Relevant bibliographies by topics / Laminated plastics

Contents

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

Academic literature on the topic 'Laminated plastics'

Author: Grafiati
Published: 4 June 2021
Last updated: 28 July 2024

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Journal articles on the topic "Laminated plastics"

1

Kormanikova, Eva, Kamila Kotrasova, Jozef Melcer, and Veronika Valaskova. "Numerical Investigation of the Dynamic Responses of Fibre-Reinforced Polymer Composite Bridge Beam Subjected to Moving Vehicle." Polymers 14, no. 4 (February 20, 2022): 812. http://dx.doi.org/10.3390/polym14040812.

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In modern industry, heavy traditional materials are being substituted with light and strong fibre-reinforced polymer composite materials. Bridges and railroads made of composite laminates are considerably affected by traffic loads. Therefore, it is very important to analyse this effect which would find practical applications in engineering designs. This paper explains the theoretical formulation that governs the dynamic response of a composite beam subjected to a moving load. The governing equations for the dynamic effect on the laminated composite bridge beam are explained here. The main theories in the micro–macro modelling of composite laminates are also described in the paper. Within the macro modelling, the Classical Laminate and Shear Deformation Laminate Theory of beams are presented. The symmetric cross-ply laminated bridge, made of boron/epoxy is under consideration. The computational two-dimensional model of the vehicle is adopted. The governing equations for the dynamic effect on the laminated composite bridge beam are explained. The calculation of the time response of the bridge for the characteristic speeds of the vehicle is performed in the environment of the MATLAB software. The maximum dynamic magnification factor for the dynamic analysis of a composite beam is found.
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Luo, Shen-Yi, and Faruk Taban. "Deformation of Laminated Elastomer Composites." Rubber Chemistry and Technology 72, no. 1 (March 1, 1999): 212–24. http://dx.doi.org/10.5254/1.3538791.

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Abstract Flexible elastomer composites subjected to finite deformation are usually associated with significant fiber re-orientation and configuration change which cannot be described by classical composite lamination theory. Utilizing the Lagrangian description and a strain-energy density approach, this work presents a set of 2-D constitutive equations in terms of the overall deformation of laminated composites. This model includes both geometric and material nonlinearities of the laminate. Interlaminar shear deformation is addressed but not studied in this analysis. Theoretical predictions have been compared with the available experimental data about symmetric laminates with various fiber orientations in the finite deformation range. Also, a parametric study has been performed under various ratios of biaxial deformation.
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Evran, Savaş. "Numerical and statistical buckling analysis of laminated composite plates with functionally graded fiber orientation angles." Polymers and Polymer Composites 28, no. 7 (June 26, 2020): 502–12. http://dx.doi.org/10.1177/0967391120936029.

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The aim of this numerical and statistical study was to investigate the buckling analysis of laminated composite plates containing functionally graded fiber orientation angles. The laminated composite plates had functionally graded fiber orientation angles based on Taguchi’s L18 (21 × 32) orthogonal array. The fiber orientation angles were considered to be control factors. Numerical analyses were performed using finite element software ANSYS. The optimum critical buckling load and the effects of fiber orientation angles for maximum data were determined using the analysis of the signal-to-noise ratio. The importance levels of laminates and their percent contribution on the buckling characteristics were calculated using analysis of variance. Regression analysis was employed to investigate the effects of control factors on buckling responses mathematically. The effects of laminate stacking sequence, mesh size, element type, mode number, and boundary condition were carried out using laminates with the optimum levels.
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Lin, Yan Yu, Mei-Chen Lin, Ching-Wen Lou, Yueh-Sheng Chen, and Jia-Horng Lin. "Thermoplastic Laminated Composites Applied to Impact Resistant Protective Gear: Structural Design and Development." Polymers 15, no. 2 (January 6, 2023): 292. http://dx.doi.org/10.3390/polym15020292.

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Laminated composites have been commonly applied to all fields. When made into laminated composites, Kevlar woven fabrics are able to provide the required functions. In this study, two types of TPU are incorporated to improve the intralayer features of Kevlar/TPU laminated composites. Hence, the Kevlar/TPU laminated composites consist of firmly bonded laminates while retaining flexibility of the fabrics. Being the interlayer of the laminated composites, the TPU layer provides adhesion while strengthening the tensile property, dynamic puncture resistance, and buffer strength of Kevlar/TPU laminated composites. The test results indicate that with a blending ratio of two types of TRU being 85/15 wt%, the Kevlar/TPU laminated composites exhibit a tensile strength of 18.08 MPa. When the stacking thickness is 1 mm, the tensile strength is improved to 357.73 N with the buffering strength reaching 4224.40 N. Notably, with a thickness being 1.2 mm, the laminated composites demonstrate a dynamic resistance being 672.15 N. In the meanwhile, functional Kevlar fabrics are allowed to keep the fiber morphology owing to the protection of TPU composite films. Considering the composition of protective gear, Kevlar/TPU laminated composites possess a powerful potential and are worthwhile exploring.
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Parhizgar, S. "Determination of Stiffness Properties of Multi-Ply Cord-Rubber Composites." Tire Science and Technology 17, no. 3 (July 1, 1989): 201–16. http://dx.doi.org/10.2346/1.2141685.

