Journal articles: 'Honeycomb sandwiched beam'

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Sharif, Umer, Bei Bei Sun, Peng Zhao, Dauda Sh Ibrahim, Orelaja Oluseyi Adewale, and Aleena Zafar. "Dynamic Behavior Analysis of the Sandwich Beam Structure with Magnetorheological Honeycomb Core under Different Magnetic Intensities: A Numerical Approach." Materials Science Forum 1047 (October 18, 2021): 31–38. http://dx.doi.org/10.4028/www.scientific.net/msf.1047.31.

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In this article a sandwich beam structure with honeycomb core filled of MRE (magnetorheological elastomer) with different ratios of Elastomer and iron particles is proposed. Modal response for structures with Nylon and Resin8000 honeycomb core filled with MRE and sandwiched between aluminum face sheets were analyzed and compared for two different ratios of MRE by placing magnets at free end and center of the structure. The force generated by magnets on the sandwich beam structure was calculated using ANSYS EDT and the modal response of the structure was then observed under generated magnetic force using ANSYS Workbench. The results showed that the resonance frequency of the structure decreased as the magnetic intensity was increased for all the cases specially for the first mode. Secondly structure with Nylon honeycomb core showed lower frequency drop and higher deformation than the structure with Resin8000 honeycomb core.

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Atli-Veltin, B., and F. Gandhi. "Energy absorption of sandwiched honeycombs with facesheets under in-plane crushing." Aeronautical Journal 117, no. 1193 (July 2013): 687–708. http://dx.doi.org/10.1017/s000192400000837x.

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AbstractThe in-plane crushing and energy absorption of sandwiched honeycomb cores with facesheets are examined through finite element simulations. Assuming no debonding between the facesheet and honeycomb core (which would be the case if manufacturing techniques such as brazing are used to produce very strong bonds between the facesheeet and the core), intracellular buckling mode for thin facesheets, and wrinkling mode for thick facesheets are observed. In the dimpling mode, deformation is governed by the core, honeycomb vertical cell walls do not deform, and the inclined wall deformation does not vary through the cell depth. In the wrinkling mode, deformation is governed by the facesheet, the vertical cell walls deform significantly, and the inclined cell wall deformation varies through the cell depth. Increasing cell angle increased Specific Energy Absorption (SEA) for honeycombs with thin facesheets. Decreasing vertical cell wall length increased SEA for honeycombs with thick facesheets. Increasing wall thickness and decreasing core depth increased SEA for honeycombs with thin and thick facesheets. With geometric changes, SEA increased ~3 times over the baseline configurations. For a given keel beam dimensions, using fewer rows of larger cells reduces the effective non-dimensional core-depth, thereby increasing the effect of the facesheet and the SEA significantly. The SEA of sandwiched honeycombs with facesheets in in-plane crushing appears to be competitive with, or better than, SEA honeycombs in out-of-plane crushing.

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Liu, Weidong, Honglin Li, Jiong Zhang, and Hongda Li. "Theoretical analysis on the elasticity of a novel accordion cellular honeycomb core with in-plane curved beams." Journal of Sandwich Structures & Materials 22, no. 3 (April 11, 2018): 702–27. http://dx.doi.org/10.1177/1099636218768174.

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Flexible skin is an essential component for morphing wind turbine blade to maintain a smooth profile and bear aerodynamic loads during morphing. Cellular honeycomb cores with low in-plane and high out-of-plane stiffness are potential candidates for support structures of flexible skin. Honeycomb structure also requires zero Poisson’s ratio to avoid unnecessary stress and strain during one-dimensional morphing. A novel accordion cellular honeycomb core of close-to-zero Poisson’s ratio with in-plane corrugated U-type beams was proposed as a solution for these problems. The elastic properties of the structure are illustrated through a combination of theoretical analysis and finite element analysis. Results show that better in-plane morphing and out-of-plane load-bearing capabilities can be obtained with parameters of larger height-to-length ratio, spacing-to-length ratio and vertical beam to U-type beam thickness ratio as well as smaller thickness-to-length ratio. Results of comparisons on properties of the proposed honeycomb with two existing accordion honeycombs reveal that the in-plane elastic modulus of the proposed structure is as low as about 56% of that of the accordion honeycomb with V-type beams and 79% of that of the accordion honeycomb with cosine beams, showing better in-plane property but weaker out-of-plane load-bearing capability. Nevertheless, the out-of-plane load-bearing capability can be reinforced by increasing the vertical beam to U-type beam thickness ratio. Smaller driving force and less energy consumption are required by the proposed honeycomb core than conventional structures during morphing. The methods and results could be used for predictions of elasticity in design of sandwich morphing skin with similar cellular honeycomb cores.

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Zhu, Dalei, Xiaoxin Wang, Shuang Yao, Jianfeng Zhang, and Mengmeng Jiao. "Analytical and experimental study on honeycomb sandwich plates reinforced by ring beam of satellites." Journal of Physics: Conference Series 2472, no. 1 (May 1, 2023): 012007. http://dx.doi.org/10.1088/1742-6596/2472/1/012007.

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Abstract The equivalent parameters of hexagon aluminum honeycombs are work out with the theories of sandwich plates in this paper. The honeycomb sandwich plate reinforced by ring beam applied with static load is simulated by the finite element model of honeycomb sandwich plates, which is validated by static test. The research results show that the numerical calculation error of the honeycomb sandwich plate is less than 10% compared with test results, which is acceptable for an engineering project, and the mechanical behavior of the honeycomb sandwich plate can be described in detail. Thus, the method of equivalent honeycomb parameter is proved to be effective for the design and analysis of honeycomb sandwich plates. The influence of equivalent elasticity modulus and equivalent shear modulus to honeycomb sandwich plates can be reflected exactly from the results which are figured out with the equivalent theories of sandwich plates. The assembly clearance and assembly accuracy have a significant influence to the test results of honeycomb sandwich plates, which is obvious especially at a lower load level.

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Li, Chong, Hui-Shen Shen, and Hai Wang. "Nonlinear Vibration of Sandwich Beams with Functionally Graded Negative Poisson’s Ratio Honeycomb Core." International Journal of Structural Stability and Dynamics 19, no. 03 (March 2019): 1950034. http://dx.doi.org/10.1142/s0219455419500342.

