Relevant bibliographies by topics / Laminated materials Mechanical properties

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  2. Dissertations / Theses
  3. Books
  4. Book chapters
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Academic literature on the topic 'Laminated materials Mechanical properties'

Author: Grafiati
Published: 4 June 2021
Last updated: 31 January 2023

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Journal articles on the topic "Laminated materials Mechanical properties"

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Ramful, Raviduth. "EVALUATION OF THE MECHANICAL PROPERTIES OF BAMBUSA BAMBOO LAMINATES THROUGH DESTRUCTIVE TESTING." Journal of Green Building 13, no. 4 (September 2018): 1–18. http://dx.doi.org/10.3992/1943-4618.13.4.1.

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In this research study, Bambusa ssp, the utilized species of bamboo, was rendered into a more versatile construction material in the form of laminates. The laminated specimens were manufactured using simplified processing methods according to the ASTM D3039 and ASTM D143 standards. Polyvinyl acetate was the adhesive used between the 2-ply laminate. The mechanical properties of the specimens were evaluated through tensile, compressive and bending strength tests according to set standards on the Testometric M500-50AT Universal Testing Machine. The tensile strength of laminated bamboo was comparable to that of redwood, spruce, cedar and pine. The ratio of compressive strength of parallel to perpendicular fibers in compressive tests was in a close range to that of poplar, fir and pine. The correlation in compressive strength values between bamboo and wood confirmed the inherent anisotropic nature of both plant materials.
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You, Feng Xiang, Fei Zhang, and Buo Lei Zuo. "Spline-Based Finite Element Analysis in Composite Laminates Mechanical Properties." Applied Mechanics and Materials 138-139 (November 2011): 673–80. http://dx.doi.org/10.4028/www.scientific.net/amm.138-139.673.

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The geometric parameters of the composite laminate in the engineering structure tend to have random properties. It is of great significance on how to study sensitivity of random parameters of laminated plates and carry on the optimized analysis to the parameteranalys when accurately estimating the reliability of structural design. According to the first order shear deformation theory, by using the spline finite element method, we can infer and the establish a laminated plate vibration equation, the stiffness matrix, mass matrix, proportional damping matrix, before making solution of the antisymmetric laminated plates response sensitivity formula, and analyzing the normal displacement, the sensitivity, the natural frequency of compound materials laminated plate. The Numerical examples verify the effectiveness of this algorithm.
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ALLEN, D. ALBERT, G. RAMANAN, R. R. NEELA RAJAN, and A. K. DARWINS. "Experimental Study on Change in Mechanical Characteristics of E-Glass Fibre Reinforced Epoxy Composite by Adding Carbon Nanotube Layers." Asian Journal of Chemistry 31, no. 6 (April 29, 2019): 1251–54. http://dx.doi.org/10.14233/ajchem.2019.21874.

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Polymer composite reinforced with fiber materials have always proven its superior significant enactment over numerous traditional materials, considering their incomparable strength to weight ratio and stiffness. Carbon nanotubes usage in glass-fiber reinforced polymer has high potential in changing the characteristics of composite laminates. Carbon nanotubes have engrossed composite fraternity in exploring the opportunity of utilizing them as a supplementary reinforcement in fiber reinforced polymer composites. This study examines the mechanical characters of glass-fiber reinforced polymer with and without multi-walled carbon nanotubes (MWCNT). Composite laminated layers are fabricated using epoxy resin without carbon nanotube and with 0.5 and 1.5 % MWCNT. The materials were tested to determine tensile, flexural and compression properties. It is observed that the carbon nanotubes can enhance the mechanical properties in the composite laminates. Composite laminate with 1.5 wt % MWCNT exhibited good mechanical properties compared to that with 0.5 wt % MWCNT and without MWCNT.
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bin Yaakob, Mohd Yuhazri, T. T. T. Jennise, H. Sihombing, N. Mohamad, S. H. Yahaya, and M. Y. A. Zalkis. "Water Absorption and Thickness Swelling of Laminated Composite after Cured at Different Angle." Applied Mechanics and Materials 465-466 (December 2013): 86–90. http://dx.doi.org/10.4028/www.scientific.net/amm.465-466.86.

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Moisture absorption is a very important factor in polymers and composite materials used for hull manufacture and stability in marine environment. High water absorption of the material will affects the mechanical properties and stability in composite. This research is carried out to study the feasibility of the gravity effects on curing position of the laminated composite structures to enhance the curing space needed. Vertical cured laminate having almost similar properties with common horizontal cured laminate able to save much space in composite industry. Horizontal cured laminates filled up spaces in which SMI lack of. Polyesters and E-glass fibers were used as the raw material in this research. Vacuum bagging technique was used to suck out the excess resin during lay-up to avoid any voids and air inside laminate and cured at different angle position in room temperature for 24 hours. Seven samples of laminated composite were fabricated and cut into specific dimension in accordance to ASTM standard. This paper will discuss about the investigation on the water absorption and thickness swelling of the thermosetting laminated composite by curing the laminate at different angle using vacuum bagging technique. From the testing, SN6 and SN7 shows to have good water resistant in physical properties.
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Colvin, G. E., and S. R. Swanson. "Mechanical Characterization of IM7/8551-7 Carbon/Epoxy Under Biaxial Stress." Journal of Engineering Materials and Technology 112, no. 1 (January 1, 1990): 61–67. http://dx.doi.org/10.1115/1.2903188.

