Relevant bibliographies by topics / Composite Honeycomb Sandwich Panels

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Composite Honeycomb Sandwich Panels'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Composite Honeycomb Sandwich Panels"

1

Im, Kwang-Hee, Sun-Kyu Kim, Jong-An Jung, Young-Tae Cho, Yong-Deuck Woo, and Chien-Ping Chiou. "NDE Terahertz Wave Techniques for Measurement of Defect Detection on Composite Panels of Honeycomb Sandwiches." Electronics 9, no. 9 (August 21, 2020): 1360. http://dx.doi.org/10.3390/electronics9091360.

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Terahertz wave (T-ray) technologies have become a popular topic in scientific research over the last two decades, and can be utilized in nondestructive evaluation (NDE) techniques. This study suggests an optimal scanning technique method for honeycomb sandwich composite panels, where skins were utilized with two different skins, namely, carbon fiber-reinforced plastic (CFRP) skin and glass fiber-reinforced plastic (GFRP) skin, as layers of the panel surfaces. Foreign objects were artificially inserted between the skins and honeycomb cells in the honeycomb sandwich composite panels. For this experiment, optimal T-ray scanning methods were performed to examine defects based on the angle between the one-ply thin fiber skin axis and the angle of the electric field (E-field) according to the amount of conductivity of the honeycomb sandwich composite panels. In order to confirm the fundamental characteristics of the terahertz waves, the refractive index values of the GFRP composites were experimentally obtained and analyzed, with the data agreeing with known solutions. Terahertz waves (T-rays) were shown to have limited penetration in honeycomb sandwich composite panels when utilized with a skin of carbon fibers. Therefore, T-rays were found to interact with the electrical conductivity and electric field direction of honeycomb sandwich composite panels with glass fiber skins. The T-ray images were obtained regardless of the electric field direction and the fiber direction. In the honeycomb sandwich composite panels with carbon fiber skins, the T-ray images with higher signal-to-noise (S/N) ratios depended on the scanning angle between the angle of the carbon fiber and the angle of the electric field. Thus, the angle of optimum detection measurement was confirmed to be 90° between the E-field and the fiber direction, particularly when using a carbon fiber skin.
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SKOVAJSA, MICHAL, FRANTISEK SEDLACEK, and MARTIN MRAZEK. "DETERMINATION OF MECHANICAL PROPERTIES OF COMPOSITE SANDWICH PANEL WITH ALUMINIUM HONEYCOMB CORE." MM Science Journal 2021, no. 6 (December 15, 2021): 5353–59. http://dx.doi.org/10.17973/mmsj.2021_12_2021132.

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This paper deal with comparison of mechanical properties of composite sandwich panel with aluminium honeycomb core which is determined by experimental measurement, analytic calculation and numerical simulation. The goal was to compared four composite sandwich panels. The composite sandwich panels were made of two different aluminium honeycomb cores with density 32 and 72 kg.m-3 and two different layup of skin with 4 and 5 layers. The comparison was performed on a three-point bend test with support span 400 mm. This paper confirms the possibility of a very precise design of a composite sandwich panel with an aluminium honeycomb core using analytical calculation and numerical simulation.
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Marsono, Marsono, Sarah Fauziyyah Hanifa, and Faizal Akbar. "Pembuatan dan Pengujian Panel Honeycomb Sandwich dengan Inti Berbentuk Gelombang Berbahan Komposit Serat Bambu." Jurnal Rekayasa Hijau 5, no. 2 (July 29, 2021): 165–77. http://dx.doi.org/10.26760/jrh.v5i2.165-177.