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This paper investigates the nonlinear flexural vibration of sandwich beams with functionally graded (FG) negative Poisson’s ratio (NPR) honeycomb core in thermal environments. The novel constructions of sandwich beams with three FG configurations of re-entrant honeycomb cores through the beam thickness direction are proposed. The temperature-dependent material properties of both face sheets and core of the sandwich beams are considered. 3D full-scale finite element analyses are conducted to investigate the nonlinear vibration, and the variation of effective Poisson’s ratio (EPR) of the sandwich beams in the large deflection region. Numerical simulations are carried out for the sandwich beam with FG-NPR honeycomb core in different thermal environmental conditions, from which results for the same sandwich beam with uniform distributed NPR honeycomb core are obtained as a basis for comparison. The effects of FG configurations, temperature changes, boundary conditions, and facesheet-to-core thickness ratios on the nonlinear vibration ratio curves and EPR–deflection curves of sandwich beams are discussed in detail.

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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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ZHU, KAIGE, and DAINING FANG. "CALCULATION OF DISPERSION CURVES FOR ARBITRARY WAVEGUIDES USING FINITE ELEMENT METHOD." International Journal of Applied Mechanics 06, no. 05 (October 2014): 1450059. http://dx.doi.org/10.1142/s1758825114500598.

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Dispersion curves for waveguide structures are an important prerequisite for the implementation of guided wave-based nondestructive evaluation (NDE) approach. Although many methods exist, each method is only applicable to a certain type of structures, and also requires complex programming. A Bloch theorem-based finite element method (FEM) is proposed to obtain dispersion curves for arbitrary waveguides using commercial finite element software in this paper Dispersion curves can be obtained for a variety of structures, such as homogeneous plates, multilayered structures, finite cross section rods and honeycomb sandwiches. The propagation of guided waves in honeycomb sandwich plates and beams are discussed in detail. Then, dispersion curves for honeycomb sandwich beams are verified by experiments.

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Sharif, Umer, Lin Chen, Beibei Sun, Dauda Sh Ibrahim, Orelaja Oluseyi Adewale, and Noman Tariq. "An experimental study on dynamic behaviour of a sandwich beam with 3D printed hexagonal honeycomb core filled with magnetorheological elastomer (MRE)." Smart Materials and Structures 31, no. 5 (March 18, 2022): 055004. http://dx.doi.org/10.1088/1361-665x/ac5c8a.

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Abstract Sandwich beams with an aluminium face sheet and a magnetorheological elastomer (MRE) of varying proportions of elastomer and magnetic particles (weight to weight)% filled in a honeycomb core of Nylon and Resin8000 are manufactured and experimentally analysed in this study. To evaluate the dynamic properties of sandwich beams, manufactured structures subjected to sine sweep and classic shock tests and assessed both with and without magnetic field of varying intensities applied on the free end of the beam. The experimental results demonstrated good performance in vibration level attenuation, particularly in the structure’s primary vibration mode under consideration. The magnetic field applied was capable of lowering the first natural frequency of the proposed sandwich beam structures. Experiment results showed that an increase in an induced magnetic field shifted the natural frequencies, vibration amplitude, and damping ratio of sandwich panels with MRE honeycomb core.

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Gdoutos, E. E., and M. S. Konsta-Gdoutos. "Load and Geometry Effect on Failure Mode Initiation of Composite Sandwich Beams." Applied Mechanics and Materials 3-4 (August 2006): 173–78. http://dx.doi.org/10.4028/www.scientific.net/amm.3-4.173.

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Facing compressive failure, facing wrinkling and core shear failure are the most commonly encountered failure modes in sandwich beams with facings made of composite materials. The occurrence and sequence of these failure modes depends on the geometrical dimensions, the form of loading and type of support of the beam. In this paper the above three failure modes in sandwich beams with facings made of carbon/epoxy composites and cores made of aluminum honeycomb and two types of foam have been investigated. Two types of beams, the simply supported and the cantilever have been considered. Loading included concentrated and uniform. It was found that in beams with foam core facing wrinkling and core shear failure occur, whereas in beams with honeycomb core facing compressive failure and core shear crimping take place. Results were obtained for the dependence of failure mode on the geometry of the beam and the type of loading. The critical beam spans for failure mode transition from core shear to wrinkling failure were established. It was found that initiation of a particular failure mode depends on the properties of the facing and core materials, the geometrical configuration and loading of composite sandwich beams.

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Meng, Li Qing, Shi Zhe Chen, Yan Wu, and Xue Feng Shu. "Projectile Impact Behaviour of Sandwich Material with Nomex Honeycomb and Metallic Skins." Advanced Materials Research 204-210 (February 2011): 632–35. http://dx.doi.org/10.4028/www.scientific.net/amr.204-210.632.

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Projectile impact test is carried out to investigate damage and failure behaviour under different impact velocity from 90m/s to 160m/s. Strain-time history curve on the control points are analysed in this paper. Sandwich beam dynamic response and the degree of structural degeneration under impact loading both depends on the thickness of metallic skins. The projectile impact test demonstrate difference damage characteristics between the sandwich beams with different thickness skins. The peak stress value are estimated approximately to determine the skin deformation and sandwich beam global damage degree.

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Meng, Li Qing, Yan Wu, Shi Zhe Chen, and Xue Feng Shu. "Quasi-Static Failure Analysis of Honeycomb Sandwich Beam with Composite Facesheets." Advanced Materials Research 160-162 (November 2010): 855–59. http://dx.doi.org/10.4028/www.scientific.net/amr.160-162.855.

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Sandwich construction consists of two thin composite or metal facesheets separated by a core material. Despite extensive researches on the sandwich constructions, their mechanical properties and failure behaviours are still not fully understand. The objective of the paper is to use a experimental and theoretical predicting failure mode for sandwich beam consisting of GFRP facesheets and Nomex honeycomb core. Two kinds of composite sandwich beams are observed in quasi-static three-point bending and indentation test.

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Kong, Cheol Won, Se Won Eun, Jae Sung Park, Ho Sung Lee, Young Soon Jang, Yeong Moo Yi, and Gwang Rae Cho. "The Effect of a Honeycomb Core on the Mechanical Properties of Composite Sandwich Plates." Key Engineering Materials 297-300 (November 2005): 2752–57. http://dx.doi.org/10.4028/www.scientific.net/kem.297-300.2752.