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This paper presents the results of a detailed characterization of the relatively new IM7/8551-7 carbon/epoxy material system under conditions of multiaxial stresses applied to both laminae and laminates. IM7 is a high elongation, high strength carbon fiber, and the 8551-7 matrix is a high toughness epoxy resin. The lamina tests provided a failure envelope for combinations of transverse tension or compression and in-plane shear, and illustrated that the matrix dominated strength properties exhibit a strong dependence on the state of stress. The transverse strains at failure were found to be higher than for previous epoxy systems examined, and the shear stress-strain curves showed significant nonlinear behavior. These features apparently contribute to the “toughness” of the resin. Laminated specimens in a quasi-isotropic configuration were tested in tension-tension and tension-compression stress states. In previous work on other fiber/resin systems it has been shown that laminate ultimate failure could be correlated by means of fiber direction strain in a critical ply, independent of matrix cracking and the details of the laminate configuration and state of stress. However, different fiber strain values must be used for tension and compression. The behavior of quasi-isotropic IM7/8551-7 laminates appears to follow the observations noted above, with the important exception that laminate tension failure strain is lower than unidirectional coupon strain. The compression values are significantly higher than seen previously with AS4/3501-4 laminates, but as usual lower than the tension values. The results raise presently unresolved issues about the effect of the resin and possibly the processing variables on the delivered laminate strength.
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Carreño, Fernando, M. Pozuelo, José A. Jiménez, and Oscar A. Ruano. "Bend and Shear Tests: Suitable Methods for Mechanical Characterization of Laminated Composite Materials." Materials Science Forum 539-543 (March 2007): 901–6. http://dx.doi.org/10.4028/www.scientific.net/msf.539-543.901.

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Bend and shear tests were used to characterize the improvement in impact behavior of various ultrahigh carbon steel laminated composites. These tests turned out to deliver much more useful information about the mechanical properties of the laminates than the Charpy impact tests and were especially interesting for characterization of laminates of very high toughness values. The toughness of the various laminates was controlled by the rolling conditions that determined the quality of the bond and the appearance of delamination by the interfaces. The bend test allows determination of yield and maximum stresses, absorbed energy and permits graphical visualization of layer fracture and delaminations as testing proceeds. The shear test allows mechanical characterization of the bond quality between layers, permitting prediction of possible delaminations, and therefore, the mechanical properties of the layered material.
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Fukunaga, Hisao, and Hideki Sekine. "A Laminate Design for Elastic Properties of Symmetric Laminates with Extension-Shear or Bending-Twisting Coupling." Journal of Composite Materials 28, no. 8 (May 1994): 708–31. http://dx.doi.org/10.1177/002199839402800802.

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A laminate design method for elastic properties of symmetric laminates with extension-shear or bending-twisting coupling is presented using lamination parameters which give a complete expression of laminate configurations. The elastic properties of Young's moduli, Poisson's ratios and shear modulus are represented on the lamination parameter plane. A general method is also developed for determining laminate configurations corresponding to lamination parameters. The graphical representation clarifies the relation between laminate configurations and elastic properties. Effects of extension-shear coupling on in-plane elastic properties are discussed. The elastic properties of Young's moduli and shear modulus have the maximum values when the coupling terms vanish. Two design examples are also presented which utilize bending-twisting couplings. One is concerned with the control of a cross-coupling parameter in an aeroelastic tailoring of a composite wing, and the other is concerned with the shear buckling optimization of a symmetric laminated plate.
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Marzuki, Haslan Fadli Ahmad, Engku Ahmadhilmi Engku Ubaidillah, Sivakumar A/l Sivarasa, Mohd Syamsul, and Mariatti Jaafar. "Study on Effect of Fiber Orientation on Flexural Properties of Glass Fiber Reinforced Epoxy Composite Laminates for Structural Applications." Solid State Phenomena 301 (March 2020): 227–37. http://dx.doi.org/10.4028/www.scientific.net/ssp.301.227.

