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Добірка наукової літератури з теми "Al-honeycomb sandwich composites"

Автор: Grafiati
Опубліковано: 14 березня 2023

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Статті в журналах з теми "Al-honeycomb sandwich composites"

1

Gunes, Recep, Kemal Arslan, M. Kemal Apalak, and JN Reddy. "Ballistic performance of honeycomb sandwich structures reinforced by functionally graded face plates." Journal of Sandwich Structures & Materials 21, no. 1 (January 24, 2017): 211–29. http://dx.doi.org/10.1177/1099636216689462.

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Анотація:
This study investigates damage mechanisms and deformation of honeycomb sandwich structures reinforced by functionally graded face plates under ballistic impact. The honeycomb sandwich structure consists of two identical functionally graded face sheets, having different material compositions through the thickness, and an aluminum honeycomb core. The functionally graded face sheets consist of ceramic (SiC) and aluminum (Al 6061) phases. The through-thickness mechanical properties of face sheets are assumed to vary according to a power-law. The locally effective material properties are evaluated using the Mori–Tanaka scheme. The effect of material composition of functionally graded face sheets on the ballistic performance of honeycomb sandwich structures was investigated using the finite element method and the penetration and perforation threshold energy values on ballistic performance and ballistic limit of the sandwich structures are determined. The contribution of the honeycomb core on the ballistic performance of the sandwich structure was evaluated by comparing with spaced plates (without honeycomb core) in terms of the residual velocity, kinetic energy, and damage area.
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2

Srilakshmi, R., and R. Sanjay kumar. "Numerical analysis of sandwich panels under high-velocity impact." IOP Conference Series: Materials Science and Engineering 1248, no. 1 (July 1, 2022): 012104. http://dx.doi.org/10.1088/1757-899x/1248/1/012104.

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Abstract Composites are gaining importance in aircraft structures, due to their high specific strength, stiffness, and low weight. There are different types of composites used in aircraft structures out of which carbon fiber reinforced polymer (CFRP) serves best in the aircraft industry. Half of the weight of the Boeing 787 is made of CFRP and other composites that reduced the weight of the aircraft by 20% as compared to the conventional design with aluminum alloy. Similar to CFRP the recent trend focused on the usage of sandwich structures in aircraft design. Sandwich structure is a composite material made of the lightweight thick core placed between the thin face sheets made of CFRP or Glass fiber reinforced polymer. During service, aircraft panels are subjected to severe structural, aerodynamics loads, and impact loads. These loads cause severe damage to the structure that affects the residual strength. The impact is the more susceptible damage in composite panels. In this paper, a numerical impact analysis of the sandwich panel is carried out. There are different parameters that influence the impact strength of sandwich panels are face sheet material, core material, and thickness of the core. In this paper, finite element-based parametric analysis is carried out by varying face sheet materials such as CFRP, GFRP, Al alloy, Ti alloy, and core materials (such as honeycomb structure and PVC foam). Further, in this work, the combined MADM method using TOPSIS and AHP is applied to find out the optimal face sheet material for the sandwich panel. The attribute data for applying the MADM method is obtained from finite element analysis (FEA).
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3

Nasution, Muhammad Ridlo Erdata, Naoyuki Watanabe, and Atsushi Kondo. "Numerical study on thermal buckling of CFRP–Al honeycomb sandwich composites based on homogenization–localization analysis." Composite Structures 132 (November 2015): 709–19. http://dx.doi.org/10.1016/j.compstruct.2015.06.009.

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4

Arslan, Kemal, Recep Gunes, M. Kemal Apalak, and JN Reddy. "Experimental tests and numerical modeling of ballistic impact on honeycomb sandwich structures reinforced by functionally graded plates." Journal of Composite Materials 51, no. 29 (March 8, 2017): 4009–28. http://dx.doi.org/10.1177/0021998317695423.

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Анотація:
The aim of this study is to determine the ballistic impact response of a novel sandwich structure consisting of aluminum honeycomb and Al/SiC functionally graded face sheets and develop a compatible numerical model with experiments. The experiments were carried out by a single-stage gas gun system and numerical simulations were performed using the explicit finite element code, LS-DYNA®. The mechanical properties of the functionally graded face sheets through the thickness were considered in accordance with a power-law distribution. The Mori–Tanaka scheme was used in order to determine the effective material properties of the functionally graded face sheets at a local point. In order to simulate the elastoplastic behavior of the functionally graded face sheets, Tamura–Tomota–Ozawa model was implemented in the numerical model. The ballistic performance of the sandwich structure was investigated for metal-rich ( n = 0.1), linear ( n = 1.0), and ceramic-rich ( n = 10.0) compositions of the functionally graded face sheets. The results indicated that the ceramic fraction of the functionally graded face sheets was quite influential on energy absorption capability, damage mechanism, and impact resistance of the sandwich structure. The sandwich structure with linear functionally graded face sheets showed the highest ballistic performance in terms of damage and deformation shapes of the entire sandwich structure among investigated material compositions.
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5