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ABSTRAKDalam penelitian ini, komposit serat bambu dibuat menjadi panel struktur honeycomb sandwich dan diuji untuk mengukur kemungkinan pemanfaatannya sebagai bahan untuk membuat sudu turbin angin sumbu vertical. Honeycomb sanwich serat bambu yang dibuat memiliki inti (core) yang berbentuk gelombang sinus pada arah memanjang panel. Sebagai pengikat pada komposit ini digunakan resin polyester. Panel honeycomb sandwich yang dibuat memiliki panjang 500mm dan lebar 200mm, sedangkan tebal panel dibuat dengan dua variasi, yaitu dengan tinggi inti honeycomb 12mm dan 17mm. Panel honeycomb sandwich ini diuji dengan uji bending untuk mendapatkan angka kekuatan lentur (flexural strength) dan angka kekakuan (stiffness). Dari tiga panel yang dibuat identik untuk masih-masing ketinggian inti honeycomb, diperoleh angka kekuatan lentur dan kekakuan terbesar pada panel dengan ketinggian inti honeycomb17mm, yaitu dengan angka kekuatan lentur 0,91kg/mm2 dan angka kekakuan 11,35kg/mmKata kunci: honeycomb sandwich, komposit serat bambu,gelombang sinus,kekuatan lentur, kekakuan. ABSTRACTIn this research, bamboo fiber composite are made into honeycomb sandwich structure panel and to be tested for its ability as a material for vertical axis wind turbine blades. Bamboo fiber honeycomb sandwich had a sinusoidal-shaped core in the longitudinal direction of the panel. Polyester resin was used as a binder on this composite. The honeycomb panels that have been made have a length of 500mm and a width of 200mm. The thickness of the panels was made of two variations, which was has 12mm and 17mm honeycomb core-height. The honeycomb sandwich panel was tested by bending test to obtain flexural strength and stiffness. From the three panels that have been made in identical dimension for each honeycomb core-height, the highest flexural strength and stiffness was obtained in the specimen with the honeycomb core-height of 17mm, with a flexural strength of 0,91kg/mm2 and astiffness of 11,35kg/mm. Keywords: honeycomb sandwich, bamboo fiber composite, sinusoidal wave, flexurall strength, stiffness.
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Shi, Shanshan, Bingzhi Chen, and Zhi Sun. "Equivalent properties of composite sandwich panels with honeycomb–grid hybrid core." Journal of Sandwich Structures & Materials 22, no. 6 (July 30, 2018): 1859–78. http://dx.doi.org/10.1177/1099636218789615.

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Combining the complementary properties of honeycomb cores and grid cores, a composite sandwich panel with honeycomb–grid hybrid core was proposed to enhance the structural performance of composite sandwich panels. However, important gaps remain in calculating the structural performance of the composite sandwich panels. In this paper, an equivalent stiffness model was proposed to analytically estimate the stiffness matrix of composite sandwich panels with honeycomb–grid hybrid core. The reliability and accuracy of the equivalent stiffness model were verified by experimental measurements from three-point bending tests. Furthermore, the effects of face-sheet thickness, core height, grid spacing, rib width and material properties on structural stiffness were investigated for the design of sandwich structures with hybrid core. The parameter studies demonstrated that core height had the most significant influence on the specific bending stiffness, while grid spacing was most important for specific in-plane stiffness of sandwich panels with carbon-fiber grid. Moreover, using carbon-fiber grid, although increases manufacturing cost, could further enhance the specific stiffness.
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Wang, Yongwei, Deng Zhou, Gang Yan, and Zhuangjie Wang. "Experimental and Numerical Study on Residual Strength of Honeycomb Sandwich Composite Structure after Lightning Strike." Aerospace 9, no. 3 (March 14, 2022): 158. http://dx.doi.org/10.3390/aerospace9030158.