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Abstract The material properties of cord-rubber composites required for finite element analysis of tires are discussed. It is shown that the current experimental methods used in verification of the Laminated Plate Theory have not adequately included the coupling deformations existing in unsymmetrical laminated composites. The importance of these coupling deformations is demonstrated on a 0/90 laminated strip. A special grip system capable of decoupling loads and moments applied to a 0/90 laminated strip is introduced. A procedure for experimental determination of the stiffness constants of 0/90 laminate is given.
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Valot, E., P. Vannucci, and G. Verchery. "Complete In-plane Elastic Characterisation under Tensile Tests of Angle-Ply Laminates Composed of Polymer-Matrix Layers." Polymers and Polymer Composites 10, no. 7 (October 2002): 483–92. http://dx.doi.org/10.1177/096739110201000701.

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In this paper we present a new strategy to completely characterise the in-plane elastic properties of a large range of angle-ply laminates using only unidirectional tests. We consider laminates having the same number of identical plies in the α and – α directions. This new method uses some preceding results found by Verchery for orthotropic laminates, namely the conditions of existence of a specific direction ω, in which the shear-extension coupling is null. The characterisation of the laminate is then made using the results of three tensile tests: two in the orthotropy axes, and the third one in the ω direction, in order to have always a pure one-dimensional state of stress. We show that for the most common unidirectional fibre-reinforced materials, the angle ω is, in most cases, close to the α direction of the fibres. This result permits a complete experimental characterisation of the laminate, which then does not need any a priori knowledge of the elastic properties of the elementary layer. In addition, it provides a simple method to verify the predictions of the laminate behaviour obtained by the Classical Laminated Plate Theory (CLPT) when the elementary layer is completely known. The paper ends with numerical examples and with the results of some experimental tests.
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Huang, Zheng-Ming, X. C. Teng, and S. Ramakrishna. "Fatigue Behaviour of Multilayer Braided Fabric Reinforced Laminates." Polymers and Polymer Composites 13, no. 1 (January 2005): 73–81. http://dx.doi.org/10.1177/096739110501300106.

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In this paper, the fatigue behaviour of the laminated composites made from an epoxy matrix and four layers of flat regular braided carbon fiber fabrics of different braiding angles was investigated experimentally. Three laminate lay-ups were used. They are: [100/100/100/100], [280/100/100/280], and [280/280/280/280], where 100 within the bracket indicates that the single layer braid lamina had a braiding angle of 100 inclined with the longitudinal (loading) direction. The static tensile and tension-tension fatigue tests were conducted for those laminates, and detailed fatigue data are reported in the paper. Failure mechanisms of the tested laminates were also characterized. The stiffnesses and strengths (including static tensile and fatigue strengths) of the [100/100/100/100], [280/100/100/280], and [280/280/280/280] laminates were the highest, intermediate, and the lowest respectively. However, different failure mechanisms were recognized. It was found that under the uniaxial tensile or a high-level fatigue load, the [280/280/280/280] laminate failed catastrophically as a result of fiber breakage nearly across the cross section of the specimen. Delamination was seen only when a low-level fatigue load was applied to the laminate. In the case of the [100/100/100/100] laminate, a laminate longitudinal splitting was the main failure mode. No delamination accompanied the laminate failure. For the [280/100/100/280] laminate, significant delamination was found with any applied load (whether static or tensile fatigue of any load level). Splitting, both across the cross-sectional breakage and longitudinal, were involved in the failure of this combined laminate. These findings provide a useful insight into understanding the fatigue behaviour of braided fabric reinforced laminates.
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Evran, Savaş. "Experimental and statistical free vibration analyses of laminated composite beams with functionally graded fiber orientation angles." Polymers and Polymer Composites 28, no. 7 (June 27, 2020): 513–20. http://dx.doi.org/10.1177/0967391120938210.