Arslan, Kemal, and Recep Gunes. "Experimental damage evaluation of honeycomb sandwich structures with Al/B4C FGM face plates under high velocity impact loads." Composite Structures 202 (October 2018): 304–12. http://dx.doi.org/10.1016/j.compstruct.2018.01.087.

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6

Kim, Hong Gun, Young Jun Kim, Hee Jae Shin, Sun Ho Ko, Hyun Woo Kim, Young Min Kim, Yun Ju Cha, Woo Kum Lee, and Lee Ku Kwac. "A Study on the Bending Analysis of the Al Honeycomb Core Sandwich Composite Panel Bearing Large Bending Load." Advanced Materials Research 702 (May 2013): 245–52. http://dx.doi.org/10.4028/www.scientific.net/amr.702.245.

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Анотація:
Al honeycomb core sandwich composite panels have different core and plate materials. The core is the Al honeycomb core, and the thin plate is GFRP sheets with fibers laminated in the 0°/90° symmetric structure. The Al honeycomb core sandwich composite panel is used for structures, which involve relatively high bending load. Before designing the structures, their stability is evaluated via the finite element analysis. In this study, an analysis method that is closest to the reality was proposed for designing the structures with Al honeycomb core sandwich composite panels. For that purpose, the modulus was reviewed. In the finite element analysis, the tensile modulus is generally used. In the results of this study, however, the tensile modulus led to significant deviations from the test results, whereas the bending modulus led to a closer value to the test results.
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7

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

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Анотація:
Coefficients of thermal and moisture expansion (CTE and CME) can be predicted for many composite laminates and sandwich panels. Core and adhesive properties, such as geometry and stiffness are important variables. Laminate theory is augmented with a modified model for anisotropic core properties to predict the CTE and CME of sandwich panels. Procedures to measure both CTE and CME are described. Since these are thermodynamic properties, methods to obtain equilibrium moisture strains are needed. Results are given for CFRP facesheets with Al and NOMEX honeycomb cores, and for woven Kevlar facesheets with Al cores. Agreement with predictions is good and depends highly on knowledge of properties of all constituents.
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8

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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Анотація:
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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9

Cho, Ki-Dae, Sung-Rok Ha, Kwang-Hee Kang, Jie-Eok Kim, and Sung-Chul Yang. "An Experimental Study on the Mechanical Properties of T-Joints Structure using CFRP/Al Honeycomb Sandwich Composite." Journal of the Korean Society of Precision Engineering 29, no. 3 (March 1, 2012): 313–18. http://dx.doi.org/10.7736/kspe.2012.29.3.313.

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10

Patel, Murlidhar, and Shivdayal Patel. "Novel design of honeycomb hybrid sandwich structures under air-blast." Journal of Sandwich Structures & Materials, September 19, 2022, 109963622211279. http://dx.doi.org/10.1177/10996362221127967.

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Анотація:
In this study, dynamic explicit analysis was performed to examine the air-blast performance of various hybrid sandwich designs in terms of face plate deflections and energy dissipation capacity under the conventional weapons effects program (CONWEP) air-blast loads ranging from 3 kg to 8 kg trinitrotoluene for stand-off distance ranges from 150 mm to 200 mm. The blast resistance of honeycomb sandwich configurations was evaluated using steel honeycomb with different core topologies, crushable Al foam-filled steel honeycomb, and steel or steel with 3D Kevlar/polypropylene laminate employing fiber metal laminate (FML) front face. For an accurate prediction of the deformation mechanism of all steel parts, the Johnson-Cook (J-C) model was used. The composite failure criteria of Hashin, Puck, and Matzenmiller were implemented to accurately examine the fiber and matrix damage behavior. The novel hybrid design of the honeycomb sandwich structure’s blast resistance is improved by the employment of foam-filled honeycomb, an FML front face, and a circular honeycomb core. In comparison to other sandwich configurations, a novel designed hybrid sandwich construction composed of foam filled circular honeycomb with FML front facing and steel back facing (FCH-1KP0.5) achieved the highest blast resistance due to its lowest face deflection with the smallest plastic dissipation energy.
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Частини книг з теми "Al-honeycomb sandwich composites"

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Khuntia, Sravan Kumar, Kumbhar Avinash Suresh, Jithin Joshi, and Shantanu Bhowmik. "Finite Element Analysis and Mechanical Property Evaluation of CFRP and Al Honeycomb Sandwich Composite." In Techniques and Innovation in Engineering Research Vol. 4, 1–20. B P International (a part of SCIENCEDOMAIN International), 2022. http://dx.doi.org/10.9734/bpi/taier/v4/3943a.

