used for the purpose. The plate model is based on a refined higher-order shear deformation theory, where the transverse shear stresses are continuous at the layer interfaces with stress free conditions at plate top and bottom. A linear spring-layer model is used to model the interfacial slips by introducing in-plane displacement jump at the interfaces. Some interesting new results are presented in this paper, which are useful to understanding of the behavior of laminated composite materials.

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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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Grigsby, Warren, Victor Gager, Kimberly Recabar, Andreas Krause, Marc Gaugler, and Jan Luedtke. "Quantitative Assessment and Visualisation of the Wood and Poly(Lactic Acid) Interface in Sandwich Laminate Composites." Fibers 7, no. 2 (February 11, 2019): 15. http://dx.doi.org/10.3390/fib7020015.

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Fluorescence microscopy was applied to understand adhesion interfaces developed within laminated composite sandwiches formed between poly(lactic acid) (PLA) and wood veneers. Composites formed with maple veneer had greater tensile bond strength when manufactured at 200 °C (10.4 N/mm2) compared to formation at 140 °C (8.7 N/mm2), while significantly lower bond strength was achieved using spruce veneers, at 5.2 and 3.5 N/mm2, respectively. Qualitative and quantitative confocal microscopy assessments revealed differing bondline thicknesses and PLA ingress within the wood ultrastructure. Forming maple veneer composites at 200 °C promoted greater PLA mobility away from the bondline to reinforce the wood–PLA interface and deliver associated greater composite bond strength. The addition of 25% wood fibre to PLA led to fibre alignment and overlap within bondlines contributing to relatively thicker, heterogeneous bondlines. Study outcomes show that the composite processing temperature impacts the adhesion interface and composite performance and will have broad application over veneer overlays, laminates and wood plastic composites (WPCs) using wood, particles or fibres with PLA.

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Nor Hasnidawani, Johari, Noor Azlina Hassan, and Zahurin Halim. "Thermal Analysis of Kenaf Sandwich Panel." Advanced Materials Research 812 (September 2013): 271–74. http://dx.doi.org/10.4028/www.scientific.net/amr.812.271.

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The introduction of the eco-core sandwich panel composite is contributing a new approach to the designer to achieve high performance and light weight. In this research project, the new kenaf eco-core sandwich panel will be developed and then laminated with galvanized steel. The final goal is to find the optimum eco-core metal matrix composite sandwich structure with maximum mechanical properties such as stiffness and buckling. Kenaf eco-core sandwich will be fabricated and study on the interaction between eco-core sandwich panel and metal faces will be performed. The characterization of the eco-core sandwich panel will be done using different analytical tools. This study would provide a way to enhance the application of this new eco-core metal matrix composite sandwich structure.The amount of sample used was approximately 12 mg. The temperature profile was from 27°C to 1000°C at a heating rate of 10°C/min. In this study, result shows that degradation of composites starts to occur at about 180°C. Increasing the kenaf percent ratio will decrease the percent residue.

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Tu, Tran Minh. "Static analysis of laminated and sandwich composite plates based on simple refined higher-order displacement theory." Vietnam Journal of Mechanics 32, no. 2 (July 1, 2010): 95–106. http://dx.doi.org/10.15625/0866-7136/32/2/309.

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A simple refined higher-order displacement theory is used for the static analysis of laminated and sandwich plates. Both analytical and finite element solutions are developed. Numerical examples of laminated and sandwich plates are given for different thickness ratios, length-to-thickness ratios to illustrate the accuracy of the present formulation by comparing the present results with results already available in the literature.

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Utami, Mala, Jonathan Ernest Sirait, Beny Budhi Septyanto, Aries Sudiarso, and I. Nengah Putra Apriyanto. "Laminar Composite Materials for Unmanned Aircraft Wings." Defense and Security Studies 3 (December 21, 2022): 106–12. http://dx.doi.org/10.37868/dss.v3.id211.

