Relevant bibliographies by topics / Composite Sandwich Panels

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

Academic literature on the topic 'Composite Sandwich Panels'

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

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Journal articles on the topic "Composite Sandwich Panels"

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RUSU, Bogdan, Simona BLINDU BLINDU, Andra MICU, and Valentin SOARE. "Guidelines for Aircraft Composite Panels." INCAS BULLETIN 12, no. 1 (March 1, 2020): 217–28. http://dx.doi.org/10.13111/2066-8201.2020.12.1.21.

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The objective of this paper is to give a general perspective and present some elementary steps for manufacturing aircraft sandwich panel composites. Composite materials have been widely used in high performance sectors of the aerospace and automotive industry, and there is considerable knowledge and confidence in their static, dynamic and crashworthiness properties. Sandwich composites are becoming more and more used in airframe structural design, mainly for their ability to substantially reduce weight while maintaining their high mechanical properties. The steps for manufacturing a sandwich composite that meets all the requirements for exploitation are very precise and rigorous, involving specific design requirements, specific materials selection and specific manufacturing conditions starting with the lay-up procedure and up to the curing process inside an autoclave. After the curing process, destructive and nondestructive tests and experiments are performed on the composite structures in order to validate the products. At the same time, this paper presents a short briefing about the implication of 3D printing technologies with high temperature resistance resins for sandwich cores used in aerospace applications.
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Shi, Yunxing, Yangang Zhang, Kun Ni, Wei Liu, and Ye Luo. "Research and practices of large composite external wall panels for energy saving prefabricated buildings." MATEC Web of Conferences 289 (2019): 10012. http://dx.doi.org/10.1051/matecconf/201928910012.

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The production process and application of large composite external wall panels (composite panels for short) are introduced in this paper. Composite panels with both load bearing and thermal insulation were formed by pouring normal concrete (NC) and ceramsite foamed concrete (CFC) continuously according to particular technological requirements, which made two layers into a seamless whole. The layers of NC and CFC are for load bearing and thermal insulation respectively. The composite panels were manufactured in the scale of industrial production, and applied to several energy saving prefabricated buildings successively, instead of polystyrene sandwich composite panels (sandwich panel for short) as external wall panels. There are several obvious advantages of the composite panel over the sandwich panel or outer benzoic board. Firstly, it solved the problems of durability of polystyrene and the complex production process of the sandwich pane, the production process of the external wall was thus greatly simplified. In addition, the fire risk was much reduced.
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Ravindran, Bharath, Michael Feuchter, and Ralf Schledjewski. "Investigation of the Mechanical Properties of Sandwich Composite Panels Made with Recyclates and Flax Fiber/Bio-Based Epoxy Processed by Liquid Composite Molding." Journal of Composites Science 7, no. 3 (March 15, 2023): 122. http://dx.doi.org/10.3390/jcs7030122.

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Despite significant advancements in bio-based natural-fiber-reinforced composites, the recyclability/reprocessing of thermoset composites remains a persistent challenge that needs to be addressed. In the present study, an effort is made to provide a justification for the recyclability/reprocessing assessment of sandwich composite panels made with ‘recyclate’ (i.e., recycled flax/bio-based epoxy composite) cores and (flax/bio-based epoxy) skins produced by liquid composite molding. Resin transfer molding and vacuum-assisted resin infusion processes were used to investigate the influence of production processes on mechanical properties. Two different recyclate sizes—4 mm and 10 mm—were used to fabricate sandwich composite panels to study the effect of size on the mechanical properties of the panels. This study aims to compare the qualities of sandwich panels to those of virgin composite panels in terms of their physical (density) and mechanical properties (tensile and flexural). Additionally, the recyclate packing was verified by employing digital microscopy. The results illustrated that the sandwich panels made with the 4 mm recyclates exhibited better mechanical properties compared to those made with the 10 mm recyclates. In comparison with virgin composite panels, the sandwich composite panels made of flax fiber and (flax/epoxy) recyclate exhibited significantly higher flexural moduli, which was attributed to their moments of inertia. This article emphasizes recycling/reprocessing and demonstrates an effective closed-loop approach. Thus, by preserving the structural integrity of recyclates, sandwich panels could be advantageous for semi-structural applications.
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Alves, LM, RM Afonso, CMA Silva, and PAF Martins. "Joining sandwich composite panels to tubes." Proceedings of the Institution of Mechanical Engineers, Part L: Journal of Materials: Design and Applications 233, no. 7 (March 27, 2018): 1472–81. http://dx.doi.org/10.1177/1464420718763463.

