Relevant bibliographies by topics / Composite Laminate

Contents

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

Academic literature on the topic 'Composite Laminate'

Author: Grafiati
Published: 4 June 2021
Last updated: 26 July 2025

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Journal articles on the topic "Composite Laminate"

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Fakhruddin, Muhammad, Maskuri Maskuri, Elka Faizal, Bayu Pranoto, Hangga Wicaksono, and Hilmi Iman Firmansyah. "Pengaruh Perlakuan Permukaan Pengikatan Terhadap Sifat Mekanik Komposit Serat Kaca Dengan Laminasi Almunium." Jurnal Energi dan Teknologi Manufaktur (JETM) 4, no. 02 (2021): 27–32. http://dx.doi.org/10.33795/jetm.v4i02.79.

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Fiber metal laminates or commonly known as fiber metal laminates (FML) are composite structures made by combining 2 layers of material as the outer layer with the core material. The outer layer of this composite is called the laminate. Generally, laminated composites are produced by joining techniques under solid-state conditions, such as diffusion bonding, extrusion, friction-stir welding, and roller welding. In this study, glass fiber composites with aluminum lamination were made using the vacuum assisted resin infusion (VARI) method, using epoxy resin. The surface treatment of the aluminum
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Zhang, Chun Hua, Jin Bao Zhang, Mu Chao Qu, and Jian Nan Zhang. "Toughness Properties of Basalt/Carbon Fiber Hybrid Composites." Advanced Materials Research 150-151 (October 2010): 732–35. http://dx.doi.org/10.4028/www.scientific.net/amr.150-151.732.

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Basalt fiber and carbon fiber hybrid with alternate stacking sequences reinforced epoxy composites have been developed to improve the toughness properties of conventional carbon fiber reinforced composite materials. For comparison, plain carbon fiber laminate composite and plain basalt fiber laminate composite have also been fabricated. The toughness properties of each laminate have been studied by an open hole compression test. The experimental results confirm that hybrid composites containing basalt fibers display 46% higher open hole compression strength than that of plain carbon fiber comp
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bin Yaakob, Mohd Yuhazri, T. T. T. Jennise, H. Sihombing, Qumrul Ahsan, S. T. W. Lau, and Mohd Imran bin Ghazali. "Gravity Effects on the Density of Laminated Composite due to the Differences in Angle Cured." Applied Mechanics and Materials 465-466 (December 2013): 81–85. http://dx.doi.org/10.4028/www.scientific.net/amm.465-466.81.

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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 especially for developing Small and Medium Industry (SMI). 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
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Junaedi, H., and T. A. Sebaey. "Carbon-Aramid Fiber/Epoxy Hybrid Composite Laminates with the Presence of Defect: An Experimental Study." Journal of Physics: Conference Series 2805, no. 1 (2024): 012008. http://dx.doi.org/10.1088/1742-6596/2805/1/012008.

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Abstract Carbon-Aramid fiber-reinforced epoxy has been used extensively in the aerospace and automobile industries. The combination of high-strength carbon fiber and the high toughness of aramid fiber is believed to be beneficial to the structural behavior of composites. In the current study, Aramid fiber was sandwiched between carbon fiber layers to maintain high strength and toughness simultaneously. The behavior of the laminate with the presence of an open hole and single-edge notch was investigated. For justification, the response of the hybrid laminate was compared with two other laminate
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Dibyajyoti, D., and B. Alfia. "Review on laminated composite plates." Proceedings of the 12th Structural Engineering Convention, SEC 2022: Themes 1-2 1, no. 1 (2022): 83–88. http://dx.doi.org/10.38208/acp.v1.477.

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A composite material is a combination of different material which can be assembled to provide required engineering properties like bending, buckling, stiffness etc. It can give better properties than those of individual components. A lamina is the building block of modern composite laminated structures. A lamina is also known as a ply, or a layer. A laminate has several layers of lamina, or laminae. Since the early years of engineering, various types of laminated composite materials have been used in various engineering fields, such as in aerospace, military and automotive industries that are
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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
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Ramadhan, Redha Akbar, Muhamad Giri Suada, and Hendri Syamsudin. "A FINITE ELEMENT ANALYSIS OF CRITICAL BUCKLING LOAD OF COMPOSITE PLATE AFTER LOW VELOCITY IMPACT." Jurnal Teknologi Dirgantara 18, no. 2 (2020): 195. http://dx.doi.org/10.30536/j.jtd.2020.v18.a3328.

