Relevant bibliographies by topics / Laminated

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

Academic literature on the topic 'Laminated'

Author: Grafiati
Published: 4 June 2021
Last updated: 15 June 2025

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Journal articles on the topic "Laminated"

1

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 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. The aim of the research was to investigate the density property of the thermosetting laminated composite by curing the laminate at different angle using vacuum bagging technique. From the testing, SN6 had the same density value with control sample, SN1 that had value of 1.46 g/cm3.
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Marzuki, Haslan Fadli Ahmad, Mawarni Mohamad, Engku Ahmadhilmi Engku Ubaidillah, et al. "Effect of Anodizing on Strength of Carbon-Fibre Aluminium-Laminated Composites." Advanced Materials Research 748 (August 2013): 216–21. http://dx.doi.org/10.4028/www.scientific.net/amr.748.216.

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Fibre-metal-laminated composites that consist of aluminium and carbon fibre/epoxy was widely use in engineering fields such as in aerospace and civil application. An issue arise for this laminate systems is that aluminium surfaces must be treated to ensure the effectiveness of load transfer mechanism in the interfacial region. In this research, the effect of anodized layer on the aluminium surface towards strength of the carbon fibre-aluminium-laminated composites was studied. Aluminium 6061-T6 was anodized using phosphoric acid as electrolyte and different anodizing voltage to produce different surface morphology. The surface roughness and morphology were determined via Atomic Force Microscopy and its wettability was determined by Static Contact Angle. Then, anodized aluminium was laminated with carbon fibre/epoxy system via vacuum bagging techniques. It shows that the strength of laminated composite with anodized surface increases up to 26% compared to laminates without anodized surfaces. Furthermore, the failure mechanism of laminated composite with anodized surface resulted in partial adhered failure instead of adhesive failure. These show that anodized surfaces contributes to the effectiveness of load transfer mechanism in fibre-metal-laminates composites.
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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 thickness variation and spring effect of laminated composites. The analysis for concave and convex corners showed that the bagging techniques is the main factor in controlling the laminate thickness for complex shape applications. The modified (single) vacuum-bag-only (MSVB) technique appeared to be superior when compared to other bagging techniques, exhibiting the least coefficients of variation of 0.015 and 0.016 in composites with concave and convex corners, respectively. Curing profiles and their interaction with bagging techniques showed no statistical significance in the contribution toward laminate thickness variation. The spring effect of laminated composites was investigated by calculating the coefficient of determination (R2) relative to that of the mold. The specimens exhibited a good agreement with R2 values ranging from 0.9824 to 0.9946, with no major data offset. This study provides guidelines to reduce thickness variations and spring effect in laminated composites with complex shapes by the optimum selection of processing parameters for prepreg processing.
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Mori, Ryota, Hiroshi Miyamura, Shiomi Kikuchi, et al. "Hydrogenation Characteristics of Mg Based Alloy Prepared by Super Lamination Technique." Materials Science Forum 561-565 (October 2007): 1609–12. http://dx.doi.org/10.4028/www.scientific.net/msf.561-565.1609.

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In order to improve the hydrogenation property of Mg/Ti laminate composite, Ni was added as a third element. Hydrogen storage properties of the laminated Mg/Ti/Ni alloy films were studied. Laminated Mg/Ti/Ni multilayer alloy films were prepared by cold rolling of stacked Mg, Ti and Ni under ambient conditions. The stacked foils were subjected to repetition of rolling and stacking, resulting in super-laminated foils with the thickness less than 0.3mm, containing more than 15000 layers. Microstructures of the super-laminates were studied by scanning electron microscopy and X-ray diffractometry. Their hydrogenation behaviors were investigated by use of a Sieverts type apparatus. The hydrogen storage capacity (H/M) of the laminate with composition Mg/Ti/Ni=9.0/0.9/0.1 amounted H/M=1.6 at 573K, 0.4MPa. Initial activation property was improved by controlling the amount of Ni appropreately.
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Zhang, Guo Li, Fu You Wang, Jia Lu Li, Guang Wei Chen, and Li Chen. "The Effect of Splicing Shape and Interval Length on the Failure Mode of Laminated Composites under Tensile Condition." Applied Mechanics and Materials 44-47 (December 2010): 2922–25. http://dx.doi.org/10.4028/www.scientific.net/amm.44-47.2922.