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Unmanned Aerial Vehicles (UAVs) have high popularity, especially in the military field, but are now also being applied to the private and public sectors. One of the UAV components that require high material technology is the wing. The latest material technology developed as a material for unmanned aircraft wings is a composite material that has high strength and lightweight. This research aims to identify composite materials that can be used for unmanned aircraft wing structures. The method used in this research is a qualitative method with a literature study approach. The results of this theoretical study show that some of the latest composite materials that have been developed into materials for unmanned aircraft wings are Laminar Composites with a sandwich structure. Laminar and sandwich composites consist of various constituent materials such as Balsa wood fiber-glass and polyester resin, microparticles, Carbon Fibre Reinforced Polymer, polymer matrix composites reinforced with continuous fibers, Polymer matrix composites, E-glass/Epoxy, Kevlar/Epoxy, Carbon/Epoxy, woven fabrics, acrylonitrile butadiene styrene-carbon (ABS) laminated with carbon fiber reinforced polymer (CFRP) and uniaxial prepreg fabrics. Laminar and sandwich composite materials are a reference for developing unmanned aircraft wing structures that have resistant strength and lightweight.

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Ramesh, Babu V., R. Vasudevan, and Naveen B. Kumar. "Vibration Analysis of a Laminated Composite Magnetorheological Elastomer Sandwich Beam." Applied Mechanics and Materials 592-594 (July 2014): 2097–101. http://dx.doi.org/10.4028/www.scientific.net/amm.592-594.2097.

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In this study, the vibration analysis of a laminated composite magnetorheological elastomer (MRE) sandwich beam is presented. The governing differential equations of motion of a sandwich beam embedding a MRE layer as core layer and laminated composite beams as the face layers are presented in a finite element formulation. The validity of the developed finite element formulation is demonstrated by comparing results in terms of the natural frequencies derived from the present finite element formulation with those in the available literature. Various parametric studies are also performed to investigate the effect of a magnetic field on the variation of the natural frequencies and loss factors of the MR elastomer composite sandwich beam under various boundary conditions. Furthermore, the effect of the thickness of the MR elastomer layer on the variation of the natural frequencies and loss factors are studied. The study suggested that the natural frequency increases with increasing magnetic field, irrespective of the boundary conditions.

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Kurhe Nikhil, M., B. Shedbale Indrajeet, D. Charapale Utkarsh, and R. Manoharan. "Modal Analysis of Hybrid Laminated Composite Sandwich Plate." Materials Today: Proceedings 5, no. 5 (2018): 12453–66. http://dx.doi.org/10.1016/j.matpr.2018.02.225.

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Anish, Ajay Kumar, and Anupam Chakrabarti. "Failure mode analysis of laminated composite sandwich plate." Engineering Failure Analysis 104 (October 2019): 950–76. http://dx.doi.org/10.1016/j.engfailanal.2019.06.080.

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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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Araújo, A. L., P. Martins, C. M. Mota Soares, C. A. Mota Soares, and J. Herskovits. "Damping optimization of viscoelastic laminated sandwich composite structures." Structural and Multidisciplinary Optimization 39, no. 6 (May 6, 2009): 569–79. http://dx.doi.org/10.1007/s00158-009-0390-4.

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Madeira, J. F. A., A. L. Araújo, C. M. Mota Soares, C. A. Mota Soares, and A. J. M. Ferreira. "Multiobjective design of viscoelastic laminated composite sandwich panels." Composites Part B: Engineering 77 (August 2015): 391–401. http://dx.doi.org/10.1016/j.compositesb.2015.03.025.

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Kumar, Dhotre Pavan, and Chikkol V. Srinivasa. "Modal Characterization of Sandwich Skew Plates." Acta Mechanica et Automatica 15, no. 3 (September 1, 2021): 143–53. http://dx.doi.org/10.2478/ama-2021-0019.