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Honeycomb sandwich composite structures are widely used in various aircraft structures due to their unique performance. However, honeycomb sandwich composite structures are prone to lightning damage that threatens the structure safety. Therefore, it is necessary to assess the residual mechanical properties of honeycomb sandwich composite structures after a lightning strike. In this study, simulated lightning strike tests were first conducted for honeycomb sandwich panels with and without carbon nanotube film (CNTF) to obtain different damage scenarios and study the protection effect of CNTF. Then, the residual compressive strength of the panels with lightning strike damage was predicted using a progressive damage analysis method and verified with the experimental results. It was found that the numerical prediction results agree with the experimental results. The size and extent of lightning damage have an important effect on the compression damage mode of honeycomb sandwich panel with closed edges.
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Yang, Xiao Jun, Qing Shan Lan, and Yu Ning Zhong. "Buckling Analysis and Experiment of Fiber-Paper Honeycomb Sandwich Structure Composites." Advanced Materials Research 314-316 (August 2011): 566–70. http://dx.doi.org/10.4028/www.scientific.net/amr.314-316.566.

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The aim of this paper is to present a finite element method to predict buckling characteristics of paper honeycomb sandwich panels with composite skins under dynamic axial compression via ANSYS/LS-DYNA. First of all, some problems of the conventional method using honeycomb plate theory, sandwich laminboard theory and equivalent panel theory were pointed out. In order to develop an effective predicting method, by assuming appropriate periodic boundary condition on the edges, a simplified finite element model on hexagonal structure of a unit cell for sandwich panels was developed utilizing the 3D finite element method. The effective Young's modulus of the cellular wall was obtained from the result of the test on the honeycomb core. Several useful conclusions are drawn about the axial crushing of honeycomb sandwich composites and unit cell and can be used to guide the design of composite structures. The paper further attempts to explain numerical results are well consistent with the corresponding experimental ones.
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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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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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Ren, Jin, Yutaka Iwakawa, and Jian Mei He. "An Evaluation on Impact Performance of Light-Weight Composite Honeycomb Sandwich Panels." Applied Mechanics and Materials 423-426 (September 2013): 78–83. http://dx.doi.org/10.4028/www.scientific.net/amm.423-426.78.

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A honeycomb core sandwich panel is superior in impact absorption under whole surface compression, because of the buffer effect of core. However impact properties of honeycomb sandwich panels under local compressions such as drop weight impact are affected by the plates as the face sheets in addition to the core layers. This research describes the drop weight impact properties of honeycomb sandwich panels which consist of various aluminum-alloy honeycomb cores and CFRP composite laminate faces through the spindle falling experiments. In order to confirm the validity of the experiments convictively, analytical approaches based on 3D modeling and ANSYS LS-DYNA software were also carried out. Comparisons of the experimental and analytical results are reported in this study.
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Franco-Urquiza, Edgar Adrián, Perla Itzel Alcántara Llanas, Victoria Rentería-Rodríguez, Raúl Samir Saleme, Rodrigo Ramírez Aguilar, Cecilia Zarate Pérez, Mauricio Torres-Arellano, and Saúl Piedra. "Innovation in Aircraft Cabin Interior Panels. Part II: Technical Assessment on Replacing Glass Fiber with Thermoplastic Polymers and Panels Fabricated Using Vacuum Forming Process." Polymers 13, no. 19 (September 24, 2021): 3258. http://dx.doi.org/10.3390/polym13193258.

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The manufacturing process of the aircraft cabin interior panels is expensive and time-consuming, and the resulting panel requires rework due to damages that occurred during their fabrication. The aircraft interior panels must meet structural requirements; hence sandwich composites of a honeycomb core covered with two layers of pre-impregnated fiberglass skin are used. Flat sandwich composites are transformed into panels with complex shapes or geometries using the compression molding process, leading to advanced manufacturing challenges. Some aircraft interior panels are required for non-structural applications; hence sandwich composites can be substituted by cheaper alternative materials and transformed using disruptive manufacturing techniques. This paper evaluates the feasibility of replacing the honeycomb and fiberglass skin layers core with rigid polyurethane foams and thermoplastic polymers. The results show that the structural composites have higher mechanical performances than the proposed sandwich composites, but they are compatible with non-structural applications. Sandwich composite fabrication using the vacuum forming process is feasible for developing non-structural panels. This manufacturing technique is fast, easy, economical, and ecological as it uses recyclable materials. The vacuum forming also covers the entire panel, thus eliminating tapestries, paints, or finishes to the aircraft interior panels. The conclusion of the article describes the focus of future research.
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Dissertations / Theses on the topic "Composite Honeycomb Sandwich Panels"