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When comparing composite sandwich analysis with an exact solution, the results of finite element modeling with an ANSYS shell 91 element agreed well with the exact solution. The practical applications of the shell 91 element are demonstrated with a four-point bend test conducted on sandwich beam specimens. The specimens comprised carbon/epoxy fabric face sheets and a honeycomb core. Two kinds of honeycomb cores were used to fabricate the composite sandwich specimens: an aluminum one and a glass/phenolic one. The predictions with the shell 91 element were also agreed well with the experimental results. A variety of tests was conducted; namely, a long beam flexural test, a short beam shear test, a flatwise tensile test, a flatwise compression test and an edge compression test. The sandwich plate with the aluminum honeycomb core had a specific bending stiffness that was 1.7 to 2.0 times higher than that of the sandwich plate with the glass/ phenolic honeycomb core.

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Coskun, Onur, and Halit S. Türkmen. "Bending Fatigue Behaviour of Laminated Sandwich Beams." Advanced Materials Research 445 (January 2012): 548–53. http://dx.doi.org/10.4028/www.scientific.net/amr.445.548.

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In this study, the bending fatigue behaviour of laminated sandwich beams, which are made of carbon/epoxy face sheets and aramid honeycomb core, has been investigated experimentally. The wet hand lay-up technique is used and curing is processed on the heated vacuum table at an elevated temperature to manufacture the sandwich beams. The experimental set-up for bending fatigue test provides a cantilever in one end and a cyclic load at the free end with constant displacement amplitude at room temperature. The load applied to the beam is measured using a load cell during the bending test. Different displacement amplitudes are performed. Mechanical properties, bending stiffness and free vibration frequency of the sandwich beam are investigated. The bending test of the beams and vibration identification test using a vibration analyzer, a hammer and an accelerometer are performed to measure the bending stiffness and determination of free vibration frequency of the clamped sandwich beams before starting and after completion of the fatigue tests. The bending stiffness and free vibration frequencies before and after the fatigue tests are compared to understand the effect of repeated loadings on the mechanical performance of the laminated sandwich beams.

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Saseendran, Vishnu, and Christian Berggreen. "Mixed-mode fracture evaluation of aerospace grade honeycomb core sandwich specimens using the Double Cantilever Beam–Uneven Bending Moment test method." Journal of Sandwich Structures & Materials 22, no. 4 (June 3, 2018): 991–1018. http://dx.doi.org/10.1177/1099636218777964.

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Fracture testing of aerospace grade honeycomb core sandwich composites is carried out using the Double Cantilever Beam specimen loaded with Uneven Bending Moments, and a Double Cantilever Beam–Uneven Bending Moment test rig capable of applying pure moments is utilized. Specimens with carbon fiber-reinforced plastic face sheets are employed with a range of honeycomb core grades comprising of Nomex® and Kevlar paper. The sandwich specimens are reinforced with steel doublers to reduce excessive rotation of the face sheets. The mode mixity phase angle pertaining to a particular ratio of moments between the two arms of the Double Cantilever Beam specimen is determined using the numerical mode mixity method—Crack Surface Displacement Extrapolation method. For Nomex® honeycomb core sandwich specimens, it is observed that the mode I interface fracture toughness increases with increase in core density. The interface fracture toughnesses for Nomex®-based honeycomb cores are also compared against specimens with Kevlar paper-based honeycomb cores. Crack propagation is observed at the interface just beneath the meniscus layer for the majority of the tested specimen configurations. The Double Cantilever Beam–Uneven Bending Moment test methodology with the concept of direct application of moments on both crack flanks has proven to have a significant potential for mixed mode face/core fracture characterization of aerospace grade sandwich composites.

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Sadeghian, Pedram, Dimo Hristozov, and Laura Wroblewski. "Experimental and analytical behavior of sandwich composite beams: Comparison of natural and synthetic materials." Journal of Sandwich Structures & Materials 20, no. 3 (May 31, 2016): 287–307. http://dx.doi.org/10.1177/1099636216649891.

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In this study, the flexural behavior of sandwich composite beams made of fiber-reinforced polymer (FRP) skins and light-weight cores are studied. The focus is on the comparison of natural and synthetic fiber and core materials. Two types of fiber materials, namely glass and flax fibers, as well as two types of core materials, namely polypropylene honeycomb and cork, are considered. A total of 105 small-scale sandwich beam specimens (50 mm wide) were prepared and tested under four-point bending. Test parameters were fiber types (flax and glass fibers), core materials (cork ad honeycomb), skin layers (0, 1, and 2 layers), core thicknesses (6–25 mm), and beam spans (150 and 300 mm). The load–deflection behavior, peak load, initial stiffness, and failure mode of the specimens are evaluated. Moreover, the flexural stiffness, shear rigidity, and core shear modulus of the sandwich composites are computed based on the test results of the two spans. An analytical model is also implemented to compute the flexural stiffness, core shear strength, and skin normal stress of the sandwich composites. Overall, the natural fiber and cork materials showed a promising and comparable structural performance with their synthetic counterparts.

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Kirollos, Benjamin William Mounir, Richard Trede, and Peter Lampen. "The experimental static mechanical performance of ironed repaired GFRP–honeycomb sandwich beams." Journal of Sandwich Structures & Materials 14, no. 6 (September 19, 2012): 694–714. http://dx.doi.org/10.1177/1099636212460538.

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Damaged glass fibre reinforced plastic–honeycomb core sandwich beams are repaired using uncured glass fibre reinforced plastic fabrics and a handheld iron. The effect of iron temperature, application time and pressure on the effectiveness of repair is investigated by measuring the failure load and flexural stiffness of the repaired beams using third span four-point bending tests. Repairs are tested in compression and tension. A repair process is suggested which consistently recovers 95% of the compressive strength and 77% of the tensile strength of the damaged beam. The repair is shown to have little effect on beam flexural stiffness.

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Chantarapanich, Nattapon, Apinya Laohaprapanon, Sirikul Wisutmethangoon, Pongnarin Jiamwatthanachai, Prasert Chalermkarnnon, Sedthawatt Sucharitpwatskul, Puttisak Puttawibul, and Kriskrai Sitthiseripratip. "Fabrication of three-dimensional honeycomb structure for aeronautical applications using selective laser melting: a preliminary investigation." Rapid Prototyping Journal 20, no. 6 (October 20, 2014): 551–58. http://dx.doi.org/10.1108/rpj-08-2011-0086.