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Composite laminate design is an important procedure in defining the mechanical properties of laminated composite structure to be used in multi-directional service loading application. Composite technologies or manufacturers who is lack of knowledge regarding the importance of laminate design, tend to develop a composite structure that will collapse or fail below the service requirement. The purpose of this study is to determine the effect of fiber orientation on flexural properties of the designed glass fiber reinforced epoxy laminated composite. Six sets of laminates with different fiber orientation and sequence were simulated using CompositeStar© software to determine its flexural properties. Samples were fabricated to verify the simulated data and were tested in accordance to ASTM D2344. Moreover, crack pattern within the samples after the flexural test is studied. From the simulated results, it shows that laminates which have fiber in tri-direction and quasi-direction display a higher flexural modulus and strength compared to laminates with fiber in uni-directional and bi-directional. In addition, data from tested fabricated laminates samples displayed the same modulus patterns against the simulated data, with variants from 8% to 35%. Additionally, it is found that samples with fiber in ±45 direction shows a transverse and shear cracking which prolonged the cracking propagation before the samples show a complete failure.
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Wang, Chuang, Qing Sun, Lang Zhao, Jing Jia, Lixiao Yao, and Zongren Peng. "Mechanical and Dielectric Strength of Laminated Epoxy Dielectric Graded Materials." Polymers 12, no. 3 (March 9, 2020): 622. http://dx.doi.org/10.3390/polym12030622.

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Laminated epoxy dielectric graded material is a commonly used insulating material with broad application prospects in power equipment. The interlaminar interfaces of laminated epoxy dielectric material between different layers form during its lamination process, and these interfaces are the crucial characteristic structures determining the mechanical and dielectric properties of laminated materials. Therefore, in order to gain a thorough understanding of physic properties behind a certain structural motif, it is necessary to study how these interfacial structures influence the mechanical and dielectric performances of graded materials. In this study, double-layered epoxy resin samples with an interlaminar interface are prepared to study their mechanical and dielectric strength. More importantly, the formation mechanism of the interface, as well as its influence on the mechanical and dielectric strength of this laminated material, is discussed. We found that a cross-linking reaction may take place between epoxy resins at the interlaminar interface, and the degree of cross-linking at the interface should be less than that in the bulk. The mechanical strength of the interlaminar interface is weaker than that of the bulk, and it is reduced by less than 40%. Moreover, the interlaminar interface is inclined to trap carriers, which improves the breakdown strength and arc ablation resistance of the laminated material. Our study of interlaminar interface properties could help in designing epoxy dielectric graded materials with better mechanical and dielectric properties.
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Jamaludin, Mohd Ariff, Shahril Anuar Bahari, Mohd Nazarudin Zakaria, and Ummu Amirah Azizan. "Improvement of Binderless Banana Pseudo-Stem Particleboard Properties via Natural Laminating Materials." Solid State Phenomena 305 (June 2020): 23–27. http://dx.doi.org/10.4028/www.scientific.net/ssp.305.23.

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In this study, the first objective was to investigate the basic mechanical and physical properties of the binderless banana pseudo-stem particleboard (BBP) at a targeted density of 650 kg/m3. The second objective was to examine the effect of laminates on the properties of BBP. Three types of BBP were produced, that were oil palm veneer laminated BBP, layered banana leaf laminated BBP, and BBP without lamination. No adhesive was used in the production of the BBP, but for lamination process, cold setting polyvinyl acetate (PVAc) was used. Three tests were conducted which were internal bonding (IB), static bending, and water absorption resistance tests. According to the results, BBP without lamination had the lowest IB. The lowest modulus of rupture (MOR) and lowest modulus of elasticity (MOE) in static bending was also recorded by BBP without lamination. The highest IB, MOR and MOE, were of BBP laminated with oil palm veneer. These values were followed by IB, MOR and MOE of BBP with banana leaf lamination. Highest percentage water absorption (WA) was exhibited by BBP without lamination, followed by BBP laminated with oil palm veneer, and then by BBP laminated with layered banana leaves. The types of BBP significantly influence the MOR and MOE, but did not significantly affect the IB and WA. In general, laminating the BBP using natural layered materials has significantly improved the MOR and MOE.
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Dissertations / Theses on the topic "Laminated materials Mechanical properties"

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Li, Edward. "Characterization of mechanical and fatigue properties for a hybrid titanium composite laminate." Thesis, Georgia Institute of Technology, 1997. http://hdl.handle.net/1853/19897.

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Johnson, David Page. "The effect of specimen size on the mechanical response of laminated composite coupons loaded in tension and flexure." Diss., This resource online, 1994. http://scholar.lib.vt.edu/theses/available/etd-06062008-164926/.

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Zhang, Mei. "The effects of contamination on the mechanical properties of carbon fibre reinforced epoxy composite materials." Thesis, University of Portsmouth, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.299084.

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Rhymer, Donald William. "Fatigue damage mechanisms of advanced hybrid titanium composite laminates." Thesis, Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/18980.

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Appiah, Kwadwo Ampofo. "Microstructural and microanalytical characterization of laminated (C-SiC) matrix composites fabricated by forced-flow thermal-gradient chemical vapor infiltration (FCVI)." Diss., Georgia Institute of Technology, 2000. http://hdl.handle.net/1853/14910.