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Тези доповідей конференцій з теми "Al-honeycomb sandwich composites"

1

Vaidya, Uday K., Mohan V. Kamath, Mahesh V. Hosur, Anwarul Haque, and Shaik Jeelani. "Low Velocity and Compression-After-Impact Response of Pin-Reinforced Sandwich Composites." In ASME 1999 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/imece1999-0499.

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Анотація:
Abstract In the current work, sandwich composite structures with innovative constructions referred to as Z-pins, or truss core pins are investigated, in conjunction with traditional honeycomb and foam core sandwich constructions, such that they exhibit enhanced transverse stiffness, high damage resistance and furthermore, damage tolerance to impact. While the investigations pertaining to low velocity impact have appeared recently in Vaidya et al. 1999, the current paper deals with compression-after-impact studies conducted to evaluate the residual properties of sandwich composites “with” and “without” reinforced foam cores. The resulting sandwich composites have been investigated for their low velocity (< 5 m/sec) impact loading response using instrumented impact testing at energy levels ranging from 5 J to 50 J impact energy. The transverse stiffness of the cores and their composites has also been evaluated through static compression studies. Compression-after-impact studies were then performed on the sandwich composites with traditional and pin-reinforcement cores. Supporting vibration studies have been conducted to assess the changes in stiffness of the samples as a result of the impact damage. The focus of this paper is on the compression-after-impact (CAI) response and vibration studies with accompanying discussion pertaining to the low velocity impact.
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2

Leshchynsky, Volf, Oleksandra Bielousova, and Anatoli Papyrin. "Cold Spray and Reaction Sintering of Ti-TiAl3 Composite Coatings." In ITSC2015, edited by A. Agarwal, G. Bolelli, A. Concustell, Y. C. Lau, A. McDonald, F. L. Toma, E. Turunen, and C. A. Widener. ASM International, 2015. http://dx.doi.org/10.31399/asm.cp.itsc2015p0015.

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Анотація:
Abstract Recently a Ti–TiAl3 metal–intermetallic laminate (MIL) composite attracts growing attention because they have potential application in honeycomb or sandwich components of airplanes and as biomaterial with good bio-compatibility. Of the available processing techniques, diffusion bonding of elemental titanium and aluminum foils is an effective low-temperature method to synthesize the composite, allowing growth of the intermetallic layer. However, application of assembling and multi-pass cold rolling operations leads to fact that this technology is complex and expensive. The use of Cold Spray technology instead of aluminum foils utilization and multi-pass cold rolling to produce the Ti–TiAl3 MIL composites is believed to be more effective. However, reaction diffusion kinetics of Ti-Al particulate composite differs from that of classical MIL composite and needs to be studied. The task of this paper is to define microstructural changes of Tl-TiAl3 composite coating during cold spraying and reaction sintering. The optical microscopy, SEM, EDS, X-ray and microhardness examinations are presented and discussed.
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3

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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Анотація:
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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4

Nagesh, Athreya, Ola Rashwan, and Ma’moun Abu-Ayyad. "Optimization of the Composite Airplane Fuselage for an Optimum Structural Integrity." In ASME 2018 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/imece2018-88215.

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Анотація:
The newly developed airplanes are using composite laminates to replace the metal alloys for different components, such as the fuselage and the wings. The major advantage of the composite materials is to reduce structural weight which results in reducing the fuel consumption. The aim of this project is to investigate the structural integrity of an airplane fuselage, which uses various types of carbon composite laminates under the static loading of the cabin pressurization. The research is performed using the finite element method and the HYPERMESH commercial software with a composite tool to change the thickness and the orientation of carbon fiber laminates used in the facesheet of the sandwich structure. Three different orientations/stacking sequence of the HexPly 8552 AS4 carbon fibers with two honeycomb cores: Hexagonal Al and Nomex. The results show that the composite material using the HexPly 8552 carbon fiber oriented at angle 30 and angle 45 and the Nomex Honeycomb core of a total laminate thickness of 15.875mm outperform all other thicknesses and orientations in regards to the static loading failure.
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