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In this experimental and statistical study, free vibration behavior of laminated composite beams with functionally graded fiber orientation angles was investigated under clamped-free boundary conditions. The beams were manufactured using E-glass/epoxy. Fiber orientation angles of the beams were analyzed based on Taguchi’s L9 (33) orthogonal array. The effect of fiber orientation angles and beams with optimum levels were assessed using analysis of signal-to-noise ratio. Significant laminates of the beams and their percent contributions on the free vibration responses were obtained using analysis of variance. According to this study, the increase of fiber orientation angle from 0° to 80° causes a decrease in the fundamental frequency behavior of laminated composite beams. The most effective control factors were found to be the first and the second laminates symbolized as L1 with 85.86% contribution, the third and the fourth laminates symbolized as L2 with 12.29% contribution, the fifth and the sixth laminates symbolized as L3 with 1.84% contribution, respectively. This study can be used as a reference for free vibration analysis of cantilever laminated composite beams made of functionally graded fiber orientation angles as experimentally and statistically.
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Go, Sun-Ho, Min-Sang Lee, Chang-Gi Hong, Lee-Ku Kwac, and Hong-Gun Kim. "Correlation between Drop Impact Energy and Residual Compressive Strength According to the Lamination of CFRP with EVA Sheets." Polymers 12, no. 1 (January 16, 2020): 224. http://dx.doi.org/10.3390/polym12010224.

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Carbon-fiber-reinforced plastic is an important building material; however, its application is limited because of its brittleness, leading to vulnerability under shock. Thus, the strength performance of carbon-fiber-reinforced plastics needs to be improved. Here, the drop impact test was conducted to analyze the impact energy and fracture characteristics of carbon-fiber-reinforced plastics and ethylene vinyl acetate sheets. The compression after impact test was performed to assess the residual compressive strength. The thermal energy generated was measured as change in temperature at the time of fracture to investigate the relationship between thermal and mechanical properties. The impact absorption efficiency of 100% was achieved when the carbon-fiber-reinforced plastics specimen was laminated with four or more sheets of ethylene vinyl acetate. The thermal energy generated during impact, the impact load, and the compression after impact test strength was reduced with the increasing number of laminated ethylene vinyl acetate layers. Our results showed that, by carefully selecting the optimal conditions of fabricating the carbon-fiber-reinforced plastic/ethylene vinyl acetate composites, carbon composite materials can be used for impact mitigation.
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Lee, Sang-Kwon, Sungil Bang, and Jiseon Back. "Effect of laminated angle of carbon fiber on interior noise on an enclosure under center point excitation." Journal of Reinforced Plastics and Composites 38, no. 3 (October 22, 2018): 117–32. http://dx.doi.org/10.1177/0731684418808091.

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This paper presents a novel method to control passively the interior noise of an enclosure such as car cabin by using the movement of the peak level and peak frequency according to the laminated angle of carbon fiber reinforced plastic composite plate. Recently, the use of carbon fiber reinforced plastic laminated plates in a car has been increased in order to reduce the weight of a car. For example, the metal plate roof has been replaced by the carbon fiber reinforced plastic plate roof for weight reduction of an electric vehicle. The characteristics of the interior noise inside of a car made of carbon fiber reinforced plastic plate roof can be changed according to the laminated angle of carbon fiber. In this paper, how this characteristic is changed was studied based on the effect of laminated angle of carbon fiber. In order to perform this study, a closed box with one flexible side wall and five acoustically rigid side walls was modelled as the interior compartment of a car. The flexible side wall of the closed box regards as the roof plate of a car. For the flexible side wall of the closed box, three carbon fiber reinforced plastic plates with different angle-ply (± θ) laminates each other were used. Therefore, three carbon fiber reinforced plastic plates with the fiber lamination angles of [−15/15/15/–15]s, [–30/30/30/–30]s, and [–75/75/75/–75]s were fabricated and used as the flexible side wall of the closed box. How the interior noise inside of the closed box was changed according to the laminated angle was studied by theoretical and numerical methods. For the validation of theoretical and numerical methods, the experimental work was performed. Finally, the carbon fiber reinforced plastic plate roof for a passenger car was numerically simulated, and the effect of the laminated angle on the interior noise was studied.
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Dissertations / Theses on the topic "Laminated plastics"

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Ramakrishnan, Karthik Ram Engineering &amp Information Technology Australian Defence Force Academy UNSW. "Low Velocity Impact Behaviour of Unreinforced Bi-layer Plastic Laminates." Awarded by:University of New South Wales - Australian Defence Force Academy. Engineering & Information Technology, 2009. http://handle.unsw.edu.au/1959.4/43918.