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Cobb, Ted Quincy Jr. "Optimization of hybrid titanium composite laminates." Thesis, Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/19965.

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Minnaar, Karel. "Experimental and numerical analyses of damage in laminate composites under low velocity impact loading." Diss., Georgia Institute of Technology, 2002. http://hdl.handle.net/1853/15812.

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Subramanian, Suresh. "Effect of fiber/Matrix Interphase on the Long Term Behavior of Cross-Ply Laminates." Diss., This resource online, 1994. http://scholar.lib.vt.edu/theses/available/etd-01252008-165523/.

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Kuriakose, Sunil. "Analysis of damage in composite laminates under bending." Diss., Georgia Institute of Technology, 2002. http://hdl.handle.net/1853/12054.

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Kousourakis, Asimenia, and asimeniak@hotmail com. "Mechanical Properties and Damage Tolerance of Aerospace Composite Materials Containing CVM Sensors." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2009. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20090506.095922.

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The PhD thesis evaluates the mechanical properties and damage tolerance of aerospace carbon/epoxy laminates containing long, narrow interlaminar galleries. The term 'galleries' refers to thin and long holes in a laminate used for the installation of small measuring devices, such as structural health monitoring (SHM) sensors. The galleries considered in this study are similar to those used in a novel SHM system known as 'Comparative Vacuum Monitoring (CVM)'. CVM was developed by the Australian company - Structural Monitoring Systems (SMS) - for damage detection in aircraft structures. CVM is a SHM system that utilises pressure differentials between a parallel series of galleries at atmospheric or low pressure to detect damage initiation and propagation. Thus far, CVM has been used for the monitoring of surface cracks in metallic structures using surface mounted sensors. Recent research has also demonstrated that it may be possible to monitor damage along the bond- line of both metallic and composite joints using CVM. The ability of CVM sensors to detect delamination damage inside composite structures is less well understood. It is envisaged that CVM can be used for the through-life health monitoring of composite aircraft structures prone to delamination damage. However, a major concern with applying CVM to composite laminates is the open-hole design of the galleries that may initiate damage growth under external loading. Material property data, structural tests, and models for predicting the properties of laminates containing galleries is needed before CVM technology can be certified for use in aircraft composite structures. The primary objectives of this PhD thesis are the development of an optimum process method for introducing multiple interlaminar CVM galleries in composite laminates; the development of a validated model for calculating changes to the mechanical properties of laminates containing CVM galleries; and the determination of optimum CVM gallery shape, size and orientation combinations for minimising the effect of the galleries on the mechanical properties of laminates. The effects of the shape, size and orientation of CVM galleries on the mechanical properties of carbon/epoxy laminates are evaluated by an extensive experimental research program, and the results are presented in the thesis. The properties investigated include the in-plane tensile and compressive properties, tensile and compressive fatigue life, through-thickness tensile strength, interlaminar shear strength, mode I and mode II interlaminar fracture toughness, and impact damage resistance. The results from tensile tests on lap-joints and T-joints containing CVM galleries are also presented.
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Books on the topic "Laminated materials Mechanical properties"

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Anthony, Green William, and Mićunović M, eds. Mechanical behaviour of composites and laminates: Proceedings of the European Mechanics Colloquium 214 'Mechanical Behaviour of Composites and Laminates' held in Kupari, Yugoslavia, 16-19 September 1986. London: Elsevier Applied Science, 1987.

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Mechanics of composite materials. 2nd ed. Philadelphia, PA: Taylor & Francis, 1999.

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Soares, Carlos A. Mota, 1945-, Soares Cristóvão M. Mota, Freitas Manuel J. M, and NATO Advanced Study Institute on Mechanics of Composite Materials and Structures (1998 : Troia, Portugal), eds. Mechanics of composite materials and structures. Dordrecht: Kluwer Academic Publishers, 1999.

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Reddy, J. N. Mechanics of laminated composite plates: Theory and analysis. Boca Raton: CRC Press, 1997.

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Introduction to plastics and composites: Mechanical properties and engineering applications. New York: M. Dekker, 1996.

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Ochoa, O. O. Finite element analysis of composite laminates. Dordrecht: Kluwer Academic Publishers, 1992.

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Nayfeh, Adnan H. Wave propagation in layered anisotropic media: With applications to composites. Amsterdam: Elsevier, 1995.

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Bogdanovich, Alexander. Mechanics of textile and laminated composites: With applications to structural analysis. London: Chapman & Hall, 1996.

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Reddy, J. N. A refined shear deformation theory for the analysis of laminated plates. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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1945-, Reddy J. N., ed. Mechanics of laminated composite plates and shells: Theory and analysis. 2nd ed. Boca Raton: CRC Press, 2004.