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Composite is a material formed from two or more materials that macroscopically alloyed into one material. Nowadays, composite has been generally applied as lightweight structure of aircraft. This is due to the fact that composites having high strength-to-weight ratio. It means the composites have the capability to take on various loads, despite their lightweight property.Laminate composite is one type of composite that has been generally used in aircraft industries. This type of composite is susceptible to low-velocity impact induced damage. This type of damage can be happening in manufacture,
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Bir, Amarpreet S., Hsin Piao Chen, and Hsun Hu Chen. "Optimum Stacking Sequence Design of Composite Sandwich Panel Using Genetic Algorithms." Advanced Materials Research 585 (November 2012): 29–33. http://dx.doi.org/10.4028/www.scientific.net/amr.585.29.

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In the present study, both critical buckling load maximization and face-sheet laminate thickness minimization problems for the composite sandwich panel, subjected to bi-axial compressive loading under various imposed constraints have been investigated using genetic algorithms. In the previously published work, the optimization of simple composite laminate panels with only even number of laminae has been considered [1, 3]. The present work allows the optimization of a composite sandwich panel with both even and odd number of laminae in the face-sheet laminates. Also, the effects of the bending-
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Mujahid, Yasir, Nabihah Sallih, Mazli Mustapha, Mohamad Zaki Abdullah, and Faizal Mustapha. "Effects of Processing Parameters for Vacuum-Bagging-Only Method on Shape Conformation of Laminated Composites." Processes 8, no. 9 (2020): 1147. http://dx.doi.org/10.3390/pr8091147.

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Complex composite structures manufactured using a low-pressure vacuum bag-only (VBO) method are more susceptible to defects than flat laminates because of the presence of complex compaction conditions at corners. This study investigates the contribution of multivariate processing parameters such as bagging techniques, curing profiles, and laminate structures on laminates’ shape conformation. Nine sets of laminates were produced with a concave corner and another nine sets with a convex corner, both with a 45° inclined structure. Three-way analysis of variance (ANOVA) was performed to quantify t
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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 (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 theo
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Dissertations / Theses on the topic "Composite Laminate"

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Adams, David Bruce. "Blending Methods for Composite Laminate Optimization." Thesis, Virginia Tech, 2002. http://hdl.handle.net/10919/34815.

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Composite panel structure optimization is commonly decomposed into panel optimization subproblems, with specified local loads, resulting in manufacturing incompatibilities between adjacent panel designs. Using genetic algorithms to optimize local panel stacking sequences allows panel populations of stacking sequences to evolve in parallel and send migrants to adjacent panels, so as to blend the local panel designs globally. The blending process is accomplished using the edit distance between individuals of a population and the set of migrants from adjacent panels. The objective function eva
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Palazzetti, Roberto <1984&gt. "Electrospun nanofibrous interleaves in composite laminate materials." Doctoral thesis, Alma Mater Studiorum - Università di Bologna, 2013. http://amsdottorato.unibo.it/5245/1/Tesi.pdf.

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The present work aims for investigate the influence of electrospun Nylon 6,6 nanofibrous mat on the behavior of composite laminates. The main idea is that nanofibrous interleaved into particular ply-to-ply interfaces of a laminate can lead to significant improvements of mechanical properties and delamination/damage resistance. Experimental campaigns were performed to investigate how nanofibers affect both the static and dynamic behavior of the laminate in which they are interleaved. Fracture mechanics tests were initially performed on virgin and 8 different configuration of nanomodified speci
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Palazzetti, Roberto <1984&gt. "Electrospun nanofibrous interleaves in composite laminate materials." Doctoral thesis, Alma Mater Studiorum - Università di Bologna, 2013. http://amsdottorato.unibo.it/5245/.

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The present work aims for investigate the influence of electrospun Nylon 6,6 nanofibrous mat on the behavior of composite laminates. The main idea is that nanofibrous interleaved into particular ply-to-ply interfaces of a laminate can lead to significant improvements of mechanical properties and delamination/damage resistance. Experimental campaigns were performed to investigate how nanofibers affect both the static and dynamic behavior of the laminate in which they are interleaved. Fracture mechanics tests were initially performed on virgin and 8 different configuration of nanomodified speci
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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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Schmidt, Andrew S. (Andrew Stephen). "Three-dimensional analysis of composite laminate edge effects." Thesis, McGill University, 1995. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=22674.