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This paper proposes a new joining by forming process for connecting metal–polymer sandwich composite panels to metallic tubes. The process involves forming an annular flange with rectangular cross-section by partial sheet-bulk of the tube wall thickness and performing the mechanical interlocking by upsetting the free tube end against the sandwich composite with a flaring punch. The presentation addresses the main process variables and workability limits, and the overall conclusions are supported by experimentation and finite element analysis. Results show that the new proposed joining by forming process has potential to be used in mass production contributing, therefore, to extend the application of metal–polymer sandwich composites to structural components.
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Li, Hao, Cong Jiang, Ye Wu, Yonghu Huang, Yun Wan, and Ru Chen. "Experimental study on the low-velocity impact failure mechanism of foam core sandwich panels with shape memory alloy hybrid face-sheets." Science and Engineering of Composite Materials 28, no. 1 (January 1, 2021): 592–604. http://dx.doi.org/10.1515/secm-2021-0059.

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Abstract Superelastic shape memory alloy (SMA) as an advanced smart material has been used to improve the impact performance of fiber-reinforced composites in recent decades. Due to the low impact toughness of the thin composite face-sheet and the poor strength of the foam core, sandwich panels are sensitive to the transverse loading. SMA fibers were embedded into the composite laminated to improve the impact resistance of the traditional foam core sandwich panel in this work. Five new types of SMA hybrid panels were prepared, and the testing panels with penetration failure were observed at the impact energy of 50 J. The impact mechanical responses and the damage morphology were analyzed, and the impact failure mechanism was also revealed. Results show that all sandwich panels were failed, the fiber breakage occurred at the impact region in the traditional panels, while part plies of the rear face-sheets split-off in the SMA hybrid panels. The impact performance of the SMA hybrid panels is improved when compared with the traditional panel, the reduction of the delamination area by 48.15% and the increase of the load-bearing threshold by 32.75% are acquired for the hybrid sandwich panel with two layers of SMA fibers in the rear face-sheet.
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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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Kormaníková, Eva, and Kamila Kotrasová. "Dynamic Behavior of Composite Sandwich Panel with CFRP Outer Layers." WSEAS TRANSACTIONS ON APPLIED AND THEORETICAL MECHANICS 17 (December 31, 2022): 259–65. http://dx.doi.org/10.37394/232011.2022.17.32.

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Sandwich panel with laminate faces is used for free vibration analysis. The periodic microstructure and Mori- Tanaka model are used for homogenization of unidirectional fiber reinforced composite. The Shear Deformation Theory is considered for analytical and numerical analysis. FEM in ANSYS is used for numerical analysis. The effect of sandwich design parameters such as panel length, core thickness and fiber reinforced angle on vibration response is investigated. Natural frequencies of sandwich panel versus sandwich design parameters are presented in graphical form. From the results can be concluded that sandwich design parameters affect the natural frequencies of sandwich panels, and this effect is important for designing of sandwich panels under dynamic load.
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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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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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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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Dissertations / Theses on the topic "Composite Sandwich Panels"

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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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Serranía-Soto, Florencia. "Low velocity impact of composite sandwich panels." Thesis, Queen Mary, University of London, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.398305.

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Zangani, D. "Modelling of z-Core composite sandwich panels." Thesis, University of Newcastle Upon Tyne, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.533691.

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Cowan, Andre James. "Sound Transmission Loss of Composite Sandwich Panels." Thesis, University of Canterbury. Mechanical Engineering, 2013. http://hdl.handle.net/10092/7879.

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This thesis examines the sound transmission loss (STL) through composite sandwich panel systems commonly used in the marine industry. Experimental, predictive and optimisation methods are used to evaluate the acoustic performance of these systems and to improve their acoustic performance with noise treatment. The complex nature of the material properties of composite sandwich panels was found to be dependent not only on the physical properties but also the frequency of incident noise. Young’s modulus was found to reduce with increasing frequency as has been predicted in the literature which is due to the shear stiffness dominating over the bending stiffness. Two methods for measuring these properties were investigated; ‘fixed-free’ and ‘free-free’ beam boundary condition modal analyses. The disagreement between these methods was identified as the clamping fixed nature that increased flexibility of the beam. Composite sandwich panels can be modelled as homogeneous isotopic materials when predicting their acoustic performance provided the dilatational resonance is above the frequency range of interest. Two such panels were modelled using this simple sound insulation prediction method, but the agreement between theory and experimental results was poor. A variable Young’s modulus was included in the model but agreement remained relatively poor especially in the coincidence frequency region due to variation of Young’s modulus with frequency. A statistical method of optimisation of the parameter settings by fractional factorial design proved successful at identifying the important parameters that affect the sound transmission class (STC) of a noise treatment material applied to a panel. The decouple foam layer and attachment method were the most significant factors. The same method, with higher resolution was then used to identify the important parameters that affected the noise reduction class (NRC) finding that the outer foam thickness without a face sheet were the most significant factors. The independent optimisation studies performed for each of the STC and NRC produced conflicting results meaning that both could not be achieved simultaneously.
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Vogler, Tracy J. (Tracy John). "Compressive behavior and failure of composite sandwich panels." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/11677.