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Low velocity impact behaviour of bi-layered laminates of acrylic and polycarbonate was investigated using a combination of drop tower impact experiments and explicit finite element analysis in LS-DYNA. Material characterisation tests were conducted in tension and in compression to obtain material properties for input to the material model in the numerical analysis. Quasistatic plate bending tests were conducted at different loading rates to compare the quasistatic response of the materials to the impact behaviour. Impact tests on circular plates of monolithic acrylic and polycarbonate were carried out using an instrumented drop weight impact tester. The impact force histories were recorded and a multiparameter approach was used to determine critical energy. Acrylic exhibited radial cracking, spalling and pene- tration while polycarbonate underwent large deformation and failed by dishing and plugging. The damage caused by impact in the bilayered laminate included partial or full delamination at the interface and radial cracks in the acrylic layer. The low velocity impact responses were simulated using 8-noded solid elements in LS- DYNA. A node-splitting technique based on maximum tensile stress failure criterion and an erosion approach based on maximum principal stress criteria was used to model the failure of acrylic. A material model that takes into account the asym- metric behaviour in tension and compression was investigated. The delamination between the acrylic and polycarbonate plate was modelled by a tiebreak contact with a shear strength based failure. The results of the finite element simulations are in good agreement with the experimental data.
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Thielman, Scott C. "Design and optimization of a material property distribution in a laminated composite flywheel /." Thesis, Connect to this title online; UW restricted, 1997. http://hdl.handle.net/1773/7031.

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Daniewicz, David Joseph 1965. "Edge delamination in advanced laminated composites, theory and verification." Thesis, The University of Arizona, 1990. http://hdl.handle.net/10150/277294.

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A damage evolution theory capable of predicting the effects of edge delamination phenomena on composite laminate response is developed. The theory is a mechanics-based formulation which quantifies the damage development of a laminate under general loading, and incorporates it directly to the constitutive behavior of the laminate. The theoretical development introduces a laminate-specific constant φ; the methodology of φ selection is presented for [±15/±50]s, [±45/0/90]s, and [0₂/90₂]s T300 graphite/epoxy laminates. Edge effects are demonstrated by comparing the damage state of the above laminates with and without edge delamination damage. The capability of the theory in predicting the volume scaling effect is shown through consideration of the failure strengths of the [±25/90n]s laminate series.
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Nayfeh, Jamal Faris. "Nonlinear dynamics of composite plates and other physical systems." Diss., This resource online, 1990. http://scholar.lib.vt.edu/theses/available/etd-07282008-135756/.

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Richie, Matthew. "Fatigue Behavior of FRP-Reinforced Douglas-Fir Glued Laminated Bridge Girders." Fogler Library, University of Maine, 2003. http://www.library.umaine.edu/theses/pdf/RichieMC2003.pdf.

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Xu, Han. "Development of FRP-Glulam Panel for Bridge Deck Replacement." Fogler Library, University of Maine, 2001. http://www.library.umaine.edu/theses/pdf/XuH2001.pdf.

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Kalluri, Ravi Shankar. "Failure of transparent polymer composite laminated glass panels under impact loading." Diss., Columbia, Mo. : University of Missouri-Columbia, 2007. http://hdl.handle.net/10355/4902.

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Thesis (M.S.)--University of Missouri-Columbia, 2007.
The entire dissertation/thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file (which also appears in the research.pdf); a non-technical general description, or public abstract, appears in the public.pdf file. Title from title screen of research.pdf file (viewed on March 27, 2008) Includes bibliographical references.
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Botting, Joshua Keith. "Development of an FRP Reinforced Hardwood Glulam Guardrail." Fogler Library, University of Maine, 2003. http://www.library.umaine.edu/theses/pdf/BottingJK2003.pdf.

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Joyce, Peter James. "Experimental investigation of defect criticality in FRP laminate composites /." Digital version accessible at:, 1999. http://wwwlib.umi.com/cr/utexas/main.

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Gamache, Christopher P. "Preliminary Investigation on the Durability of FRP Reinforced Glulam Bridge Girders." Fogler Library, University of Maine, 2001. http://www.library.umaine.edu/theses/pdf/GamacheCP2001.pdf.

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Books on the topic "Laminated plastics"

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1936-, Bentley David J., and Technical Association of the Pulp and Paper Industry., eds. Polymers, laminations, and coatings: A TAPPI Press anthology of published papers, 1986-1991. Atlanta, Ga: TAPPI Press, 1991.

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European, Plastic Laminates Forum (1995 Heidelberg Germany). 1995 European plastic laminates forum: Renaissance Hotel, Heidelberg, Germany, November 15-17. Atlanta, GA: TAPPI Press, 1995.