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Abstract The current work focuses on the experimental and finite element free vibration studies of laminated composite sandwich skew plates. The comparison was made between the experimental values obtained by the Fast Fourier transform (FFT) analyzer and a finite element solution obtained from CQUAD8 finite element of The MacNeal-Schwendler Corporation (MSC) / NASA STRucture Analysis (NASTRAN) software. The influence of parameters such as aspect ratio (AR) (a/b), skew angle (α), edge condition, laminate stacking sequence, and fiber orientation angle (θ°) on the natural frequencies of sandwich skew plates was studied. The values obtained by both the finite element and experiment approaches are in good agreement. The natural frequencies increase with an increase in the skew angle for all given ARs.

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Jedari Salami, S., M. Sadighi, M. Shakeri, and M. Moeinfar. "An Investigation on Low Velocity Impact Response of Multilayer Sandwich Composite Structures." Scientific World Journal 2013 (2013): 1–9. http://dx.doi.org/10.1155/2013/175090.

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The effects of adding an extra layer within a sandwich panel and two different core types in top and bottom cores on low velocity impact loadings are studied experimentally in this paper. The panel includes polymer composite laminated sheets for faces and the internal laminated sheet called extra layer sheet, and two types of crushable foams are selected as the core material. Low velocity impact tests were carried out by drop hammer testing machine to the clamped multilayer sandwich panels with expanded polypropylene (EPP) and polyurethane rigid (PUR) in the top and bottom cores. Local displacement of the top core, contact force and deflection of the sandwich panel were obtained for different locations of the internal sheet; meanwhile the EPP and PUR were used in the top and bottom cores alternatively. It was found that the core material type has made significant role in improving the sandwich panel’s behavior compared with the effect of extra layer location.

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Vaidya, U. K., A. N. Palazotto, and L. N. B. Gummadi. "Low Velocity Impact and Compression-After-Impact Response of Z-Pin Reinforced Core Sandwich Composites." Journal of Engineering Materials and Technology 122, no. 4 (April 21, 2000): 434–42. http://dx.doi.org/10.1115/1.1289141.

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In the current work, sandwich composite structures with innovative constructions referred to as Z-pins, or truss core pins, are investigated. The Z-pin core sandwich construction offers enhanced transverse stiffness, high damage resistance, and multi-functional benefits. The present study deals with analysis of low-velocity impact (LVI) of Z-pin sandwich plate, and experimental studies of compression-after-impact characterization. Experimental studies on LVI of Z-pin sandwich plate considered in the analysis have been reported in Vaidya, et al., 1999, “Low Velocity Impact Response of Laminated Sandwich Composites with Hollow and Foam-Filled Z-Pin Reinforced Core,” Journal of Composites Technology and Research, JCTRER, 21, No. 2, Apr., pp. 84–97, where the samples were subjected to 11, 20, 28, 33, and 40 J of impact energy. The LVI analysis is developed with regards to Z-pin buckling as a primary failure mode (and based on experimental observations). A finite element model accounting for buckling of the pins has been developed and analyzed using ABAQUS. This paper also presents experimental results on compression-after-impact (CAI) studies which were performed on the sandwich composites with Z-pin reinforced core “with” and “without” foam. The experimental LVI tests were performed in Vaidya, et al., 1999, “Low Velocity Impact Response of Laminated Sandwich Composites with Hollow and Foam-Filled Z-Pin Reinforced Core,” Journal of Composites Technology and Research, JCTRER, 21, No. 2, Apr., pp. 84–97. The results indicate that selective use of Z-pin core is a viable idea in utilizing space within the core for sandwich composites in structural applications. [S0094-4289(00)02904-2]

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Nazari, AR, H. Hosseini-Toudeshky, and MZ Kabir. "Experimental investigations on the sandwich composite beams and panels with elastomeric foam core." Journal of Sandwich Structures & Materials 21, no. 3 (May 30, 2017): 865–94. http://dx.doi.org/10.1177/1099636217701093.