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Purpose – The purpose of this paper was to investigate the feasibility on design and production of a three-dimensional honeycomb based on selective laser melting (SLM) technique for use in aeronautical application. Design/methodology/approach – Various polyhedrons were investigated using their mechanical property, i.e. strain energy density (SED), by means of finite element (FE) analysis for the suitability of use in aerospace application; the highest SED polyhedron was selected as a candidate polyhedron. From the FE analysis, the truncated octahedron (three-dimensional honeycomb) structure was considered to be the potential candidate. Polyhedron size and beam thickness of the open-cellular three-dimensional honeycomb structure were modelled and analysed to observe how the geometric properties influence the stiffness of the structure. One selected model of open-cellular honeycomb (unit cell size: 2.5 mm and beam thickness: 0.15 mm) was fabricated using SLM. The SLM prototypes were assessed by their mechanical properties, including compressive strength, stiffness and strength per weight ratio. To investigate the feasibility in production of airfoil section sandwich structure, NACA 0016 airfoil section with three-dimensional honeycomb core was constructed and also fabricated using SLM. Findings – According to the result, the three-dimensional honeycomb has elastic modulus of 63.18 MPa and compressive strength of 1.1 MPa, whereas strength per weight ratio is approximately 5.0 × 103 Nm/kg. The FE result presented good agreement to the mechanical testing result. The geometric parameter of the three-dimensional honeycomb structure influences the stiffness, especially the beam thickness, i.e. increase of beam thickness obviously produces the stiffer structure. In addition, the sandwich structure of airfoil was also successfully manufactured. Originality/value – This work demonstrated the production of sandwich structure of airfoil using SLM for aeronautical engineering. This investigation has shown the potential applications of the three-dimensional structure, e.g. aircraft interior compartment components and structure of unmanned aerial vehicles.

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Meng, Li Qing, Shi Zhe Chen, Yan Wu, and Xue Feng Shu. "Failure Behaviour of Sandwich Beam Subjected to Projectile Impact." Advanced Materials Research 183-185 (January 2011): 2143–47. http://dx.doi.org/10.4028/www.scientific.net/amr.183-185.2143.

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Aerodynamic gun impact test is carried out to investigate sandwich beam with metallic skin and Nomex honeycomb core damage mechanism and failure behaviour. Details of the deformation and damage progression within the sandwich beam are observed in particular. The comparisons between the two kinds of specimen with different thickness skins clearly show that the difference in the impact energy consumed in global bending deformation and the localized indentation. Theoretical elastic bending stiffness of the sandwich beam with thicker skins is approximately 2.26 times greater than that of sandwich beam with thinner skins.

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LIU, J., Y. S. CHENG, R. F. LI, and F. T. K. AU. "A SEMI-ANALYTICAL METHOD FOR BENDING, BUCKLING, AND FREE VIBRATION ANALYSES OF SANDWICH PANELS WITH SQUARE-HONEYCOMB CORES." International Journal of Structural Stability and Dynamics 10, no. 01 (March 2010): 127–51. http://dx.doi.org/10.1142/s0219455410003361.

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A semi-analytical method for bending, global buckling, and free vibration analyses of sandwich panels with square-honeycomb cores is presented. The discrete geometric nature of the square-honeycomb core is taken into account by treating the core sheets as thin beams and the sandwich panel as composite structure of plates and beams with proper displacement compatibility. Based on the classical model of sandwich panels, the governing equations of motion of the discrete structure are derived using Hamilton's principle. Closed-form solutions are developed for bending, global buckling, and free vibration of simply supported square-honeycomb sandwich panels by employing Fourier series and the Galerkin approach. Results from the proposed method agree well with available results in the literature and those from detailed finite element analysis. The effects of various geometric parameters of the sandwich panel on its behavior are investigated. The present method provides an efficient way of analysis and optimization of sandwich panels with square-honeycomb cores.

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Pourriahi, Vahid, Mohammad Heidari-Rarani, and Amir Torabpour Isfahani. "Influence of geometric parameters on free vibration behavior of an aluminum honeycomb core sandwich beam using experimentally validated finite element models." Journal of Sandwich Structures & Materials 24, no. 2 (December 10, 2021): 1449–69. http://dx.doi.org/10.1177/10996362211053633.

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The hexagonal honeycomb core sandwich panels used in the satellite structure are subjected to severe vibration during launch. Therefore, the amounts of natural frequencies of these panels are of great importance for design engineers. Three-dimensional finite element modeling of the core considering all geometric parameters (i.e., a high-fidelity model) to achieve accurate results is not cost-effective. The honeycomb core is traditionally equivalent to a homogenized continuum core (i.e., a low-fidelity model) using simple analytical relations with ignoring the adhesive layer at the double cell-walls and radius of inclined cell-wall curvature. In this study, analytical formulations are first presented for the prediction of the equivalent elastic properties of a hexagonal aluminum honeycomb with considering all geometric parameters including adhesive layer thickness, cell-wall thickness, inclined cell-wall length, radius of inclined cell-wall curvature at the intersection, internal cell-wall angle, and honeycomb height. Then, two aluminum honeycomb core sandwich beams with free-free boundary conditions are modeled and analyzed in Abaqus finite element software, one with 3D high-fidelity core and the other with 3D low-fidelity core. In order to validate the results of the equivalent model, the modal analysis test was performed and the experimental natural frequencies were compared. The obtained results show a good agreement between the 3D low-fidelity and high-fidelity finite element models and experimental results. In addition, the influence of the above-mentioned geometric parameters has been investigated on the natural frequencies of a sandwich beam. [Formula: see text]

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Safaei, Babak, Emmanuel Chukwueloka Onyibo, Mehmet Goren, Kamila Kotrasova, Zhicheng Yang, Samaneh Arman, and Mohammed Asmael. "FREE VIBRATION INVESTIGATION ON RVE OF PROPOSED HONEYCOMB SANDWICH BEAM AND MATERIAL SELECTION OPTIMIZATION." Facta Universitatis, Series: Mechanical Engineering 21, no. 1 (April 10, 2023): 031. http://dx.doi.org/10.22190/fume220806042s.

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In this paper, free vibration, modal and stress state analyses of honeycomb sandwich structures with different boundary conditions was investigated and major factors affecting the sandwich frequencies and stiffness due to material or parameter changes were determined. The representative volume element (RVE) method used in this work were analytically and numerically validated by comparing the obtained results to those available in literature. Firstly, unit cell method was used to capture the entire effects of different parameters on the free vibration of honeycomb sandwich structure in ANSYS. This study analyzed the natural frequencies of honeycomb sandwich structures with different core materials combination. The effects of foil thickness, boundary conditions, materials selection, density and presence of crack on sandwich structure were taken into consideration and examined. The proposed core had an inbuilt shaped reinforcement with different materials for effective resonance, fatigue and deformation resistance at much higher frequency.