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Asian International Laminates Symposium (1997 Hong Kong, China). 1997 Asian International Laminates Symposium: November 19-21, 1997, Sheraton Hotel & Towers, Hong Kong, China. Atlanta, GA: Tappi press, 1997.

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European Plastic Laminates Forum (1993 Cologne, Germany). 1993 European plastic laminates forum: Hyatt Regency, Köln, Germany, May 18-20 : course notes. Atlanta, GA: TAPPI Press, 1993.

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Polymers, Laminations and Coatings Conference (1993 Chicago, Ill.). 1993 Polymers, Laminations & Coatings Conference: Hyatt Regency Chicago, Chicago, Illinois, August 29 - September 2. Atlanta, GA: TAPPI Press, 1993.

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Polymers, Laminations and Coatings Conference (1994 Nashville, Tenn.). 1994 Polymers, Laminations & Coatings Conference, Opryland Hotel, Nashville, Tennessee, August 28 - September 1: Proceedings. Atlanta, GA: TAPPI Press, 1994.

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Plastic Laminates Symposium (2000 Atlanta, Ga.). 2000 TAPPI Plastic Laminates Symposium: August 21-23, 2000, Hyatt Regency, Atlanta, GA. Atlanta, GA: TAPPI Press, 2000.

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Kimball, Herrick. Making plastic-laminate countertops. Newtown, CT: Taunton Press, 1996.

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Plastic, Laminates Symposium (1994 Atlanta Ga ). 1994 Plastic Laminates Symposium, Hyatt Regency, Atlanta, Georgia, August 22-25: Proceedings. Atlanta, GA: TAPPI Press, 1994.

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Plastic Laminates Symposium (1996 Atlanta, Ga.). 1996 Plastic Laminates Symposium: Hyatt Regency, Atlanta, GA, August 19-22. Atlanta, GA: TAPPI Press, 1996.

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Book chapters on the topic "Laminated plastics"

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Schneider, F., B. Kirsch, M. Gurka, T. Hermann, J. A. L’huiller, and J. C. Aurich. "Improved Quality of Drilled Holes in Laminated Carbon Fiber Reinforced Plastics via Laser-Preprocessing." In Lecture Notes in Production Engineering, 27–31. Cham: Springer International Publishing, 2013. http://dx.doi.org/10.1007/978-3-319-01964-2_4.

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Paimushin, Vitaly, Andris K. Chate, Sergey Kholmogorov, Maksim Makarov, and Ruslan Gazizullin. "Tension–Compression and Shear of Plane Test Specimens from Laminated Composites with the [90°]s Structure." In Multiscale Buckling Modes in the Mechanics of Fiber-Reinforced Plastics, 93–146. Cham: Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-48216-8_4.

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Nikhamkin, M. Sh, S. V. Semenov, and D. G. Solomonov. "Application of Experimental Modal Analysis for Identification of Laminated Carbon Fiber-Reinforced Plastics Model Parameters." In Proceedings of the 4th International Conference on Industrial Engineering, 487–97. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-95630-5_51.

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Porter, R. J. "Paper for resin bonded paper laminates." In Plastics Additives, 474–84. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5862-6_52.

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Diebold, Michael, Steven De Backer, Philipp M. Niedenzu, Brett R. Hester, and Frank A. C. Vanhecke. "Durability of Paints, Plastics, and Paper Laminates." In Pigments, Extenders, and Particles in Surface Coatings and Plastics, 483–543. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-99083-1_14.

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Shibutani, Yoji, Hiroshi Kitagawa, and Takayuki Nakamura. "Growth of interfacial inhomogeneous deformation in thin laminated material subjected to biaxial tension." In Large Plastic Deformations, 261–69. London: Routledge, 2021. http://dx.doi.org/10.1201/9780203749173-29.

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Owen, D. R. J., and Z. H. Li. "Elasto-Plastic Analysis of Laminated Anisotropic Shells by a Refined Finite Element Laminated Model." In Computational Mechanics ’88, 681–85. Berlin, Heidelberg: Springer Berlin Heidelberg, 1988. http://dx.doi.org/10.1007/978-3-642-61381-4_177.

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Sakai, Masatoshi, Atsuo Inoue, Tatsuyoshi Okamoto, Yuki Joho, Hiroshi Yamauchi, and Kazuhiro Kudo. "Laminated Plastic Electronics:Energy Saving and Low Stress on Environment." In Design for Innovative Value Towards a Sustainable Society, 882–84. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-3010-6_180.

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Soudki, K. A. "Rehabilitation of Structures by Fibre Reinforced Plastic Laminates." In Trends in Structural Mechanics, 125–34. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5476-5_13.