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In this study, the edge effects of composite laminates are investigated mathematically. The presence of stress singularities at the ply interfaces along the free edges is studied. The importance of determining all terms, including interlaminar stresses, in investigating the failure of composite plates is also shown. The simple composite plate, the pin-loaded composite plate, and the bolt-loaded composite plate are analyzed three-dimensionally.<br>A new "slice" model is developed to simulate the simple composite plate. Three-dimensional finite element analysis is performed with the "slice" mode
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Adams, David Bruce. "Optimization Frameworks for Discrete Composite Laminate Stacking Sequences." Diss., Virginia Tech, 2005. http://hdl.handle.net/10919/28631.

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Composite panel structure optimization is commonly decomposed into panel optimization subproblems, with specied local loads, resulting in manufacturing incompatibilities between adjacent panel designs. Using genetic algorithms to optimize local panel stacking sequences allows panel populations of stacking sequences to evolve in parallel and send migrants to adjacent panels, so as to blend the local panel designs globally. The blending process is accomplished using the edit distance between individuals of a population and the set of migrants from adjacent panels. The objective function evaluati
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Soremekun, Grant A. E. "Genetic Algorithms for Composite Laminate Design and Optimization." Thesis, Virginia Tech, 1997. http://hdl.handle.net/10919/36699.

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Genetic algorithms are well known for being expensive optimization tools, especially if the cost for the analysis of each individual design is high. In the past few years, significant effort has been put forth in addressing the high computational cost GAs. The research conducted in the first part of this thesis continues this effort by implementing new multiple elitist and variable elitist selection schemes for the creation of successive populations in the genetic search process. The new selection schemes allow the GA to take advantage of a greater amount of important genetic information that
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Hepworth, Ammon Ikaika No Kapono. "Methods to Streamline Laminate Composite Design, Analysis, and Optimization." BYU ScholarsArchive, 2010. https://scholarsarchive.byu.edu/etd/2405.

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Advanced composite materials have seen major market growth in recent years due to their high strength and low weight properties. These materials are often made using a process that creates a composite laminate by stacking several composite layers together. However, the design, analysis and optimization of laminate composite materials are often a labor intensive process when done manually. This thesis discusses CAD independent algorithms that are integrated into commercial CAD tools to streamline these processes. Methods have been developed to automatically create 3D ply geometry for a laminate
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Barbero, Ever J. "On a generalized laminate theory with application to bending, vibration, and delamination buckling in composite laminates." Diss., Virginia Polytechnic Institute and State University, 1989. http://hdl.handle.net/10919/54484.

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In this study, a computational model for accurate analysis of composite laminates and laminates with including delaminated interfaces is developed. An accurate prediction of stress distributions, including interlaminar stresses, is obtained by using the Generalized Laminate Plate Theory of Reddy in which layer-wise linear approximation of the displacements through the thickness is used. Analytical, as well as finite-element solutions of the theory, are developed for bending and vibrations of laminated composite plates for the linear theory. Geometrical nonlinearity, including buckling and post
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Timarci, Taner. "Vibrations of composite laminated cylindrical shells." Thesis, University of Nottingham, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.283227.

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Books on the topic "Composite Laminate"

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BridgeComposites, LLC. Laminate specification and characterization: Composite bridge decking. U.S. Department of Transportation, Federal Highway Administration, Highways for LIFE, 2012.

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Martin, Roderick H. Delamination failure in a unidirectional curved composite laminate. National Aeronautics and Space Administration, Langley Research Center, 1990.

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Toledano, A. A composite plate theory for arbitrary laminate configurations. Office of Naval Research, 1985.

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C, Chamis C., and United States. National Aeronautics and Space Administration., eds. Composite laminate tailoring with probabilistic constraints and loads. NASA, 1990.

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C, Chamis C., Minnetyan L, and United States. National Aeronautics and Space Administration., eds. Prediction of composite laminate fracture: Micromechanics and progressive fracture. National Aeronautics and Space Administration, 1996.

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Murthy, P. L. N. Free-edge lamination: Laminate width and loading conditions effects. National Aeronautics and Space Administration, 1987.

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Murthy, P. L. N. Free-edge lamination: Laminate width and loading conditions effects. National Aeronautics and Space Administration, 1987.

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Murthy, P. L. N. Free-edge lamination: Laminate width and loading conditions effects. National Aeronautics and Space Administration, 1987.