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Toribio, Michael Garcia-Lopez 1975. "Compressive response of notched composite-honeycomb sandwich panels." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/50540.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.
Includes bibliographical references (leaves 237-250).
Experimental and numerical work was conducted to understand better the compressive response of notched composite sandwich panels. The quasi-static uniaxial compressive response of notched (circular through hole) E-glass/epoxy- NomexTM sandwich panels were studied experimentally. Two different woven fabric architectures were examined. The key failure mechanism was observed to be linear damage zones (LDZs) emanating from the notch tip (in both materials). LDZ's behaved in a macroscopically similar manner to a bridged crack under tensile loading, and were characterized by semi-stable propagation. Crosssectioning studies revealed the key damage mechanisms operating within the LDZ. Progressive cross-sections indicated that individual fiber microbuckling led to out-of-plane warp tow kinking. The LDZ wake was characterized by kinking in all warp tows and transverse tow splitting. Strain gages were used to measure the in situ damage zone tractions as the LDZ propagated across the width of the specimen; a softening trend was observed. Consistent with observations, a two parameter linear strain softening traction law was used to model the LDZ constitutive behavior. The traction law was treated as a material property. The damage zone modeling (DZM) framework was investigated to determine its validity, specifically its ability to predict three experimentally observed phenomena: the notched strength, local strain distribution, and LDZ growth characteristics. A self-consistent physically-based model should be able to predict all three phenomena. Two models were created in order to interrogate the DZM. The damage growth model was used to determine the ability of the DZM to predict the LDZ growth behavior and notched strength. A finite element model that used discrete nonlinear springs in the wake of the LDZ to model the LDZ as a continuous spring, was implemented to determine if the DZM could predict the local strain distribution. Results showed that the current traction law provided excellent agreement with the phenomenon used to calibrate the traction law, for all specimen sizes. Extension of predictive power to other phenomena resulted in weaker correlations. The modeling framework and methodology established provide a robust tool for investigating the potential of adding physical bases to the DZM.
by Michael Garcia-Lopez Toribio.
S.M.
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Taylor, Matthew Claire. "Damage tolerance of composite honeycomb sandwich panels under quasi-static bending and cyclic compression." Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/41237.

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Hill, Michelle Denise. "Damage resistance and tolerance investigation of carbon/epoxy skinned honeycomb sandwich panels." Thesis, Loughborough University, 2007. https://dspace.lboro.ac.uk/2134/10072.

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This thesis documents the findings of a three year experimental investigation into the impact damage resistance and damage tolerance of composite honeycomb sandwich panels. The primary area of work focuses on the performance of sandwich panels under quasi-static and low-velocity impact loading with hemispherical and flat-ended indenters. The damage resistance is characterised in terms of damage mechanisms and energy absorption. The effects of varying the skin and core materials, skin thickness, core density, panel boundary conditions and indenter shape on the transverse strength and energy absorption of a sandwich panel have been examined. Damage mechanisms are found to include delamination of the impacted skin, core crushing, limited skin-core de bonding and top skin fibre fracture at high loads. In terms of panel construction the skin thickness is found to dominate the panel strength and energy absorption with core density having a lesser influence. Of the external factors considered the indenter noseshape has the largest effect on both failure load and associated damage area. An overview of existing analytical prediction methods is also included and the most significant theories applied and compared with the experimental results from this study. The secondary area of work expands the understanding obtained from the damage resistance study and assesses the ability of a sandwich panel to withstand in-plane compressive loading after sustaining low-velocity impact damage. The importance of the core material is investigated by comparing the compression-after-impact strength of both monolithic carbon-fibre laminates and sandwich panels with either an aluminium or nomex honeycomb core. The in-plane compressive strength of an 8 ply skinned honeycomb sandwich panel is found to be double that of a 16 ply monolithic laminate, with the type of honeycomb also influencing the compressive failure mechanisms and residual compressive strength. It is concluded that under in-plane loading the stabilising effect of the core opposes the de-stabilising effect of any impact damage.
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Nash, Peter. "Experimental impact damage resistance and tolerance study of symmetrical and unsymmetrical composite sandwich panels." Thesis, Loughborough University, 2016. https://dspace.lboro.ac.uk/2134/21748.