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Diebold, Michael, Steven De Backer, Philipp M. Niedenzu, Brett R. Hester, and Frank A. C. Vanhecke. "Application to Décor Paper for Use in Laminates." In Pigments, Extenders, and Particles in Surface Coatings and Plastics, 649–95. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-99083-1_18.

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Conference papers on the topic "Laminated plastics"

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Suda, Mitsunori, Defang Zhao, Takanori Kitamura, Kanta Ito, Kenji Wada, Zhiyuan Zhang, Yuqiu Yang, and Hiroyuki Hamada. "A New Paper Tube Laminated by Plastics." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-38112.

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Recycled paper and plastics are widely used in current society. Recycled paper is very helpful to reduce waste emissions and energy consumption, saving resource and cost and environment protection. Recycled paper tube is one of the most successful cases in application of recycled paper. Plastics and Recycled paper are excellent choices for packing materials. They are also used to construct temporary structures for both exhibition spaces or for rapid-recovery shelters in emergency operations. As paper tubes are laminated composite materials composited of paperboard which is inherent anisotropy materials, the research on mechanical property and fracture behavior becomes more complicated. In order to analyze deformation and fracture behavior of paper tube and paper tube laminated combined with polymer under lateral compressive load, both the paper tube and hybrid paper tube which was dipped in to the thermosets resin were tested and compared. The energy analysis was also conducted here.
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Teimouri, Hessamodin, Ali Abedian, and Hengameh Farahpour. "The Influence of Fiber/Matrix Debonding on Inelastic Micro-Mechanical Behavior of Cross-Ply IMC Composites." In ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2010. http://dx.doi.org/10.1115/esda2010-25059.

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In this study the effect of stress field on delamination and fiber/matrix debonding in laminated composite panels is investigated from the micro-mechanical point of view by means of 3-D Finite Element Models. Specifically, the behavior of two-layer cross-ply symmetric laminates made up of SCS-6/Ti-24Al-11Nb Intermetallic Matrix Composite (IMC) during cooling from the processing temperature is studied. The results show that large plastic strains occur at the fiber/matrix interface at the fiber end on the laminate free edge which may eventually extend to the interface of the layers of the laminate inflicting delamination damage. This phenomenon is more serious at the corner areas of the laminate. It also can be shown that this situation is more serious for the four-layer laminate compared to the results of two-layer composite.
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Regez, Brad, Ying Zhang, Tsuchin Chu, and Ajay Mahajan. "In-Plane Deformation Measurements Using Digital Image Correlation of Ultrasonic C-Scan Images." In ASME 2003 International Mechanical Engineering Congress and Exposition. ASMEDC, 2003. http://dx.doi.org/10.1115/imece2003-42033.

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The extension of digital image correlation method to ultrasonic C-scan acoustical speckle images of the bulk is presented in this paper. The approach discussed in this paper is ideally suited to composite materials such as particulate composites, fiber-reinforced plastics, and laminated composites. It can also be effectively employed for critical surfaces that are not within view, such as interfaces and back surfaces. Images taken prior to and after deformation are analyzed to estimate a deformation profile from changes in the image. The aim of the method is to find the displacements and strains of small subsets from the second image relative to the first one. This is accomplished by comparing the intensity levels of the subsets in the images. The speed and accuracy of the system is enhanced by the genetic algorithms(GAs) which are used to optimize correlation of images. An ultrasonic C-scan system was used to obtain the intensity images of the front or back surface of an isotropic or composite material. Three experimental tests were conducted to illustrate the application of Ultrasonic C-scan digital image correlation method. These tests include: 1) uniform translation, 2) small angle rotation, and 3) uniform deformation. A laminated carbon/epoxy composite panel (305×305×8 mm) was used for uniform translation and small angle rotation tests. A rubber specimen was used to perform the uniform axial deformation test. The results of correlated displacements (angles) are compared to the actual displacements (angles). The accuracy and applied limitation of the three experiments are also illustrated in this paper.
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Ganesan, R., and A. K. Arumugam. "Effect of Notch Location on the Stress Concentration and Reliability of Notched Composite Laminates Based on a Probabilistic Approach." In ASME 2007 International Mechanical Engineering Congress and Exposition. ASMEDC, 2007. http://dx.doi.org/10.1115/imece2007-41178.