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Murthy, P. L. N. Free-edge lamination: Laminate width and loading conditions effects. National Aeronautics and Space Administration, 1987.

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George C. Marshall Space Flight Center., ed. The effects of embedded internal delaminations on composite laminate compression strength: An experimental review. National Aeronautics and Space Administration, George C. Marshall Space Flight Center, 1994.

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Book chapters on the topic "Composite Laminate"

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Gooch, Jan W. "Composite Laminate." In Encyclopedic Dictionary of Polymers. Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-6247-8_2745.

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Hanifan, Ron. "Composite Laminate Drawings." In SpringerBriefs in Applied Sciences and Technology. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-06983-8_7.

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Hollaway, L. "Laminate theory: macroanalyses of composite laminates." In Polymer Composites for Civil and Structural Engineering. Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-011-2136-1_3.

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Mittelstedt, Christian. "Laminate and Sandwich Beams." In Mechanics of Composite Structures. Springer Berlin Heidelberg, 2025. https://doi.org/10.1007/978-3-662-70788-3_23.

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Mittelstedt, Christian. "Higher-Order Laminate Theories." In Mechanics of Composite Structures. Springer Berlin Heidelberg, 2025. https://doi.org/10.1007/978-3-662-70788-3_11.

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Jia, Zehui, Lingwei Xu, Shuangkai Huang, Haoran Xu, Zhimo Zhang, and Xu Cui. "Preparation and Impact Resistance of Carbon Fiber Reinforced Metal Laminates Modified by Carbon Nanotubes." In Lecture Notes in Civil Engineering. Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-1260-3_27.

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AbstractFiber reinforced metal laminates (FMLs) are a kind of interlaminar hybrid composites made of metal sheets and fibers alternately stacked and cured at a certain pressure and temperature. In this paper, through the simulation of ABAQUS finite element software and recording the change of projectile velocity, the energy loss of projectile is calculated and the impact resistance is judged. Through the comparison of three groups of simulation experimental results, the energy absorbed by carbon fiber reinforced metal laminate is about 300 times that of aluminum alloy plate, which fully shows
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Mittelstedt, Christian. "Static and Dynamic Laminate Problems." In Mechanics of Composite Structures. Springer Berlin Heidelberg, 2025. https://doi.org/10.1007/978-3-662-70788-3_8.

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Mittelstedt, Christian. "Mechanics of a Laminate Layer." In Mechanics of Composite Structures. Springer Berlin Heidelberg, 2025. https://doi.org/10.1007/978-3-662-70788-3_6.

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Öchsner, Andreas. "Composite Laminate Analysis Tool—CLAT." In Advanced Structured Materials. Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-32390-4_7.

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Öchsner, Andreas, and Resam Makvandi. "Composite Laminate Analysis Tool—CLAT." In A Numerical Approach to the Classical Laminate Theory of Composite Materials. Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-32975-3_3.

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Conference papers on the topic "Composite Laminate"

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Burnett, Michael, and Michael Dearman. "Development of Allowables for Composite Wrinkles." In Vertical Flight Society 73rd Annual Forum & Technology Display. The Vertical Flight Society, 2017. http://dx.doi.org/10.4050/f-0073-2017-12173.

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Wrinkles in composite structure have been a source of concern since the first structural laminates were developed. Identified as out of plane distortions in the fibers of composite laminates, wrinkles are known to dramatically reduce laminate strength. To address these issues, an experimental investigation was undertaken to determine the critical characteristics of wrinkles as related to the static strength of composites. The critical characteristics include wrinkle type, wrinkle aspect ratio, and wrinkle depth. Resulting characterizations were used to determine design allowables for further a
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Mejdi, Abderrazak, Bryce Gardner, and Chadwyck Musser. "Comprehensive Modeling Approach for High-Frequency Structural Properties and Noise Transmission of Composite Panels." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10069.

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This paper addresses the modeling of the thick uniform or general composite laminate and sandwich structures commonly used for helicopter construction to support the fast and accurate modelling of such structures for high frequencies using SEA. For laminated composites, each layer of the lamina is described by a Reissner-Mindlin displacement field leading to equilibrium relations accounting for membrane, transverse shearing, bending and full inertial terms. The sandwich model adheres to the sandwich panels' assumptions and uses a discrete displacement field for each layer, also allowing for ou
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Conklin, Craig, Darryl Toni, and Arild Barrett. "Composite Laminate Resin Pooling Defect Strength Reduction Quantification." In Vertical Flight Society 81st Annual Forum and Technology Display. The Vertical Flight Society, 2025. https://doi.org/10.4050/f-0081-2025-147.