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CHEN, LI-MING, MING-JI CHEN, YONG-MAO PEI, YI-HUI ZHANG, and DAI-NING FANG. "OPTIMAL DESIGN OF SANDWICH BEAMS WITH LIGHTWEIGHT CORES IN THREE-POINT BENDING." International Journal of Applied Mechanics 04, no. 03 (September 2012): 1250033. http://dx.doi.org/10.1142/s1758825112500330.

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Being widely used in engineering, the optimization of sandwich beams to achieve greater stiffness-to-weight ratio is of great research interest. In this paper, the optimization process was carried to obtain minimum weight designs in three-point bending based on prescribed stiffness index. Results indicate that honeycomb-cored sandwich beams possess smaller minimum weight index in comparison with metal foam-cored beams. In addition, failure mechanisms of the optimized designs were also investigated to reveal that the sandwich-cored beams were more prone to face wrinkling than metal foam-cored beams. In the optimization process, five different core topologies and four different parent materials were investigated under a given load index. It was found for low prescribed load values where bending is dominant, unidirectional lattice composite sandwich beams bear loads more efficiently than steel cored beams. However, the primary mode of failure for high prescribed load index is core shear, thus implying no significant advantage in lattice composite sandwich beams over other materials. Comparing the different materials, that laminate lattice composite sandwich beams possess the best bending performance for varying levels of prescribed load index, making it suitable for applications in the aerospace field.

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Wang, B., and M. Yang. "Damping of honeycomb sandwich beams." Journal of Materials Processing Technology 105, no. 1-2 (September 2000): 67–72. http://dx.doi.org/10.1016/s0924-0136(00)00564-1.

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Seo, Sung Il, Jung Seok Kim, Se Hyun Cho, and Seong Chul Kim. "Manufacturing and Mechanical Properties of a Honeycomb Sandwich Panel." Materials Science Forum 580-582 (June 2008): 85–88. http://dx.doi.org/10.4028/www.scientific.net/msf.580-582.85.

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Sandwich panels are widely used in the main structure of aircrafts and ships because of their lightweight, high strength, stiffness, durability, and corrosion resistance. The present paper proposes a manufacturing process of a carbody structure of rolling stock using a composite honeycomb sandwich panel. The panel is made of carbon/epoxy composite faces and an aluminum core. The faces bear bending loads and the core shearing load. A product is manufactured by lay-up of composite material on the mold of the product in final dimensions; then cured in a large autoclave for obtaining one body of a structure. In this study, in order to evaluate the mechanical properties of the honeycomb sandwich panel, tensile test, compressive test, flexural test and shear test of the face in honeycomb sandwich panel were performed. Impact test for the honeycomb sandwich panel was also carried out. Moreover, end compression test was conducted. The results show that the composite honeycomb sandwich panel has good properties for the carbody structure of rolling stock.

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He, Wei. "Ultralight micro-perforated sandwich panel with double-layer hierarchical square honeycomb core for broadband sound absorption." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 6 (August 1, 2021): 83–90. http://dx.doi.org/10.3397/in-2021-1129.

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The micro-perforated panel (MPP) has only one sound absorption peak, and the sound absorption performance is poor in the wide frequency range. Besides, the stiffness and strength of MPP are insufficient, so it can not bear the external load. In this study, double layers of hierarchical square honeycomb are placed within the air-back cavity of MPP to produce a sandwich structure. On the one hand, hierarchical honeycombs divide the air-back cavity into several sub-cavities. The perforations on the panel together with the sub-cavities form a series-parallel system of Helmholtz resonators. The sound absorption curve of the structure has multiple peaks and the half-absorption bandwidth is extensively widened. On the other hand, the hierarchical honeycomb with excellent load-bearing properties can strongly support the MPP to resist external loads. This new structure possesses both sound absorption and load bearing capabilities, and has practical application value in the noise reduction of high-speed trains and civil aircraft. Through theoretical and simulation analysis, the sound absorption performance of the structure is systematically studied and the influence of key parameters is quantified, providing guidance for the design of noise reduction materials.

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Gopalakrishnan, KC, R. Ramesh Kumar, and S. Anil Lal. "Cohesive zone modeling of coupled buckling – Debond growth in metallic honeycomb sandwich structure." Journal of Sandwich Structures & Materials 14, no. 6 (September 19, 2012): 679–93. http://dx.doi.org/10.1177/1099636212460537.

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Buckling-induced skin–core debond growth in honeycomb sandwich cantilever beam is demonstrated using a cohesive zone model. The input parameters for the analysis are interfacial bond strength, mode I and mode II interfacial fracture toughness values, obtained from flatwise tension tests, drum-peel tests and three-point end notch flexure tests, respectively. Debonded honeycomb specimens are tested and the acoustic emission technique was used to observe the initiation of the debond growth. The load-displacement response from the cohesive zone model model shows a good agreement with the experimental results. The conventional analysis without cohesive zone model overestimates failure load by 56%. Cohesive zone model is able to predict the coupled debond growth and buckling failure in honeycomb sandwich structures.

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Saraswathy, B., R. Ramesh Kumar, and Lalu Mangal. "Dynamic Analysis of Honeycomb Sandwich Beam with Multiple Debonds." ISRN Mechanical Engineering 2012 (January 16, 2012): 1–7. http://dx.doi.org/10.5402/2012/826952.

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Analytical formulation for the evaluation of frequency of CFRP sandwich beam with debond, following the split beam theory, generally underestimates the stiffness, as the contact between the honeycomb core and the skin during vibration is not considered in the region of debond. The validation of the present analytical solution for multiple-debond size is established through 3D finite element analysis, wherein geometry of honeycomb core is modeled as it is, with contact element introduced in the debond region. Nonlinear transient analysis is followed by fast Fourier transform analysis to obtain the frequency response functions. Frequencies are obtained for two types of model having single debond and double debond, at different spacing between them, with debond size up to 40% of beam length. The analytical solution is validated for a debond length of 15% of the beam length, and with the presence of two debonds of same size, the reduction in frequency with respect to that of an intact beam is the same as that of a single-debond case, when the debonds are well separated by three times the size of debond. It is also observed that a single long debond can result in significant reduction in the frequencies of the beam than multiple debond of comparable length.

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Xu, Bo Hao, Shuai Wang, Kai Fa Zhou, Wen Yi Ma, and Nan Sun. "Large Torsion Deformation: Centrosymmetric Reentrant Honeycomb." Applied Mechanics and Materials 904 (January 4, 2022): 17–25. http://dx.doi.org/10.4028/www.scientific.net/amm.904.17.