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Composite materials and laminates are being widely used in aerospace and automotive industries due to their less weight to stiffness ratio. Especially the use of composite laminates, made up of Carbon or Graphite Fiber Reinforced Plastics (CFRP/GFRP), in military and commercial aircraft structures has progressed steadily over the past few decades. Drilling holes and making cutouts in these laminates are unavoidable for practical reasons. These holes (or) cutouts introduces stress concentration near the hole (or) cutout edge and reduces the load-bearing capacity of the structure. Cutouts are made at the edges of composite laminates for practical purposes, which is capable of reducing the delamination effect in notched laminates. The stress distribution in notched composite laminates can vary according to the location of the notch in the laminate, which leads to the variation in strength and reliability values of notched laminates. The objective of the present work is to study the effect of notch location on the stress concentration and reliability of notched composite laminates. Composite laminate displays significant variation in material and strength properties and the stress distribution in the laminate becomes stochastic in nature. Thus the notched laminates were analyzed using a stochastic approach and designed based on a reliability-based design approach.
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Hamamoto, Sora, Toshiki Hirogaki, Eiichi Aoyama, Kazuna Fujiwara, and Masashi Taketani. "Drilling Holes in CFRP for Aircraft Using CBN Electroplated Ball End Mill Using Helical Interpolation Motion." In ASME 2023 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2023. http://dx.doi.org/10.1115/detc2023-117499.

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Abstract The demand for carbon-fiber-reinforced plastics (CFRP) has recently increased in various fields. However, few reports consider the wear of machining tools, quality of the machined surface, decrease in the mechanical properties of CFRP by machining temperature, and price of machining tools. Therefore, in this study, we focused on cubic boron nitride (cBN) and developed a novel cBN-electroplated end mill, which can be used to cut and ground without the need for changing tools. In this study, we used a cBN-electroplated ball-end mill to drill holes in CFRP using a ball-end mill and helical interpolation motion. The laminated carbon fibers are delaminated at the entrance and exit of the hole, with the delamination at the exit side investigated using strain gauges. As a result, we found that surface delamination was reduced by decreasing the axial and tangential feed rates and increasing the cutting speed. The timing of the delamination of the machined hole can be examined by comparing and considering the strain gauge and FEM results.
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Panbarasu, K., V. R. Ranganath, and Raghu V. Prakash. "An Investigation on Flexural Fatigue Behavior of CFRP Quasi-Isotropic Laminates." In ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-23685.

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Abstract In this study, AS4/914 grade carbon fibre reinforced plastic (CFRP) laminates with two different quasi-isotropic (QI) layup sequences are compared for their performance under four point bend flexure fatigue loads. The QI laminates were designated and fabricated as Laminate-1 (L1) [0/45/-45/90]2S and Laminate-2 (L2) [0/90/45/-45]2S, respectively. These laminates were designed, such that the 0° layers are placed at a similar position in both the laminate systems by changing the other layers. During the test, load and displacement data was monitored online along with instantaneous number of constant load amplitude (CLA) fatigue cycles to calculate the stiffness degradation. Three load levels of 90%, 80%, and 70% of the ultimate flexure strength (UFS) were chosen for assessing the flexure fatigue behavior of the laminates. A few tests were also attempted under variable amplitude loads: (i) high amplitude cycles followed by low amplitude and (ii) low amplitude cycles followed by high amplitude to examine load sequence effect on fatigue life, if any, as compared to the fatigue life under CLA. It has been observed that the laminate L1 performs better under higher amplitudes, while the laminate L2 shows increased life under lower load and variable amplitudes. The results obtained in the form of data plots and failure modes, supported by microscopic images, are discussed in the paper.
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7

Asanuma, Hiroshi. "Development of Active Laminates and Composites." In ASME 2006 International Mechanical Engineering Congress and Exposition. ASMEDC, 2006. http://dx.doi.org/10.1115/imece2006-14546.

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The present paper describes development of active laminates and composites proposed by Asanuma. The active laminates were successfully made by hot-pressing of an aluminum plate as a high CTE (Coefficient of Thermal Expansion) material, a unidirectional CFRP (Carbon Fiber Reinforced Plastics) prepreg as a low CTE material and an electric resistance heater, and a KFRP (Kevlar Fiber Reinforced Plastics) prepreg as a low CTE material and an insulator between them. Curvature of the active laminate linearly changes only in the fiber direction as a function of temperature, and it was made into complicated forms and their actuation performances were successfully demonstrated. As a high temperature type active laminate, three types of SiC/Al composites, that is, a laminate of continuous-fiber layer and unreinforced one, that of discontinuous-fiber layer and unreinforced one, and that of continuous-fiber layer and discontinuous-fiber one were fabricated, and it became clear that all of the composites curve unidirectionally in the fiber direction, and the curvatures reproducibly change during thermal cycles between room temperature and 813 K. Tensile strength of the combination type is higher than that of the continuous-fiber type, and its curvature exists between the continuous-fiber type and the discontinuous-fiber type.
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Sawant, Sourabh, and Anastasia Muliana. "A Nonlinear Viscoelastic Modeling of Fiber Metal Laminates." In ASME 2007 International Mechanical Engineering Congress and Exposition. ASMEDC, 2007. http://dx.doi.org/10.1115/imece2007-42152.