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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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Wennhage, Per. "Structural-Acoustic Optimization of Sandwich Panels." Doctoral thesis, Stockholm, 2001. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3161.

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Bambal, Ashish S. "Mechanical evaluation and FE modeling of composite sandwich panels." Morgantown, W. Va. : [West Virginia University Libraries], 2007. https://eidr.wvu.edu/etd/documentdata.eTD?documentid=5379.

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Thesis (M.S.)--West Virginia University, 2007.
Title from document title page. Document formatted into pages; contains xviii, 141 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 140-141).
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Hanafi, Wemphy. "Flexural performance of glass fiber reinforced composite sandwich panels /." Available to subscribers only, 2007. http://proquest.umi.com/pqdweb?did=1328053201&sid=33&Fmt=2&clientId=1509&RQT=309&VName=PQD.

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Tsang, Pui Ho Wilson. "Impact resistance and damage tolerance of composite sandwich panels." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/11925.

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Books on the topic "Composite Sandwich Panels"

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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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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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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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H, Jackson Raymond, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Combined-load buckling behavior of metal-matrix composite sandwich panels under different thermal environments. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 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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Marshall, Rouse, and United States. National Aeronautics and Space Administration., eds. Response of composite fuselage sandwich side panels subjected to internal pressure and axial tension. [Washington, D.C: National Aeronautics and Space Administration, 1998.

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Marshall, Rouse, and United States. National Aeronautics and Space Administration., eds. Response of composite fuselage sandwich side panels subjected to internal pressure and axial tension. [Washington, D.C: National Aeronautics and Space Administration, 1998.

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Book chapters on the topic "Composite Sandwich Panels"

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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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Ebrahimnezhad-Khaljiri, Hossein. "High-Velocity Impact Properties of the Composite Sandwich Panels." In Sandwich Composites, 115–30. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003143031-7.

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Joseph, Athul, Vinyas Mahesh, Vishwas Mahesh, and Dineshkumar Harursampath. "Introduction to Sandwich Composite Panels and Their Fabrication Methods." In Sandwich Composites, 1–25. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003143031-1.

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Dewangan, Hukum Chand, Subrata Kumar Panda, Nitin Sharma, and Chetan Kumar Hirwani. "Investigation of Blast Loading Response of the Composite Sandwich Panels." In Sandwich Composites, 131–46. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003143031-8.

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Behera, B. K., Manya Jain, Lekhani Tripathi, and Soumya Choudhury. "Low-Velocity Impact Behaviour of Textile-Reinforced Composite Sandwich Panels." In Sandwich Composites, 213–60. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003143031-12.

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Dear, John P. "Blast Performance of Composite Sandwich Panels." In Advances in Thick Section Composite and Sandwich Structures, 85–119. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-31065-3_3.

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Mishra, Dhaneshwar, Charanjeet Singh Tumrate, and Anoop Kumar Mukhopadhyay. "Failure Behavior and Residual Strength of the Composite Sandwich Panels Subjected to Compression after Impact Testing." In Sandwich Composites, 75–97. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003143031-5.

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Conference papers on the topic "Composite Sandwich Panels"

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F., Warmuth, and Lange J. "Openings in Sandwich Panels." In 4th International Conference on Steel & Composite Structures. Singapore: Research Publishing Services, 2010. http://dx.doi.org/10.3850/978-981-08-6218-3_cc-fr025.

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Böttcher, Marc, and Jörg Lange. "Sandwich Panels with Openings." In Fifth International Conference on Composite Construction in Steel and Concrete. Reston, VA: American Society of Civil Engineers, 2006. http://dx.doi.org/10.1061/40826(186)14.

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Koudela, K. L., G. H. Koopmann, and W. Chen. "Concurrently Engineered Active Composite Sandwich Panels." In ASME 1996 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/imece1996-0534.