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There exist some problems in the crash box and anti-collision beam sandwich structure, such as monotone deformation pattern and uneconomical energy absorption performance. In order to raise the deformation capacity and energy absorption performance of sandwich structure, centrosymmetric reentrant honeycomb (CRH) and hexagonal centrosymmetric reentrant honeycomb (HCRH) are proposed based on auxetic reentrant honeycomb (ARH) in this work. Based on HCRH, four kinds of transverse combination structures and two kinds of longitudinal combination structures are obtained. The results of specific energy absorption show that the energy absorption capacity of the angular contact homodromous combination structure (ACOC) is about 3 times that of the other three transverse combination structures. Compared with longitudinal heterodromous combination structure (LHEC), the energy absorption capacity of longitudinal homodromous combination structure (LHOC) is improved by 72.7%.

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Cheng, Shi, Pizhong Qiao, Fangliang Chen, Wei Fan, and Zhende Zhu. "Free vibration analysis of fiber-reinforced polymer honeycomb sandwich beams with a refined sandwich beam theory." Journal of Sandwich Structures & Materials 18, no. 2 (December 30, 2015): 242–60. http://dx.doi.org/10.1177/1099636215619841.

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Silva, Hugo Miguel, and José Filipe Bizarro de Meireles. "Effective Mechanical Behavior of Sandwich Beams under Uncoupled Bending and Torsion Loadings." Applied Mechanics and Materials 590 (June 2014): 58–62. http://dx.doi.org/10.4028/www.scientific.net/amm.590.58.

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Sandwich geometries, mainly panels and beams are widely used in several transportation industries, namely aerospace, aeronautic and automotive. Sandwich geometries are known for their advantages in structural applications: high specific stiffness, low weight, and possibility of design optimization prior to manufacturing. This study aims to know the influence of the number of reinforcements (ribs), and of the thickness on the mechanical behavior of sandwich panels subjected to bending and torsion loads separately. In this study, 3 geometries are compared: simple web-core beam, corrugated core, and honeycomb core. The last 2 are asymmetric, due to the use of odd number of ribs. The influence of the geometry on the results is discussed, by means of a parameter that establishes a relation between the stiffness behavior and the mass of the object. It is shown that the all relations are non-linear, despite the elastic nature of the analysis, by means of the application of loads with low intensity.

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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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Sadiq, Sadiq E., Muhsin J. Jweeg, and Sadeq H. Bakhy. "Strength Analysis of an Aircraft Sandwich Structure with a Honeycomb Core: Theoretical and Experimental Approaches." Engineering and Technology Journal 39, no. 1A (January 25, 2021): 153–66. http://dx.doi.org/10.30684/etj.v39i1a.1722.

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In this paper, the strength of aircraft sandwich structure with honeycomb core under bending load was evaluated theoretically and experimentally based on failure mode maps. A failure mode map for the loading under three-point bending was constructed theoretically to specify the failure modes and corresponding load. Three point bending test for aluminum honeycomb sandwich beam has been achieved to measure the peak load and maximum deflection. The obtained results elucidated a good agreement between the theoretical solutions and experimental tests, where the error ratio was not exceeded 12%. The core height, the cell size and the cell wall thickness were selected to explore the effect of honeycomb parameters on the strength of sandwich structure. In order to obtain the optimum solution of peak load and maximum deflection and energy absorption, Response Surface Methodology (RSM) was used. Results showed that the maximum bending load, minimum deflection, and maximum energy absorption were found at 25 mm core height, 10 mm size cell and 1 mm cell wall thickness. The optimal value of maximum bending load, minimum deflection and maximum energy absorption were 1975.3415 N, 1.0402 mm and 1.0229 J respectively.

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Belingardi, G., P. Martella, and L. Peroni. "Fatigue analysis of honeycomb-composite sandwich beams." Composites Part A: Applied Science and Manufacturing 38, no. 4 (April 2007): 1183–91. http://dx.doi.org/10.1016/j.compositesa.2006.06.007.

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Chenini, I., R. Nasri, C. Mrad, and Y. Abdelli. "Kinematics effect on honeycomb sandwich beams vibration." Mechanics & Industry 18, no. 3 (2017): 302. http://dx.doi.org/10.1051/meca/2016039.

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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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Ijaz, Hassan, Waqas Saleem, Muhammad Zain-ul-Abdein, Tarek Mabrouki, Saeed Rubaiee, and Abdullah Salmeen Bin Mahfouz. "Finite Element Analysis of Bend Test of Sandwich Structures Using Strain Energy Based Homogenization Method." Advances in Materials Science and Engineering 2017 (2017): 1–10. http://dx.doi.org/10.1155/2017/8670207.

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The purpose of this article is to present a simplified methodology for analysis of sandwich structures using the homogenization method. This methodology is based upon the strain energy criterion. Normally, sandwich structures are composed of hexagonal core and face sheets and a complete and complex hexagonal core is modeled for finite element (FE) structural analysis. In the present work, the hexagonal core is replaced by a simple equivalent volume for FE analysis. The properties of an equivalent volume were calculated by taking a single representative cell for the entire core structure and the analysis was performed to determine the effective elastic orthotropic modulus of the equivalent volume. Since each elemental cell of the hexagonal core repeats itself within the in-plane direction, periodic boundary conditions were applied to the single cell to obtain the more realistic values of effective modulus. A sandwich beam was then modeled using determined effective properties. 3D FE analysis of Three- and Four-Point Bend Tests (3PBT and 4PBT) for sandwich structures having an equivalent polypropylene honeycomb core and Glass Fiber Reinforced Plastic (GFRP) composite face sheets are performed in the present study. The authenticity of the proposed methodology has been verified by comparing the simulation results with the experimental bend test results on hexagonal core sandwich beams.

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Zaoutsos, S. P. "Mechanical response and strength characteristics of aluminum honeycomb sandwich panels for infrastructure engineering." IOP Conference Series: Materials Science and Engineering 1201, no. 1 (November 1, 2021): 012046. http://dx.doi.org/10.1088/1757-899x/1201/1/012046.