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In this paper, the load-carrying capacity and failure mechanisms of sandwich beams and panels with elastomeric foam core and composite laminate face sheets are investigated. For this purpose, the flexural behavior of laminated composite beams and panels (applied as face sheets) is firstly investigated under three-point bending and central concentrated loads, respectively. Then, the same examination is conducted for the sandwich beams and panels, in which the proposed elastomeric foam is utilized as the core material. It is shown that the failure mechanisms which are associated to the core in the sandwich structures with crushable foams are not considered in the examined sandwich structures. The collapse of the sandwich specimens, examined here, is observed due to the failure of the skins in some steps. By multi-step collapse of these specimens via separately failure of the top and bottom skins, a considerable amount of energy is absorbed between these steps. Due to non-brittle behavior of the core material under loading, a large compression resistance is observed after failure of the top skin which led to the recovery of the load-carrying capacity in the sandwich beams. A similar behavior for the sandwich panels led to the increase of the ultimate strength after appearance of the failure lines on the top skin. The general outcomes of this investigation promise a good influence for the application of elastomeric foam as core material for sandwich structures.

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Muric-Nesic, Jelena, Z. Stachurski, Paul Compston, and N. Noble. "Effect of Vibrations on Void Content in Composite Materials." Advanced Materials Research 32 (February 2008): 145–48. http://dx.doi.org/10.4028/www.scientific.net/amr.32.145.

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Eliminating common defects such as voids, bubbles and poor adhesion at interfaces will increase the quality of laminated sandwich composite structure. We are experimenting and analyzing the effect of mechanical vibrations applied to the curing system of composite materials production, particularly on minimizing void content. The range of frequency of vibrations covered was from 2Hz to 8kHz, for different period of vibrations. The composite laminates were made by hand lay-up using glass fibres and vinyl-ester resin, and examined under a microscope to determine types and quantity of defects. The results showed reduction in the number of bubbles (as well as in void content) at frequencies between 10Hz and 50Hz for 30 minutes of vibrations.

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Hoseinzadeh, Mohammad, and Jalil Rezaeepazhand. "Dynamic stability enhancement of laminated composite sandwich plates using smart elastomer layer." Journal of Sandwich Structures & Materials 22, no. 8 (December 17, 2018): 2796–817. http://dx.doi.org/10.1177/1099636218819158.

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The dynamic stability of composite sandwich plates with a smart elastomer layer subjected to an axial periodic load is investigated. A finite element model of the composite sandwich plate with Magnetorheological elastomer (MRE) core is developed. A MRE layer, which its mechanical properties change with the applied magnetic field, is used as a damping layer to improve the stability of the structure. Due to the intrinsic characteristics of the MREs, these materials commonly operate in their pre-yield region. In this region, complex shear modulus is used for these materials. The effect of different parameters such as stacking sequences, boundary conditions, geometry of the sandwich plate, thickness and partial activation of the MRE layer on the damping treatment and stability boundaries is investigated. The presented results show that the application of an MRE layer as a core in the composite sandwich plate changes the stability region of the structure. Therefore, the instability boundaries can be manipulated to achieve the desired dynamic response of the structure.

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Vinson, J. R. "In-Plane Shear Strength Determination of Composite Materials in Laminated and Sandwich Panels." Applied Mechanics Reviews 50, no. 11S (November 1, 1997): S237—S240. http://dx.doi.org/10.1115/1.3101842.

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A simple test procedure is available to determine the in-plane shear strength of laminated composite materials, as well as other orthotropic and isotropic advanced material systems. The test apparatus is simple, inexpensive, and the flat rectangular plate test specimen is not restricted in size or aspect ratio. In addition to its use for laminated composite materials, the test can also be used for foam core sandwich panels. In sandwich panels, the tests can be used to determine the in-plane shear strength of the faces, the core and/or the adhesive bond between face and core. The shear stresses developed vary linearly in the thickness direction and are constant over the entire planform area.

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Zhang, Chen, Yunfei Rao, Zhe Li, and Wei Li. "Low-Velocity Impact Behavior of Interlayer/Intralayer Hybrid Composites Based on Carbon and Glass Non-Crimp Fabric." Materials 11, no. 12 (December 5, 2018): 2472. http://dx.doi.org/10.3390/ma11122472.