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This thesis presents the work of an experimental investigation into the impact damage resistance and damage tolerance for symmetrical and unsymmetrical composite honeycomb sandwich panels through in-plane compression. The primary aim of this research is to examine the impact damage resistance of various types of primarily carbon/epoxy skinned sandwich panels with varying skin thickness, skin lay-up, skin material, sandwich asymmetry and core density and investigate the residual in-plane compressive strengths of these panels with a specific focus on how the core of the sandwich contributes to the in-plane compressive behaviour. This aim is supported by four specifically constructed preconditions introduced into panels to provide an additional physical insight into the loading-bearing compression mechanisms. Impact damage was introduced into the panels over a range of IKEs via an instrumented drop-weight impact test rig with a hemi-spherical nosed impactor. The damage resistance in terms of the onset and propagation of various dominant damage mechanisms was characterised using damage extent in both impacted skin and core, absorbed energy and dent depth. Primary damage mechanisms were found to be impacted skin delamination and core crushing, regardless of skin and core combinations and at high energies, the impacted skin was fractured. In rare cases, interfacial skin/core debonding was found to occur. Significant increases in damage resistance were observed when skin thickness and core density were increased. The reduction trends of the residual in-plane compressive strengths of all the panels were evaluated using IKE, delamination and crushed core extents and dent depth. The majority of impact damaged panels were found to fail in the mid-section and suffered an initial decline in their residual compressive strengths. Thicker skinned and higher density core panels maintained their residual strength over a larger impact energy range. Final CAI strength reductions were observed in all panels when fibre fracture in the impacted skin was present after impact. Thinner skinned panels had a greater compressive strength over the thicker skinned panels, and panel asymmetry in thin symmetrical panels appeared to result in an improving damage tolerance trend as IKE was increased due to that the impact damage balanced the in-plane compressive resistance in the skins with respect to the pre-existing neutral plane shift due to the uneven skin thickness.
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Rudd, Jeffrey Roy. "COMPRESSIVE STRENGTH TO WEIGHT RATIO OPTIMIZATION OF COMPOSITE HONEYCOMB THROUGH ADDITION OF INTERNAL REINFORCEMENTS." University of Akron / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=akron1145900147.

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Žídek, Tomáš. "Aplikace sendvičové konstrukce na formulový vůz." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2016. http://www.nusl.cz/ntk/nusl-254214.

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The master thesis describes application of a sandwich construction for Formula Student car. It will replace the current tubular space frame according to FSAE rules. The introduction is focused on the information of international Formula Student competition, including TU Brno Racing Team. Then there are important rules for the construction of frames and composite monocoques. For the selected production technology are found strength properties of face sheets made of carbon and hybrid fibres. Another part of thesis deals with the design of the sandwich panel using analytical calculation to determine the bending stiffness. On the basis of these proposals are made three-point bending and shear tests. Using of FEM simulation is detected torsional stiffness of the tubular space frame and the monocoque concept from the proposed sandwich panels. The conclusion is devoted to a summary of the important information and possible monocoque manufacturing process.
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Chi, Yunn-Chih (Yvonne). "The response of honeycomb sandwich panels to blast loads." Master's thesis, University of Cape Town, 2008. http://hdl.handle.net/11427/5566.