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A new class of advanced composite materials namely the fibermetal laminates (FMLs) such as ARALL (Aramid Reinforced Aluminum laminate) and GLARE (Glass Reinforced Aluminum laminate) has been developed for primary load bearing components of aircraft fuselage and wings. The FML is composed of alternating layers of fiber reinforced polymer (FRP) and aluminum sheets and shows good fatigue resistance. The metal layers are placed on the top and bottom of the laminate to provide good impact resistance and resistance to extreme environments (moisture, ultraviolet radiation and solvent). Krishnakumar (1994) has provided a survey of extensive works on manufacturing, testing, and modeling of the FMLs. The FMLs exhibit nonlinear viscoelastic and/or plastic behaviors due to the existence of FRP and metal alloy layers. The nonlinearity and time-dependent responses in the FMLs are intensified under high load levels, elevated temperatures, and humid environments. A predictive capability on the overall nonlinear viscoelastic response of the FMLs that recognizes different responses in the FRP and metallic layers becomes necessary. Literature indicates a few advances in this direction by the consideration of the elastic-plastic behavior and the use of classical lamination theory (Chen & Sun, 1989; Hashagen et al., 1995). Pindera et al. (1989) have carried out an experimental investigation of the creep response of ARALL laminates at 121°C. A pronounced viscoelastic behavior is observed in ARALL at stress levels below its proportional limit. Aluminum exhibits a nonlinear viscoelastic behavior while aramid-FRP shows a linear viscoelastic behavior. The classical lamination theory (CLT) was used to model the overall creep response of the laminates.
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9

Gururaja, S., and M. Ramulu. "Failure Analysis of a Fibrous Composite Half-Space Subjected to Uniform Surface Line Load." In ASME 2007 International Mechanical Engineering Congress and Exposition. ASMEDC, 2007. http://dx.doi.org/10.1115/imece2007-42569.

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Uni-Directional Fiber-Reinforced Plastic (UD-FRP) laminates have been modeled previously as an equivalent quasi-homogeneous monoclinic half-space subjected to an inclined line load on the surface using Lekhnitskii’s formulation simulating the orthogonal edge trimming loads in UD-FRPs. In continuation, failure analysis of the aforementioned composite half-space has been carried out in the present investigation based on Tsai-Wu criterion. In particular, the failure behavior of the half-space laminate with respect to the fiber orientation, load inclination angle and spatial coordinates has been examined in detail. The motivation behind such a study lies in correlating the failure behavior of the half-space laminate with the damage progression observed during orthogonal edge trimming experiments. The present work strives at identifying this relationship and in the process, understanding the physics of orthogonal cutting mechanisms in UD-FRP laminates.
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Hosur, M. V., U. K. Vaidya, A. Haque, M. Kulkarni, R. Kulkarni, and S. Jeelani. "Evaluation of Ballistic Impact Damage of Fiber Reinforced Plastic Laminates Bonded by Polycarbonate Facesheets." In ASME 1999 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/imece1999-0210.

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Abstract Fiber reinforced polymer matrix composites are being increasingly used in many applications including aerospace, armored vehicle, marine and sporting industries. They provide the advantage of high specific stiffness and specific strength as compared to conventional metallic materials. However, they are well known by their vulnerability to threats like impact loading that occurs normally in the transverse direction. Hence, there is a need to improve the damage resistance in the transverse direction at minimum weight penalty. In this current investigations, a two component material system made of fiber reinforced laminates bonded by a polycarbonate facesheet was studied. Laminates made of both unidirectional graphite/epoxy prepregs and S2-glass twill weave woven fabric/SC-15 resin systems were used in the study. Specimens of size 304.8 × 304.8 mm were made using different thickness ratios of facesheet and the backing laminate. Three different thicknesses of s2-glass laminates (3.17, 4.31 and 5.71 mm) were used to bond to two polycarbonate sheets of thickness 2.54 and 3.17 mm each. Similarly, three different thickness of graphite/epoxy laminates (2.05, 3.75 and 7.62 mm) were used to bond to polycarbonate facesheet of thickness 1.00, 3.175, and 4.30 mm. The ballistic tests are performed with a space test setup using fragment simulating projectiles(FSP). The ensuing damage was evaluated using ultrasonic C-scan technique using pule-echo immersion method.
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