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Composites have gained wide use in structural applications; however, they are sensitive to impact damage. The use of hybrid composites is an effective way to overcome this deficiency. The effects of various hybrid structures of interlayer and intralayer warp-knitted fabrics with carbon and glass fibers on the low-velocity impact behavior of composite laminates were studied. Drop-weight impact tests were conducted on two types of interlayer, sandwich and intralayer hybrid composite laminates, which were compared with homogenous composite laminates. During low-velocity impact tests, the time histories of impact forces and absorbed energy by laminate were recorded. The failure modes were analyzed using the micro-CT (computed tomography) and C-scan techniques. The results revealed that the hybrid structure played an important role in peak force and the absorbed energy, and that the hybrid interface had an influence on damage modes, whereas the intralayer hybrid composite laminate damage was affected by the impact location. The intralayer hybrid laminate with C:G = 1:1 exhibited better impact resistance compared to the other hybrid structures.

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Kovács, György, and József Farkas. "Optimal design of a composite sandwich structure." Science and Engineering of Composite Materials 23, no. 2 (March 1, 2016): 237–43. http://dx.doi.org/10.1515/secm-2014-0186.

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AbstractThis study shows the optimization method for a new complex structural model: laminated carbon fiber-reinforced plastic (CFRP) deck plates with polystyrene foam (EPS) inner core. The structure is designed for both minimal cost and minimal weight, taking into consideration the design constraints as follows: maximum deflection of the total structure, stress in the composite plates, stress in the polystyrene foam, eigenfrequency of the structure, thermal insulation of the structure, and size constraints for the design variables.

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Avhad, Pravin V., and Atteshamuddin S. Sayyad. "On the deformation of laminated composite and sandwich curved beams." Curved and Layered Structures 9, no. 1 (October 18, 2021): 1–12. http://dx.doi.org/10.1515/cls-2022-0001.

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Abstract Plenty of research articles are available on the static deformation analysis of laminated straight beams using refined shear deformation theories. However, research on the deformation of laminated curved beams with simply supported boundary conditions is limited and needs more attention nowadays. With this objective, the present study deals with the static analysis of laminated composite and sandwich beams curved in elevation using a new quasi-3D polynomial type beam theory. The theory considers the effects of both transverse shear and normal strains, i.e. thickness stretching effects. In the present theory, axial displacement has expanded up to the fifth-order polynomial in terms of thickness coordinates to effectively account for the effects of curvature and deformations. The present theory satisfies the zero traction boundary condition on the top and bottom surfaces of the beam. Governing differential equations and associated boundary conditions are established by using the Principal of virtual work. Navier’s solution technique is used to obtain displacements and stresses for simply supported beams curved in elevation and subjected to uniformly distributed load. The present results can be benefited to the upcoming researchers.

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Ali, Hafiz Tauqeer, Roya Akrami, Sakineh Fotouhi, Farzad Pashmforoush, Cristiano Fragassa, and Mohammad Fotouhi. "EFFECT OF THE STACKING SEQUENCE ON THE IMPACT RESPONSE OF CARBON-GLASS/EPOXY HYBRID COMPOSITES." Facta Universitatis, Series: Mechanical Engineering 18, no. 1 (March 27, 2020): 069. http://dx.doi.org/10.22190/fume191119010a.

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This paper investigates low-velocity impact response of Quasi Isotropic (QI) hybrid carbon/glass fiber reinforced polymer composites with alternate stacking sequences. Cross-ply woven carbon and glass fibers were used as reinforcing materials to fabricate sandwiched and interlayer hybrid composites. For comparison, the laminates containing only-carbon and only-glass fibers were also studied. Drop weight test was used to impact the samples. The images captured by a normal camera demonstrated that localized damages (delamination) existed within plies. The hybrid laminates had smaller load drops, smaller maximum deflection, and higher maximum load compared to the single fiber laminates. In addition, carbon outside interlayer hybrid laminate showed the highest maximum load and energy absorption, showing the significant dependence of the impact performance on hybridization and stacking sequence. It was concluded that a hybrid composite would help improve impact performance of laminated composites compared to non-hybrid composites if they are properly designed.