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Book chapters on the topic "Laminated materials Mechanical properties"

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Lube, Tanja. "Mechanical Properties of Ceramic Laminates." In Key Engineering Materials, 87–96. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-424-3.87.

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Zhang, Tao, Hai Yun Jin, Yong Ian Wang, and Zhi Hao Jin. "The Mechanical Properties of AlN/BN Laminated Ceramic Composites." In Eco-Materials Processing and Design IX, 97–100. Stafa: Trans Tech Publications Ltd., 2008. http://dx.doi.org/10.4028/0-87849-472-3.97.

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Ma, Xiaolong, Chongxiang Huang, Jordan Moering, Mathis Ruppert, Heinz Werner Höppel, Mathias Göken, Jagdish Narayan, and Yuntian Zhu. "Mechanical Properties of Copper/Bronze Laminates: Role of Boundaries." In Heterostructured Materials, 131–56. New York: Jenny Stanford Publishing, 2021. http://dx.doi.org/10.1201/9781003153078-11.

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Jayapriya, J., D. Muruganandam, and C. Balasubramaniyan. "Mechanical Properties of Aluminum Wire-Reinforced GFRP Laminates." In Advances in Lightweight Materials and Structures, 233–41. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-7827-4_23.

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Harr, Michael, Paul Moy, and Jian Yu. "Mechanical Properties of Transparent Laminates Fabricated Using Multi-Material Photopolymer Jetting." In Dynamic Behavior of Materials, Volume 1, 47–51. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-30021-0_8.

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Zuo, Kai Hui, Dong Liang Jiang, Qing Ling Lin, Yu Ping Zeng, and Zhong Ming Chen. "Mechanical Properties of (Al2O3+Ni) and (Al2O3+Ni)/Ni Laminated Materials." In Key Engineering Materials, 1447–50. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-456-1.1447.

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Chen, Zejun, Hongbo Hu, Xia Wu, Minhong Zhou, Kawunga Nyirenda, Qing Liu, Guojun Wang, and Deman Wang. "Effect of Cross Accumulative Roll Bonding Process on Microstructure and Mechanical Properties of Laminated 1100/7075 Composite Sheets." In Proceedings of the 8th Pacific Rim International Congress on Advanced Materials and Processing, 2285–95. Cham: Springer International Publishing, 2013. http://dx.doi.org/10.1007/978-3-319-48764-9_284.

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Ball, A. J., R. Young, and A. Cervenka. "The Effect of Stacking Sequence Upon the Mechanical Properties of Thermoplastic Composite Laminates." In Developments in the Science and Technology of Composite Materials, 1031–36. Dordrecht: Springer Netherlands, 1990. http://dx.doi.org/10.1007/978-94-009-0787-4_149.

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Luo, Liang, Zuo Guang Zhang, Min Li, and Zhen Shen. "The Effect of Rigid Particle Interlayer Toughening on Damage Resistance and Mechanical Properties of Composite Laminate." In Advances in Composite Materials and Structures, 505–8. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-427-8.505.

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Lacroix, Damien, and Josep A. Planell. "Mechanical Properties." In Biomedical Materials, 303–36. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-49206-9_8.

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Conference papers on the topic "Laminated materials Mechanical properties"

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Pipes, R. Byron. "Interlaminar Phenomenon in Composite Materials: 1969–1999." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-1182.

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Abstract The development of multiaxial laminates consisting of layers of collimated, high performance fibers in a polymer matrix provided the opportunity to design material properties for each application. The earliest analytical methods for determining stresses in the individual laminae assumed linear strain variation through the laminate thickness (Kirchhoff assumption). For much of the design work with composite laminates this simplification was both appropriate and convenient. Yet in 1969 it was postulated by the leading engineers and scientists (such as Dr. N.J. Pagano and Dr. J. E. Ashton) that a planar state of stress within each laminae could not exist near a laminate free-edge. The argument rested on the fact that inplane shearing stresses, induced in the angle-ply laminae of a laminate under normal external loads, could not exist at the free-edge. Numerous investigators began analyses of the three-dimensional stress state in finite-width laminates including Pagano, Pipes, Puppo and Evenson. Several important developments came for this early work. First, the interlaminar load transfer mechanism between laminae in finite-width laminates was fully articulated as a boundary-layer phenomenon and the influence of stacking sequence on the sign of the interlaminar normal stress for bidirectional laminates was discovered. The roles of laminate material anisotropy and geometric variables such as laminae-to-laminate thickness and laminae-to-laminate width were clarified. A singularity in the interlaminar normal stress at the free-edge was postulated in this early work. The development of three-dimensional and anisotropic finite-element methods and increases in computation power lead to the further investigation of the afore mentioned phenomenon and to the ability to analyse the three-dimensional state of stress occurring at numerous geometric discountinuities typically found in composite structure. These analyses have confirmed many of the findings of the earlier work and provide powerful tools for investigations required in the future.
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Arıko¨k, Rifat, and Zahit Mecitog˘lu. "Large Deflection of a Laminated Composite Plate With Different Extensional and Flexural Material Properties." In ASME 2010 International Mechanical Engineering Congress and Exposition. ASMEDC, 2010. http://dx.doi.org/10.1115/imece2010-40592.