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Abstract The use of aluminium sandwich panels has been increased in a certain number of engineering applications from infrastructure systems and transportation to aircraft and naval engineering. Due to their structural efficiency these materials are ideal for applications where ratio of strength to weight is of crucial importance. In the current study the investigation of the strength characteristics of aluminium sandwich panels with aluminium honeycomb core and different types of skins is performed using both analytical models and experimental procedures. A series of strength tests such as tension, shear, three point bending and double cantilever beam were conducted on aluminium honeycomb-cored sandwich panel specimens with five different skins in order to examine the mode of failure and the mechanical behaviour of the structural elements. The experimental findings are compared to theoretical values while an attempt for the explanation of the mechanisms leading to failure such as buckling, delamination or debonding between core and skins is performed. The results occurring from the study are very useful for the enhancement of the mechanical behaviour of sandwich constructions, thus more intensive work must be carried out in order to understand the physical mechanisms leading to strength characteristics of sandwich panels.

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Selvam, Vignesh, Vijay Shankar Sridharan, and Sridhar Idapalapati. "Static and Fatigue Debond Resistance between the Composite Facesheet and Al Cores under Mode-1 in Sandwich Beams." Journal of Composites Science 6, no. 2 (February 7, 2022): 51. http://dx.doi.org/10.3390/jcs6020051.

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The debonding toughness between unidirectional glass fiber reinforced polymer face sheets and cellularic cores of sandwich structures is experimentally measured under static and fatigue loading conditions. The effect of various core geometries, such as regular honeycomb and closed-cell foams of two relative densities on the adhesive interfacial toughness is explored using the single cantilever beam (SCB) testing method. The steady-state crack growth measurements are used to plot the Paris curves. The uniformity of adhesive filleting and the crack path was found to affect the interfacial toughness. The static Mode-1 interfacial toughness of high-density foam cores was witnessed to be maximal, followed by low-density honeycomb, high-density honeycomb, and low-density foam core. Similarly, the fatigue behavior of the low-density honeycomb core has the lowest crack growth rates compared to the other samples, primarily due to uniform adhesive filleting.

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Bareille, O., and M. N. Ichchou. "Wave propagation in composite structures." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 225, no. 3 (December 15, 2009): 639–48. http://dx.doi.org/10.1243/09544062jmes1971.

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Dynamic behaviour of honeycomb-core composite structures forms the framework of this article. The wave numbers of propagative waves are the elements of comparison between a numerical method (wave finite-element method) and an experimental identification technique (inhomogeneous wave correlation). The numerical method is based on the description of the dynamics of periodic waveguides. The experimental technique uses a matching criterion with the measured displacement field to obtain the corresponding wave numbers for a wave-based description of the displacement. Both approaches are applied to a sandwich composite beam with a honeycomb core. They seem to be in quite good accordance with analytical results for the flexural wave number.

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Kardomateas, G. A. "Wrinkling of Wide Sandwich Panels∕Beams With Orthotropic Phases by an Elasticity Approach." Journal of Applied Mechanics 72, no. 6 (November 4, 2004): 818–25. http://dx.doi.org/10.1115/1.1978919.

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There exist many formulas for the critical compression of sandwich plates, each based on a specific set of assumptions and a specific plate or beam model. It is not easy to determine the accuracy and range of validity of these rather simple formulas unless an elasticity solution exists. In this paper, we present an elasticity solution to the problem of buckling of sandwich beams or wide sandwich panels subjected to axially compressive loading (along the short side). The emphasis on this study is on the wrinkling (multi-wave) mode. The sandwich section is symmetric and all constituent phases, i.e., the facings and the core, are assumed to be orthotropic. First, the pre-buckling elasticity solution for the compressed sandwich structure is derived. Subsequently, the buckling problem is formulated as an eigen-boundary-value problem for differential equations, with the axial load being the eigenvalue. For a given configuration, two cases, namely symmetric and anti-symmetric buckling, are considered separately, and the one that dominates is accordingly determined. The complication in the sandwich construction arises due to the existence of additional “internal” conditions at the face sheet∕core interfaces. Results are produced first for isotropic phases (for which the simple formulas in the literature hold) and for different ratios of face-sheet vs core modulus and face-sheet vs core thickness. The results are compared with the different wrinkling formulas in the literature, as well as with the Euler buckling load and the Euler buckling load with transverse shear correction. Subsequently, results are produced for one or both phases being orthotropic, namely a typical sandwich made of glass∕polyester or graphite∕epoxy faces and polymeric foam or glass∕phenolic honeycomb core. The solution presented herein provides a means of accurately assessing the limitations of simplifying analyses in predicting wrinkling and global buckling in wide sandwich panels∕beams.

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Kumar, Sathish, Leping Feng, and Ulf Orrenius. "Predicting the Sound Transmission Loss of Honeycomb Panels using the Wave Propagation Approach." Acta Acustica united with Acustica 97, no. 5 (September 1, 2011): 869–76. http://dx.doi.org/10.3813/aaa.918466.

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The sound transmission properties of sandwich panels can be predicted with sufficient degree of accuracy by calculating the wave propagation properties of the structure. This method works well for sandwich panels with isotropic cores but applications to panels with anisotropic cores are hard to find. Honeycomb is an example of anisotropic material which when used as a core, results in a sandwich panel with anisotropic properties. In this paper, honeycomb panels are treated as being orthotropic and the wavenumbers are calculated for the two principle directions. These calculated wavenumbers are validated with the measured wavenumbers estimated from the resonance frequencies of freely hanging honeycomb beams. A combination of wave propagation and standard orthotropic plate theory is used to predict the sound transmission loss of honeycomb panels. These predictions are validated through sound transmission measurements. Passive damping treatment is a common way to reduce structural vibration and sound radiation, but they often have little effect on sound transmission. Visco-elastic damping with a constraining layer is applied to two honeycomb panels with standard and enhanced fluid coupling properties. This enhanced fluid coupling in one of the test panels is due to an extended coincidence range observed from the dispersion curves. The influence of damping treatments on the sound transmission loss of these panels is investigated. Results show that, after the damping treatment, the sound transmission loss of an acoustically bad panel and a normal panel are very similar.

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Burman, Magnus, and Dan Zenkert. "Fatigue of Undamaged and Damaged Honeycomb Sandwich Beams." Journal of Sandwich Structures & Materials 2, no. 1 (January 2000): 50–74. http://dx.doi.org/10.1177/109963620000200103.

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Southward, T., G. D. Mallinson, K. Jayaraman, and D. Horrigan. "Buckling of Disbonds in Honeycomb-core Sandwich Beams." Journal of Sandwich Structures & Materials 10, no. 3 (May 2008): 195–216. http://dx.doi.org/10.1177/1099636207081346.