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Numerous studies have been performed in search of structures providing better blast protection and to understand the various effects influencing the structural performance. This thesis reports on an investigation into the behaviour of circular sandwich panels with aluminium honeycomb cores subjected to air blast loading. It focuses on the effect of varying core thickness, plate thickness and panel configuration. In this study, aluminium honeycomb core is sandwiched between mild steel face plates. Quasi-static tensile and compression experiments are performed to characterise the face plates and the honeycombs. Four sandwich panel configurations are proposed and subjected to blast loading. The impulse is generated by detonating plastic explosives at a constant stand-off distance and measured using a ballistic pendulum. The impulse is varied by using different charge masses. It is observed that the panels experience front plate deflection and tearing; honeycomb core crushing and densification; and back plate deflection and tearing. The deformations of the face plates and the cores increased with increasing impulse. Increasing the core thickness delayed the onset of core densification and decreased back plate deflection; and increasing the plate thickness also decreased back plate deflection. The use of an extra sandwich layer helps to provide better structural support but has the penalty of extra mass.
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Rollins, Mark Andrew. "Impact on panels of sandwich construction." Thesis, University of Oxford, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.670304.

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Maheri, M. R. "Vibration damping in composite/honeycomb sandwich beams." Thesis, University of Bristol, 1991. http://hdl.handle.net/1983/d96ba3e9-edb0-4a07-ac6e-69328ed22678.

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Palla, Leela Prasad. "Blast Response of Composite Sandwich Panels." University of Akron / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=akron1227216480.

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Books on the topic "Composite Honeycomb Sandwich Panels"

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Walker, Sandra P. Evaluation of composite honeycomb sandwich panels under compressive loads at elevated temperatures. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

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M, McGowan David. Compression response of a sandwich fuselage keel panel with and without damage. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Optimization of composite sandwich cover panels subjected to compressive loadings. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.

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Numerical and experimental investigation of hollow sphere structures in sandwich panels. Stafa-Zuerich: Trans Tech Publications, 2008.

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

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Study of compression-loaded and impact-damaged structurally efficient graphite-thermoplastic trapezoidal-corrugation sandwich and semisandwich panels. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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Jegley, Dawn C. Study of compression-loaded and impact-damaged structurally efficient graphite-thermoplastic trapezoidal-corrugation sandwich and semisandwich panels. Hampton, Va: Langley Research Center, 1992.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Study of compression-loaded and impact-damaged structurally efficient graphite-thermoplastic trapezoidal-corrugation sandwich and semisandwich panels. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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Ko, William L. Combined-load buckling behavior of metal-matrix composite sandwich panels under different thermal environments. Edwards, Calif: Dryden Flight Research Facility, 1991.

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Viita-Aho, Tarvo. A finite element analysis of the response of composite sandwich panels to blast loading. Manchester: UMIST, 1992.

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Book chapters on the topic "Composite Honeycomb Sandwich Panels"

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Nishiwaki, Tsuyoshi. "Numerical Modeling Method for the Honeycomb Sandwich Panels." In Design and Manufacturing of Composites, 247–54. New York: CRC Press, 2021. http://dx.doi.org/10.1201/9781003076131-46.

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Chen, An, and Julio F. Davalos. "Guidelines for Design of Honeycomb FRP Sandwich Panels." In Advances in FRP Composites in Civil Engineering, 468–73. Berlin, Heidelberg: Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-17487-2_101.

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Davalos, Julio F., Avinash Vantaram, An Chen, Indrajit Ray, and Jerry D. Plunkett. "Honeycomb Fiber-Reinforced Polymer Sandwich Panels for Fish Culture Tanks." In Advances in FRP Composites in Civil Engineering, 177–82. Berlin, Heidelberg: Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-17487-2_38.