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This paper presents the large deflection elastic analysis of the hand lay-up composite plates with different extensional and flexural modulus including geometric nonlinearity effects that are taken into account with the von Ka´rma´n large deflection theory of thin plates. Governing equations of the motion are derived by means of the virtual work principle. Then the Galerkin method is applied to reduce the nonlinear coupled differential equations into a nonlinear algebraic equation system. The MATLAB and MATHEMATICA software are used to solve the equation system. Because of the common nonuniformities in hand lay-up fabric laminates such as resin surface layers and unequal layer thickness, the flexural and extensional modulus of such laminated composites are different. By the way, since the bending and in-plane effects are together affect to the nonlinear behavior of a composite laminate, it should give more reliable results when using different flexural and extensional modulus in the analysis. In this study, the results of approximate analysis, ANSYS finite element analysis and experimental study are obtained and compared for a fully-clamped laminated composite plate subjected to a uniform pressure load. The material properties used in the analysis are determined tension and three-point bending tests.
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Nandi, Soumitra, Zahed Siddique, and Cengiz Altan. "A Customization Approach for Design Using Commercially Available Laminated Composite Materials." In ASME 2011 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/detc2011-48461.

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Composite materials can offer wide range of thermo-mechanical properties when designing load bearing components using them. The wide range of properties can be obtained by varying fiber-matrix volumetric ratio. Another advantage of using composite materials in design is that the directional properties of laminated composite materials can be easily manipulated by varying the angle of orientation with respect to the direction of the load. Theoretically it is possible to design composite laminates with any fiber-matrix ratio, and in any orientation. But in practice, only a selective number of laminates with given fiber volume fraction are produced and sold by the companies depending on their market demands. So, it is necessary for a designer to perform the selection of laminates from a list of available composite laminates to make it commercially viable. The manual selection process of composite laminates can be very cumbersome for the designers when multiple design goals need to be satisfied in the load bearing component that is being designed. This paper presents a new customization approach for design of load bearing components where appropriate unidirectional laminated composites can be selected to satisfy multiple property requirements. In this approach, a laminate customization technique is incorporated with a grammatical method that deals with a shape design technique, and loading analysis for the designed shape. A hip-replacement joint is designed using commercially available composite laminates to illustrate the approach.
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Chuang, Shui-Nan. "Probabilistic Analysis for the Mechanical Properties of Cross-Ply Fiber-Reinforced Composite Laminate." In ASME 2006 International Mechanical Engineering Congress and Exposition. ASMEDC, 2006. http://dx.doi.org/10.1115/imece2006-13060.

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A probabilistic micromechanics model had been developed for the unidirectional fiber-reinforced composite material design screening. In which, we used the predicted mechanical properties of IM-7 carbon fiber from the existing IM-7/5250-4 composite material system together with the observed 977-3 matrix mechanical properties to predict the probability density functions for the mechanical properties of IM-7/977-3 unidirectional composite. To include the material design in the structural design process, we had extended the probabilistic analysis to predict the probability density functions for the off-axis mechanical properties. The angle-ply and cross-ply laminates have been used extensively in aerospace structural designs. It is logical to extend the probabilistic analysis to predict the probability density functions for the mechanical properties of the laminated composite. We had provided the probabilistic analysis for a symmetric regular angle-ply laminate of IM-7/5250-4 composite laminate. In this report, we will focus on the probabilistic analysis of symmetric and anti-symmetric regular cross-ply laminates of IM-7/5250-4 fiber-reinforced composite with odd-number plies parallel to and even-number plies perpendicular to the laminate principal axes. These probabilistic micromechanics models provide a design-screening tool to help material producers to eliminate the unnecessary time-consuming and costly material fabrications and to reduce the numbers of testing to a minimum but enough to verify the model prediction. They also provide a structural analysis tool to help the structural designer to manage the structural and material uncertainties during the structural design process. And consequently, it provides a means to accelerate the insertion of materials into AF productions.
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Vinogradov, Aleksandra M. "Buckling Characteristics of Regular and Irregular Asymmetric Laminated Composites." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-0883.

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Abstract The paper examines the effects of composite material properties on the nonlinear buckling response of irregular asymmetric composite structures through the analysis of asymmetric laminated beam-columns composed of an arbitrary number of different material layers. The nonlinear buckling behavior of the structures subjected to combined compression and bending is examined as a function of the number, orientation and stacking sequence of the layers that make up the laminate. The analysis demonstrates that, typically, buckling of asymmetric composites is initiated immediately at the load application, however, under certain conditions, the structures exhibit bifurcation. In such cases, the critical load can be optimized through tailoring the material properties of the laminates.
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Christoph, Jake E., Colin M. Gregg, Jordan R. Raney, and David A. Jack. "Low Velocity Impact Testing of Laminated Carbon Fiber/Carbon Nanotube Composites." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-52984.