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Abstract The objective of this study was to design, fabricate, and test an active panel capable of significantly reducing the radiated sound power from a vibrating structure. To accomplish this objective, a cascaded flextensional actuator was embedded in a composite sandwich panel consisting of inner and outer E-glass/epoxy face sheets separated by a foam core where portions of the core were removed to accept a high performance actuator. The actuator consisted of a cascaded flextensional, mechanical amplifier driven by two, co-fired, multi-layered, piezoceramic stacks. The stack displacements were amplified by the cascaded flextensional to generate the levels of surface normal vibrations of the panel’s composite face sheets to produce the desired sound power reductions. A prototype active composite sandwich panel containing a single embedded cascaded flextensional actuator was fabricated and an experiment was conducted to evaluate its dynamic response. Dynamic finite element analyses were performed to simulate the experiment. Good correlation was obtained between the predictions and the experimental results. Final testing was conducted in air in a sound transmission loss facility to determine the levels of sound pressure reduction achievable with the prototype active composite sandwich panel. Up to a 25 dB reduction in sound pressure level was obtained over the frequency band of interest.
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Şen, Naim, and Buket Okutan Baba. "Impact Analysis of Sandwich Composite with Auxetic Core." In 6th International Students Science Congress. Izmir International Guest Student Association, 2022. http://dx.doi.org/10.52460/issc.2022.032.

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In this study, energy absorption and impact performance of aluminum sandwich panels with different core structures under impact load were investigated. The main purpose of the study is to reveal how chiral core shapes and sizes affect the energy absorbed by the panel, the contact force and the displacement of the impactor with a constant energy of 90 joule. Numerical studies have been carried out on square sandwich panels with three different core structures: tetrachiral, anti-tetrachiral and hexachiral. Dimensions of all panels, node diameters and ligament thicknesses of chiral structures were kept constant. Finite element models were established for core structures, panels with cell configurations of 3x3, 5x5 and 7x7 for each chiral structure by changing ligament length. Johnson-Cook material model was used for the aluminum sandwich panel, and rigid and isotropic material model was used for the impactor. The effects of auxetic cell structures and cell configurations on the impact behavior of sandwich panels were discussed as a result of the analysis. The highest impact performance emerged in the hexachiral structure with 7x7 cell configuration. As a result of the study, it has been revealed that auxetic chiral structures are materials that can absorb impact energy and have an important place in the mass-performance relationship. This research will be a preliminary study for the understanding of next generation auxetic sandwich panel behaviors.
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Ciccarelli, Daniele, Archimede Forcellese, Luciano Greco, Lorenzo Panaccio, Massimiliano Pieralisi, Michela Simoncini, and Giulio Trevisan. "Mechanical properties of sandwich composite panels." In PROCEEDINGS OF THE 22ND INTERNATIONAL ESAFORM CONFERENCE ON MATERIAL FORMING: ESAFORM 2019. AIP Publishing, 2019. http://dx.doi.org/10.1063/1.5112748.

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Raju, K. S., and J. S. Tomblin. "Energy Absorption in Stitched Composite Sandwich Panels." In Advances In Aviation Safety Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/981202.

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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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8

SUN, C. "Low velocity impact of composite sandwich panels." In 32nd Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-1077.

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Sun, C. T., R. S. Hasebe, and Y. Hua. "Properties of Sandwich Structures With Reinforced Core." In ASME 1997 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/imece1997-0733.

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Abstract Sandwich panels with a Rohacell core reinforced with composite laminates were constructed. The effective properties of the reinforced core were derived and verified by three point bending tests of a sandwich beam. The equilibrium equations for the sandwich plate with the composite reinforced core were derived. Impact experiment was also conducted by use of a drop tower. Damage modes and levels of damage in sandwich panels containing bare and reinforced Rohacell cores were investigated and compared. Several NDI methods were employed to inspect the damage in the sandwich panel and their merits were compared.
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Sun, J. Q. "Active Sandwich Trim Panels for Quieter Aircraft Interior." In ASME 1999 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/imece1999-0138.

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Abstract Recent research in the area of structural acoustic control for aircraft interior noise suppression has been focused on developing active trim panels. Active trim panels being part of non-critical structures offer many advantages over active controls applied to load critical structures such as aircraft frames and skins. This paper presents a study of active sandwich composite trim panels. The paper first investigates the effect of curvature on the dynamics of the trim panel, and the power transfer between the actuator and the host panel. Experimental data of interior noise control are then presented to demonstrate the application of the active trim panels.
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Reports on the topic "Composite Sandwich Panels"

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Ratcliffe, Colin P. Experimental Modal Analysis of a Sandwich Construction, Glass Reinforced Plastic Composite Deck Panel. Fort Belvoir, VA: Defense Technical Information Center, July 1996. http://dx.doi.org/10.21236/ada359147.

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