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Kun, Yang, Yan Qun, and Xu Fei. "Simulation and Test Study on Composite Honeycomb Sandwich Panel." In Lecture Notes in Electrical Engineering, 368–79. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-7652-0_34.

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Shirbhate, Payal, Shreya Korde, and Manmohan Dass Goel. "Pressure-Impulse Diagrams for Paper Honeycomb Core Sandwich Panel Using Finite Element Method." In Composite Materials for Extreme Loading, 295–306. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-4138-1_21.

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Bendada, Aya, Djilali Boutchicha, Mokhtaria Miri, and Adel Chouiter. "Characterization of Honeycomb Sandwich Composite Panel Using Numerical Methods and Experimental Modal Analysis Validation." In Proceedings of the 1st International Conference on Numerical Modelling in Engineering, 408–16. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-2273-0_32.

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Ng, Lin Feng, and Kathiravan Subramaniam. "Composite Sandwich Panels with the Metallic Facesheets." In Sandwich Composites, 61–74. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003143031-4.

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Verma, Shashikant, Lalit Ranakoti, Brijesh Gangil, and Manoj Kumar Gupta. "Drilling and Repair of the Composite Sandwich Panels." In Sandwich Composites, 261–75. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003143031-13.

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Mahesh, Vishwas, Vinyas Mahesh, and Dineshkumar Harursampath. "Low-Velocity Impact Response of the Composite Sandwich Panels." In Sandwich Composites, 99–114. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003143031-6.

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Yang, Jin-Shui, and Shuang Li. "Metallic Core- and Truss Core-Based Composite Sandwich Panels." In Sandwich Composites, 45–60. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003143031-3.

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Conference papers on the topic "Composite Honeycomb Sandwich Panels"

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Smith, Bert L., John S. Tomblin, K. S. Raju, K. H. Liew, A. K. M. Haque, and Juan C. Guarddon. "Damage Tolerance of Honeycomb Sandwich Composite Panels." In General Aviation Technology Conference & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2002. http://dx.doi.org/10.4271/2002-01-1537.

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Alam, Shah, and Damodar Khanal. "Impact Analysis of Honeycomb Core Sandwich Panels." In ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-23825.

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Abstract The goal of this paper is to analyze the impact behavior among geometrically different sandwich panels shown upon impact velocities. Initially, composite model with aluminum honeycomb core and Kevlar (K29) face sheets is developed in ABAQUS/Explicit and different impact velocities are applied. Keeping other parameters constant, model is simulated with T800S/epoxy face sheets. Residual velocities, energy absorption (%), and maximum deformation depth is calculated for sandwich panel for both models at five different velocities by executing finite element analysis. Once the better material is found for face sheets, process is extended by varying the ratio of front face sheet thickness to back face sheet thickness keeping other geometrical parameters constant to find the better geometry. Also, comparison of impact responses of sandwich composite panel on different ratio of front face sheet thickness to back face sheet thickness is done and validated with other results available in literature.
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Gu, Haozhong. "Progressive Failure Analysis of Composite Honeycomb Sandwich Panels." In 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2051.

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Alam, Shah, and Aakash Bungatavula. "Numerical Modelling of Impact Behavior of Composite Sandwich Panel With Honeycomb Core." In ASME 2019 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/imece2019-11721.

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Abstract The goal of this paper is to find the best impact response of the composite sandwich panels with honeycomb core. The focus of the study is to find the effects of changing the face sheet thickness and the core height of the sandwich panel subjected to variable velocities on impact performance. Initially, honeycomb core sandwich panel with 1mm thick face sheet is modelled in Abaqus/explicit to calculate the energy absorption, residual velocity, and deformation at four different velocities. Then, the process is repeated by changing the face sheets thickness to 2mm and 3mm to see the effects of changing the thickness on the impact performance of a composite sandwich panel. The honeycomb core height is also changed to see its effect on the performance. In all models, Al 7039 is used in the core and T1000G is used in the face sheets.
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Gandy, H. T. N., and R. Asmatulu. "Adhesiveless Composite Structures With Carbon Fiber Prepregs for Aircraft Primary Structural Applications." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-93462.