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Carbon fiber laminated thermoset composites have become the industry standard for applications dictating a high strength-to-weight ratio. However, the brittle nature of the carbon fiber composite structure limits its energy dissipation characteristics, often leading to catastrophic failure under low energy impact loadings. This research examines the potential effects of including vertically aligned multi-walled carbon nanotube forests within a layered laminate structure with the goal being to increase the energy dissipation of the structure with attention given to the increase in the aerial density as a result of including the insert. These nanotube forests are of interest due to their broader application in coupled scenarios requiring tenability of structural, thermal and electrical properties. These nanotube forests have unique energy dissipative effects due to their hierarchical architecture (see e.g., Dario et al. (2006), Zeng et al. (2010) and Raney et al. (2011)). We synthesize vertically aligned nanotubes (VACNTs) on a single crystalline silicon wafer. After separation with the wafer, the VACNTs are placed within a carbon fiber laminated structure prior to resin infusion using vacuum assisted resin transfer molding (VARTM). Drop tower tests similar to ASTM D7136 are performed on carbon fiber laminates, carbon fiber laminates with nanotube forests, and carbon fiber laminates with several alternative materials. Results show an improved damage tolerance of the laminate with each of the investigated inserts, with the CNT system showing an increase of 13% in mean peak force. These results show a similar improvement to the alternative inserts while maintaining the potential for their broader application as a multifunctional material.
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Tiano, Thomas, Margaret Roylance, Benjamin Harrison, and Richard Czerw. "Intralaminar Reinforcement for Biomimetic Toughening of Bismaleimide Composites Using Nanostructured Materials." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-81689.

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Many conventional composite materials are composed of multiple layers of continuous fiber reinforced resin produced by lamination of b-staged prepreg and subsequent cure. These materials exhibit very high strength and stiffness in the plane, dominated by the properties of the fibers. The Achilles heel of such composites is the interlaminar strength, which is dependent on the strength of the unreinforced resin, often leading to failure by delamination under load. Current methods for increasing the interlaminar shear strength of composites consist of inserting translaminar reinforcement fibers through the entire thickness of a laminated composite, such as z-pin technology developed by Foster-Miller [1]. While effective, this technique adds several processing steps, including ultrasonic insertion of the z-pins into the laminate, subsequently causing a significant cost increase to laminated composites. Described in this paper is a process utilizing single-walled carbon nanotubes (SWNTs) and vapor grown carbon nanofibers as reinforcing elements promoting interlaminar shear strength and toughness in carbon fiber/bismaleimide (BMI) resin composites. The resulting composites mimic the natural reinforcing mechanism utilized in insect cuticles. Three different methods of increasing the affinity of these carbon nanofillers for the BMI matrix were explored. The mechanical properties of these composites were assessed using end notch flexure testing. The results indicated that including nanofiller at the laminae interface could increase the interlaminar shear strength of carbon fiber/BMI composites by up to 58%. SEM micrographs revealed that the nanofiller successfully bridged the laminae of the composite, thus biomimicking the insect cuticle. Composite fabrication techniques developed on this program would have a wide variety of applications in space and aerospace structures including leading and trailing edges of aircraft wings.
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SUN, C. "Characterization of mechanical properties and interlaminar toughnessof laminated composites containing adhesive strips." In 30th Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-1349.

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Ichikawa, Daiki, Masayuki Kitamura, Yuqiu Yang, and Hiroyuki Hamada. "Mechanical Properties of the Multilayer Laminated Intra-Hybrid Woven Fabric Composites." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-37864.

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Generally hybrid composite material is with two or more reinforcements or matrixes. They are referred as hybrid matrix and fiber hybrid. Further it is also included hybrid interface using different materials state of the interface. Therefore high functionality which compensates the disadvantages of each other by a hybrid can be expected. At current study, additionally, various strengthening forms were obtained and spread to textile material with hybrid(s). For example, techniques used in the weft and warp fibers/yarns might be different in making a fabric. It will be referred to as intra-layer hybrid fabric. It means in making fabric. It means that different physical properties due to the loading direction in one layer, the mechanical properties unique variety can be expected. In this study, carbon/glass intra-hybrid woven fabric was used to fabricate fiber reinforced plastic (FRP) composite through hand lay-up method. Then, the investigation on the mechanical property and fracture behaviour was carried out. Tensile test combined with acoustic emission (AE) measurement was conducted in this research. Knee point stress was the main factor of initial damage which discussed with AE characteristics during mechanical test. Due to the difference of energy release from fracture between glass fiber and matrix, the fracture characteristics of composite could be monitored during the test through AE facility. Relation between bundle and cracks inside the materials was examined through optical microscope. Scanning electron microscope observation was also carried out to examine the fracture of materials after testing.
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Filippini, Mauro. "Identification of the Mechanical Properties of Composite Materials by Inverse Analysis." In ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2010. http://dx.doi.org/10.1115/esda2010-25101.