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Composite materials have long been used in rotorcraft structural applications due to their high strength-to-weight ratio. However, they can also be prone to unique types of defects such as resin pooling, porosity, and delamination which can impact their structural performance. Resin pooling can occur when excess resin accumulates in certain areas of the composite laminate. This paper presents a method of finite element analysis to quantify the effect of the resin lens on the structural strength of a specific laminate. This method was used to successfully validate the structural integrity of se
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Baliashvili, Giorgi, Sophiko Kvinikadze, Tamar Iashvili, Davit Tsverava, and Aleksandre Vanishvili. "DEVELOPMENT OF METAL-POLYMER LAMINATE WITH HIGH MECHANICAL PROPERTIES." In SGEM International Multidisciplinary Scientific GeoConference 24. STEF92 Technology, 2024. https://doi.org/10.5593/sgem2024/6.1/s24.04.

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Basalt fiber-reinforced metal-polymer composites represent a cutting-edge class of materials that merge the robustness of metal with the pliability of polymer. Originating from natural volcanic rocks, basalt fibers possess remarkable mechanical properties, such as high tensile strength, resistance to extreme temperatures, and chemical inertness. Integrating basalt fibers into a polymer matrix like epoxy or thermoplastic resins significantly boosts the composite's resistance to dynamic impacts and its energy absorption capacity. The metal component ensures structural integrity and strength, whi
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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. Ashto
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Akter, Rizwana, and Oliver J. Myers. "Fabrication of a 3D Bistable Composite." In ASME 2020 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/smasis2020-2365.

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Abstract Bistable composites have created much attention in engineering applications because of its ability to sustain two stable shapes. A systematic layup of carbon fiber reinforced polymer (CFRP) causes bistability in a lamina. The transition from one stable shape to another is occurred by snap-through and snap-back process. Due to their adaptive nature a lot of study has been conducted on a 2D laminate for over the past 30 years. However, fabrication of a 3D model that exhibits bistability is yet to be explored. In this research we fabricated a 3D bistable composite structure having two pa
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Hayashi, Katsura, Tadashi Nagasawa, Keisaku Matsumoto, and Shinya Kawai. "Nano-Silica Composite Laminate." In 2013 IEEE 63rd Electronic Components and Technology Conference (ECTC). IEEE, 2013. http://dx.doi.org/10.1109/ectc.2013.6575686.

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Sharma, Sanjay, and Dennis A. Siginer. "VARTM Process Improvement for Repeatable and Improved Mechanical Properties of Composite Laminates." In ASME 2009 International Mechanical Engineering Congress and Exposition. ASMEDC, 2009. http://dx.doi.org/10.1115/imece2009-12593.

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Quality of laminates produced by Seeman Composite Resin Infusion Molding Process (SCRIMP) is studied by comparing their Fiber Volume fraction and void content. SCRIMP is a variant of Vacuum Assisted Resin Transfer Molding (VARTM). Manufacturing process parameters are then identified and varied to study the impact on mechanical properties of laminated composites. Modification to SCRIMP is carried out by infusing the resin under additional pressure. Optimal process parameters for this modified SCRIMP process are suggested to yield laminates that are repeatable and consistent in quality. Void con
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SNYDER, ALEXANDER D., ZACHARY J. PHILLIPS, and JASON F. PATRICK. "SELF-HEALING OF WOVEN COMPOSITE LAMINATES VIA IN SITU THERMAL REMENDING." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35785.

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Fiber-reinforced polymer composites are attractive structural materials due to their high specific strength/stiffness and excellent corrosion resistance. However, the lack of through-thickness reinforcement in laminated composites creates inherent susceptibility to fiber-matrix debonding, i.e., interlaminar delamination. This internal damage mode has proven difficult to detect and nearly impossible to repair via conventional methods, and therefore, remains a significant factor limiting the reliability of composite laminates in lightweight structures. Thus, novel approaches for mitigation (e.g.
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ZHAO, BANGHUA, and WENBIN YU. "MULTISCALE ANALYSIS OF COMPOSITE STRUCTURES AND MATERIALS BY SWIFTCOMP MOBILE APP." In Proceedings for the American Society for Composites-Thirty Seventh Technical Conference. Destech Publications, Inc., 2022. http://dx.doi.org/10.12783/asc37/36504.