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Hachemi, M., and SM Hamza-Cherif. "Free vibration analysis of composite laminated and sandwich plate with circular cutout." Journal of Sandwich Structures & Materials 22, no. 8 (November 24, 2018): 2655–91. http://dx.doi.org/10.1177/1099636218811393.

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This paper presents the free vibration analysis of a composite laminated and sandwich square plate with circular cutout. The problem formulation is based on the higher order shear deformation plate theory HDST C0 coupled with a curved quadrilateral p-element. The elements of the stiffness and mass matrices are calculated analytically. The curved edges are accurately represented using the blending function method. A calculation program is developed to determine the fundamental frequencies for different physical and mechanical parameters such as the cutout size and location, plate thickness, fiber orientation angle and boundary conditions. The results obtained show a good agreement with the available solutions in the literature. New results for the fundamentals frequencies of composite laminated and sandwich plates with circular cutout are presented.

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Chróścielewski, Jacek, Marian Klasztorny, Mikołaj Miśkiewicz, Łukasz Pyrzowski, Magdalena Rucka, and Krzysztof Wilde. "GFRP sandwich composite with PET core in shell structure of footbridge." Budownictwo i Architektura 13, no. 2 (June 11, 2014): 183–90. http://dx.doi.org/10.35784/bud-arch.1894.

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The paper presents experimental study of sandwich composite used for an innovative foot-and-cycle bridge. The footbridge has a U-shaped shell structure made of sandwich consisting GFRP laminate covers and foam PET core. The bridge is manufactured using the infusion technology. Results of one and two directional tension tests of the laminates, compression tests of PET foam samples and 3-point as well as 4-point bending tests of sandwich beams are presented.

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Hegde, Sandesh Rathnavarma, and Mehdi Hojjati. "Performance of composite sandwich structures under thermal cycling." Journal of Composite Materials 54, no. 2 (July 10, 2019): 271–83. http://dx.doi.org/10.1177/0021998319862324.

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Effect of thermally induced microcracks on mechanical performance of a space grade laminated sandwich panel is investigated. A simple non-contact setup using liquid nitrogen is developed to subject the material to low temperature of −170℃ with cooling rate of 24℃/min. Then the samples are exposed to the elevated temperature of 150℃ inside oven. Microcracks formation and propagation are monitored through microscopic observation of cross-section during the cycling. Flatwise tensile test is performed after a number of cycles. A correlation is made between number of cycles and flatwise mechanical strength after quantifying the microcracks. It is observed that the crack formation gets saturated at about 40 cycles, avoiding the need to conduct more thermal cycles. Microcrack formation both at the free edge and middle of laminate was observed. The crack density at the middle was comparatively less than the ones found on the free edges. Results for non-contact cooling are compared with samples from direct nitrogen contact cooling. Microscopic inspection and flatwise test show differences between contact and non-contact cooled samples. Flatwise tensile strength for non-contact cooled samples shows 15% reduction, while the contact cooled samples have about 30% decrease in bond strength. A 3D finite element analysis is conducted to qualitatively identify the location of stress concentration which can be possible sites of crack formation. Good agreement is observed between the model and experimental results.

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Wolff, Ernest G., Hong Chen, and Darrell W. Oakes. "Hygrothermal Deformation of Composite Sandwich Panels." Advanced Composites Letters 9, no. 1 (January 2000): 096369350000900. http://dx.doi.org/10.1177/096369350000900104.

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Coefficients of thermal and moisture expansion (CTE and CME) can be predicted for many composite laminates and sandwich panels. Core and adhesive properties, such as geometry and stiffness are important variables. Laminate theory is augmented with a modified model for anisotropic core properties to predict the CTE and CME of sandwich panels. Procedures to measure both CTE and CME are described. Since these are thermodynamic properties, methods to obtain equilibrium moisture strains are needed. Results are given for CFRP facesheets with Al and NOMEX honeycomb cores, and for woven Kevlar facesheets with Al cores. Agreement with predictions is good and depends highly on knowledge of properties of all constituents.

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Journal articles on the topic 'Laminated and sandwich composite'

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