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A procedure based on the principles of inverse analysis has been employed to identify the elastic material parameters and the strength characteristics of epoxy carbon fiber reinforced composite laminates. By adopting a classical optimization algorithm, elasticity parameters are chosen by minimizing the mean squared error between the values predicted by the classical theory of elastic laminates and the experimentally observed ones. The average modulus of the laminate has been calculated from elastic parameters of laminas by implementing the classical equations of anisotropic elasticity in a subroutine, in order to speed up the optimization process. In a similar fashion, even though under strongly simplifying hypothesis, the strength characteristic parameters of laminas have been identified by inverse analysis, with the aim of assessing the strength of the composite laminates in the case of complex stress state.
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Reports on the topic "Laminated materials Mechanical properties"

1

Siegel, R. W., and G. E. Fougere. Mechanical properties of nanophase materials. Office of Scientific and Technical Information (OSTI), November 1993. http://dx.doi.org/10.2172/10110297.

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Solem, J. C., and J. K. Dienes. Mechanical Properties of Cellular Materials. Office of Scientific and Technical Information (OSTI), July 1999. http://dx.doi.org/10.2172/759178.

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Tretiak, Sergei, Benjamin Tyler Nebgen, Justin Steven Smith, Nicholas Edward Lubbers, and Andrey Lokhov. Machine Learning for Quantum Mechanical Materials Properties. Office of Scientific and Technical Information (OSTI), February 2019. http://dx.doi.org/10.2172/1498000.

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Hardy, Robert Douglas, David R. Bronowski, Moo Yul Lee, and John H. Hofer. Mechanical properties of thermal protection system materials. Office of Scientific and Technical Information (OSTI), June 2005. http://dx.doi.org/10.2172/923159.

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Nix, W. D. Mechanical properties of materials with nanometer scale microstructures. Office of Scientific and Technical Information (OSTI), July 1991. http://dx.doi.org/10.2172/5951104.

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William D. Nix. Mechanical Properties of Materials with Nanometer Scale Microstructures. US: Stanford University, October 2004. http://dx.doi.org/10.2172/833870.

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Nix, William D. Mechanical properties of materials with nanometer scale dimensions and microstructures. Office of Scientific and Technical Information (OSTI), August 2015. http://dx.doi.org/10.2172/1235947.

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Clark, Elizabeth J. Molecular and microstructural factors affecting mechanical properties of polymeric cover plate materials. Gaithersburg, MD: National Bureau of Standards, 1985. http://dx.doi.org/10.6028/nbs.ir.85-3197.

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Jo, Hyungyung, Hyeyoung Son, Mitchell Rencheck, Jared Gohl, Devin Madigan, Hugh Grennan, Matthew Giroux, Trevor Thiele-Sardina, Chelsea S. Davis, and Kendra A. Erk. Mechanical Properties of Durable Pavement Marking Materials and Adhesion on Asphalt Surfaces. Purdue University, 2022. http://dx.doi.org/10.5703/1288284317357.

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Mechanical properties of commercially available temporary pavement marking (TPM) tapes and thermoplastic materials used as permanent pavement markings (PPM) were investigated using the non-destructive Tape Drape Test and conventional mechanical testing. The impact of temperature and aging on the adhesion of TPM tapes and thermoplastic PPM applied to asphalt core surfaces with various surface roughness and treatments was determined using a modular peel fixture and shear adhesion tests. The adhesion of TPM tapes to model smooth surfaces decreased as surface temperature was increased from 0 to 40°C (32 to 104°F). For some tapes, reduced adhesion and brittle broken fracture were observed at the lowest investigated temperature of -20°C (-4°F). The adhesion of tapes applied to asphalt decreased significantly within 1 week of aging at -25°C (-13°F). Ghost markings were more likely at higher aging temperatures. For PPM thermoplastics, better adhesion to asphalt was observed for higher application temperatures and rougher surfaces. Asphalt emulsion treatments reduced the adhesion of thermoplastics and increased the likelihood of adhesive failure after 5 months of aging at -25°C (-13°F). More ductile PPM thermoplastic materials had better adhesion to both smooth and rough asphalt surfaces compared to thermoplastic materials with a more brittle mechanical response.
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Westbrook, J. H. Standards and metadata requirements for computerization of selected mechanical properties of metallic materials. Gaithersburg, MD: National Bureau of Standards, 1985. http://dx.doi.org/10.6028/nbs.sp.702.

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