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Pan, Shi-Dong, Lin-Zhi Wu, Yu-Guo Sun, and Zheng-Gong Zhou. "Fracture test for double cantilever beam of honeycomb sandwich panels." Materials Letters 62, no. 3 (February 2008): 523–26. http://dx.doi.org/10.1016/j.matlet.2007.05.084.

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Li, Zhendong, Zhonggang Wang, Xinxin Wang, and Wei Zhou. "Bending behavior of sandwich beam with tailored hierarchical honeycomb cores." Thin-Walled Structures 157 (December 2020): 107001. http://dx.doi.org/10.1016/j.tws.2020.107001.

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Shahdin, Amir, Joseph Morlier, Laurent Mezeix, Christophe Bouvet, and Yves Gourinat. "Evaluation of the Impact Resistance of Various Composite Sandwich Beams by Vibration Tests." Shock and Vibration 18, no. 6 (2011): 789–805. http://dx.doi.org/10.1155/2011/259295.

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Impact resistance of different types of composite sandwich beams is evaluated by studying vibration response changes (natural frequency and damping ratio). This experimental works will help aerospace structural engineer in assess structural integrity using classification of impact resistance of various composite sandwich beams (entangled carbon and glass fibers, honeycomb and foam cores). Low velocity impacts are done below the barely visible impact damage (BVID) limit in order to detect damage by vibration testing that is hardly visible on the surface. Experimental tests are done using both burst random and sine dwell testing in order to have a better confidence level on the extracted modal parameters. Results show that the entangled sandwich beams have a better resistance against impact as compared to classical core materials.

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Sun, Wei, Junyi Xiao, Xuanwei Hu, Baoxin Hao, Huan Zhang, Peng Zhang, Tianhe Gao, and Kuo Tian. "Study on Bearing Capacity of Honeycomb Sandwich Structure Embedded Parts." Journal of Composites Science 7, no. 7 (July 8, 2023): 281. http://dx.doi.org/10.3390/jcs7070281.

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In the composite structure of spacecraft, the honeycomb sandwich structure is the basic bearing component used to bear and transmit loads. To explore the influencing factors on the bearing capacity of honeycomb sandwich structures, this study combines local tests and speckle measurement systems to conduct tensile tests on 10 test specimens with different parameters. Firstly, a comprehensive assessment was conducted on the accuracy of the loading and measurement system, the rationality of the testing method, and the mechanical properties of the test piece. It was found that the maximum measurement error of the speckle measurement system did not exceed 0.01 mm, and the differences between the yield load and failure load measured using different inner diameters of the compression ring were 0.15% and 3.84%, respectively. This indicates that the measurement system is accurate and that the influence of the inner diameter of the compression ring can be ignored. Moreover, it was found that considering the accuracy retention ability of the structure under load, the allowable load of the embedded parts is about 90% of the yield load. Finally, the data of specimens with different parameters were compared and it was found that the strength of the honeycomb sandwich structure is directly proportional to the thickness of the skin, the density of the honeycomb core cells, and the size of the embedded parts.

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Smardzewski, Jerzy. "Elastic properties of cellular wood panels with hexagonal and auxetic cores." Holzforschung 67, no. 1 (January 1, 2013): 87–92. http://dx.doi.org/10.1515/hf-2012-0055.

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Abstract Light cellular wood panels have been gaining increasing interest among furniture manufacturers, but only a few articles can be found dealing with modeling of mechanical properties of cellular wood panels with a paper honeycomb core inside. The present paper intends to fill this gap, and thus, the elastic properties of cellular wood panels with paper honeycomb of hexagonal and auxetic cells were evaluated. Analytical models have been employed by comparison of experimental data with those obtained by numerical calculations. The cores of the examined cellular wood panels exhibited strong orthotropic properties. Results of numerical calculations of sandwich beam deflections corroborated their satisfactory conformity. The results of laboratory measurements proved the correctness of the determined elastic constants.

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Lu, Jie, Guang Ping Zou, and Bao Jun Liu. "Experimental Investigation of Damage Characteristics in Steel Honeycomb Sandwich Beams." Materials Science Forum 675-677 (February 2011): 685–88. http://dx.doi.org/10.4028/www.scientific.net/msf.675-677.685.

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Honeycomb sandwich structures are generally designed to carry flexural loads. However, mechanical properties can be influenced by accidental impacts, or service conditions. Thus a nondestructive detection testing is desired for them. In contrast to many conventional nondestructive evaluation (NDE) techniques, acoustic emission (AE) technique permits continuous damage inspection, classification and identification of failure modes in real time. In this work the fracture process of steel honeycomb sandwich beams has been investigated by in-situ AE technique. Pre-cracks were made both for L-direction and W-direction specimens subjected to three-points bending loads. Damage initiation sites were observed in the vicinity of the crack tip. A series of curves among the AE hits, AE amplitude, AE energy and loading time were obtained. Damage characteristics were discussed based on the above parameters. The results indicate AE characteristic parameters can reflect the damage and failure process of specimens. A good agreement was found between the experimental and analytical results.

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Paixão, Nathália Mello Mascarenhas, and Antônio Ferreira Ávila. "Finite element simulations of auxetic structure combined with honeycomb using unidirectional continuous carbon fiber composite properties." Journal of Engineering and Exact Sciences 9, no. 1 (February 20, 2023): 15430–01. http://dx.doi.org/10.18540/jcecvl9iss1pp15430-01e.

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Metamaterials have been studied over the last few decades, as they may exhibit peculiar mechanical behavior. An example is the re-entrant auxetic structure, which can display negative Poisson ratio. Likewise, the honeycomb structure has also been widely used, mainly in sandwich-panels. Despite several studies including these geometries, the use of composite as raw material has not been reported in the literature, so this work aimed to perform finite element simulations of combined honeycomb and re-entrant auxetic structures using properties of continuous, unidirectional carbon fiber composite in epoxy matrix. For this, three types of modeling were used: beam, shell and solid and two sets of constraints were applied for each model. By analyzing the total deformation profiles obtained for these three models, it was possible to observe that both beam and shell modeling results were close to the three-dimensional modeling when applying a vertical compression displacement, in which beam modeling showed a better approximation. On the other hand, when applying the compression displacement horizontally, the beam modeling proved to be inadequate, while the shell modeling presented values close to the solid modeling. Therefore, it is concluded that it is possible to model similar structures using shell element instead of solid element.

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Journal articles on the topic 'Honeycomb sandwiched beam'

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