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SwiftComp mobile App based on iOS and Android platforms has been developed to analyze composite materials using Google’s Flutter framework and dart language. It is a user-friendly App for computing properties for composites by utilizing SwiftComp capability. The App is currently available to download on iOS AppStore and Google Play Store. The current functionalities of this App include the calculation of lamina stress/strain, lamina engineering constants, laminate stress/strain, laminate plate properties, laminate 3D properties, and composite properties for unidirectional fiber reinforced comp
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Reports on the topic "Composite Laminate"

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Liberson, Alexander S., Brian R. Walsh, Michael J. Roemer, Gyaneshwar P. Tandon, and Ran Y. Kim. Damage Quantification in Electrically Conductive Composite Laminate Structures. Defense Technical Information Center, 2009. http://dx.doi.org/10.21236/ada498157.

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2

Emerson, Ryan P., Jason Cain, Michael Simeoni, and Bradley Lawrence. Processing and Evaluation of 3D-Reinforced Needled Composite Laminate. Defense Technical Information Center, 2012. http://dx.doi.org/10.21236/ada568531.

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3

J. Lucero, F. Hemez, T. Ross, K.Kline, J.Hundhausen, and T. Tippetts. Uncertainty Quantification of Composite Laminate Damage with the Generalized Information Theory. Office of Scientific and Technical Information (OSTI), 2006. http://dx.doi.org/10.2172/884685.

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4

Harris, James, Yossef A. Elabd, Eugene Napadensky, and Paul Moy. Thermal Processing and Composite Laminate Formation of Ionic Block Copolymers for Protective Clothing. Defense Technical Information Center, 2002. http://dx.doi.org/10.21236/ada410616.

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5

Hsiung, L. In-Situ TEM Observations of Strain-Induced Interface Instability in TiAl/Ti3Al Laminate Composite. Office of Scientific and Technical Information (OSTI), 2003. http://dx.doi.org/10.2172/15007359.

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6

Roach, Dennis Patrick, and Kirk A. Rackow. Development and utilization of composite honeycomb and solid laminate reference standards for aircraft inspections. Office of Scientific and Technical Information (OSTI), 2004. http://dx.doi.org/10.2172/918390.

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7

Perez-Rivera, Anthony, Jonathan Trovillion, Peter Stynoski, and Jeffrey Ryan. Simulated barge impacts on fiber-reinforced polymers (FRP) composite sandwich panels : dynamic finite element analysis (FEA) to develop force time histories to be used on experimental testing. Engineer Research and Development Center (U.S.), 2024. http://dx.doi.org/10.21079/11681/48080.

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The purpose of this study is to evaluate the dynamic response of fiber-reinforced polymer (FRP) composite sandwich panels subjected to typical barge impact masses and velocities to develop force time histories that can be used in controlled experimental testing. Dynamic analyses were performed on FRP composite sandwich panels using the finite element method software Abaqus/Explicit. The “traction-separation” law in the Abaqus software is used to define the cohesive surface interaction properties to evaluate the damage between FRP composite laminate layers as well as the core separation within
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Roach, Dennis, and Thomas Rice. A Quantitative Assessment of Advanced NDI Techniques for Detecting Flaws in Composite Laminate Aircraft Structures. Office of Scientific and Technical Information (OSTI), 2014. http://dx.doi.org/10.2172/1762097.

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9

Lee, Wall, and Burch. L52333 NDE and Inspection Techniques Applied to Composite Wrap Repairs. Pipeline Research Council International, Inc. (PRCI), 2012. http://dx.doi.org/10.55274/r0010468.

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The objective includes: Assess commercially available inspection methods to validate integrity of composite repair systems. Identify applicability to inspect composite overwrap and parent metal for both onshore and sub-sea pipelines (where information is available). Identify sources of data to include other users of composite materials(aerospace/aircraft, naval/ship repairs). Identify procedures and technologies to assess inspection effectiveness and provide a gap analysis. Interface with other PRCI projects on long-term testing of composite repairs and other joint industry projects on composi
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10

Sandhu, Ranbir S., Robert L. Sierakowski, and William E. Wolfe. Cumulative Damage Modelling in Composite Laminates. Defense Technical Information Center, 1988. http://dx.doi.org/10.21236/ada198282.

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