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The present work was focused on the properties of adhesiveless honeycomb sandwich structures with carbon fiber prepreg, while assessing the properties with adhesive films at the skin-to-core interface simultaneously. In this work, laminate and honeycomb sandwich panels were fabricated and tested with consistent lay-up, curing, and testing processes. The test specimens from the panels were tested for physical properties at room, hot, and cold temperatures, as well as different moisture absorption performances. The results confirmed that the self-adhesive prepreg physical properties met the components and void content recommendations used in primary structures of aircraft. The mechanical tests showed comparable results to panels, with prepreg and adhesive film at the skin-to-core interface, commonly used for primary structures.
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Suji Han, Jung-Ryul Lee, and Eric B. Flynn. "Remote imaging of local resonance for inspection of honeycomb sandwich composite panels." In 2015 IEEE Sensors. IEEE, 2015. http://dx.doi.org/10.1109/icsens.2015.7370109.

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Leone, Jr., Frank A., Didem Ozevin, Valery Godinez, Bao Mosinyi, John G. Bakuckas, Jr., Jonathan Awerbuch, Alan Lau, and Tein-Min Tan. "Acoustic emission analysis of full-scale honeycomb sandwich composite curved fuselage panels." In The 15th International Symposium on: Smart Structures and Materials & Nondestructive Evaluation and Health Monitoring, edited by Peter J. Shull, H. Felix Wu, Aaron A. Diaz, and Dietmar W. Vogel. SPIE, 2008. http://dx.doi.org/10.1117/12.776146.

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Franco, Francesco, Kenneth A. Cunefare, and Massimo Ruzzene. "Structural-Acoustic Optimization of Sandwich Panels." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-85383.

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Sandwich panels, comprising face sheets enclosing a core, are increasingly common structural elements in a variety of applications, including aircraft fuselages and flight surfaces, vehicle panels, lightweight enclosures, and bulkheads. The design flexibility associated with such composite structures provides significant opportunities for tailoring the structure to the load and dynamic response requirements for the particular application. Design flexibility encompasses the details of the face sheets and the core. This paper deals with the numerical optimization of different sandwich configurations for the purposes of achieving reduced structural acoustic response. Laminated face sheets and core geometries, comprising honeycomb and truss-like structures, are considered. The relative importance of the mass and stiffening properties of the core and face sheets are discussed. The optimization work is carried out using commercial codes. Benefits and limits of using an optimization algorithm based on gradient methods are highlighted.
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Sun, Mengqian, Patrick Kendall, Diane Wowk, Il Yong Kim, and Christopher Mechefske. "Damage Assessment on the Surface and Honeycomb Core of the Aluminum Sandwich Panel Subjected to Low-Velocity Impact." In ASME 2018 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/detc2018-86028.

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Sandwich panels consisting of aluminum face-sheets and honeycomb core are widely used in transportation systems. The composite structure has a high stiffness and strength, but it is susceptible to impacts in service. An experimental investigation of surface deformation and core damage in a honeycomb sandwich panel subjected to three different low-velocity impact energies was undertaken. Surface damage evaluation using 3D laser scanning technology was conducted to assess the surface damage and a comparison was made with two typical indentation profiles which were proposed mathematically in the past. The experimental dent profile shows a good agreement with one of the two analytical dent profiles. The impacted sandwich panel was then cut transversely to study the damage inside the honeycomb core. The number of buckled or collapsed folds under the damaged top face-sheet and the depth of the core damage were utilized as two parameters to quantify the damage of the honeycomb core. It is concluded that the core damage depth and the number of folds is independent of impact energy and is constant within each dent.
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Bushnell, David, and David Bushnell. "Optimum design via PANDA2 of composite sandwich panels with honeycomb or foam cores." In 38th Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-1142.

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