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This paper presents an experimental investigation on the failure modes of glass fiber reinforced 2D woven fabric with ladder splicing laminate composites. On the basis of [0/0/+45/90/-45/90]s ply sequence, six kinds of laminated performs with different splicing interval lengths which were 4mm, 8mm, 12mm respectively and two different splicing shape which were ladder splicing and double vertical line splicing, and a kind of laminated perform with continuous laminates of 2D glass fiber woven fabric were made. By means of RTM molding technology, the technological parameters of RTM processing were designed as follows: injection temperature was 25°C, injection duration time was 180min and injection pressure was 0.4MPa, the epoxy resin based 2D glass fiber woven fabric RTM laminated specimen were prepared. According to the GB/T 1447-2005 and GB/T 1449-2005standard test method, the failure modes of 2D glass fiber woven fabric laminated RTM specimen were tested. Results show that the failure modes of laminate composites manifest as rapid damage in the form of line inlay mode and wedge shape mode at 4mm interval length condition, and accumulating failure in the form of inlay layer slippage - fiber pulled out mode and fiber fracture - splicing layer deboning mode at 12mm interval length. Otherwise, all fracture position of splicing laminates occurs at the site of splicing line because of the concentration of tensile stress.
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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 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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Joshi, S. P., and N. G. R. Iyengar. "Optimal Design of Laminated Composite Plates Under Axial Compression." Transactions of the Canadian Society for Mechanical Engineering 9, no. 1 (1985): 45–50. http://dx.doi.org/10.1139/tcsme-1985-0007.

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The study is carried out for the optimum design of laminated fiber reinforced composite plates, subjected to multiple in-plane loadings. Angle-ply laminates with orthotropic laminae are considered. Thickness of plies and corresponding fiber orientations are incorporated as design variables. The constrained optimization problem is transformed into a series of unconstrained optimization problems, using an interior penalty function approach. The results have been obtained for different aspect ratios and uniform biaxial in-plane loading ratios. This study shows that the fiber orientations of the plies near mid-plane have little effect on the optimum design. There exists a particular fiber orientation angle for the over all thickness of laminate, which results in the optimum design for a plate of a given aspect ratio under a given set of loadings.
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Huang, Zheng-Ming, K. Fujihara, and S. Ramakrishna. "Bending Failure Characterisation of Laminated Beams with Braided Fabric Reinforcement." Advanced Composites Letters 12, no. 3 (2003): 096369350301200. http://dx.doi.org/10.1177/096369350301200301.

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An experimental procedure has been performed in this work to characterise failure behaviour of braided fabric reinforced composite laminates subjected to flexural load. The material system used was carbon/epoxy. The laminated beams were made using eight layers of diamond braid reinforcement. Two braiding angles, i.e., 5° and 15°, were applied. Six beams with laminate arrangements of [5/5/5/5/5/5/5/5], [15/15/15/15/15/15/15/15], [5/5/15/15/15/15/5/5], [15/15/5/5/5/5/15/15], [5/5/15/15/5/5/15/15], and [15/15/5/5/15/15/5/5] were loaded under 4-point bending to their ultimate failure, where the braiding angle is measured with respect to the beam axis. Bending stiffnesses, ultimate bending strengths, and load-deflection curves of the tested beams were reported. It was found that all the bending failures of the laminated beams were initiated from their top surface inwards, as a consequence of an excessive compressive stress in the beam cross-section. Further evidence in failure mechanism was recognised through a matrix combustion and fabric peeling out technique. It was shown that after the bending test the only un-failed lamina in some of the laminates was its bottom surface ply. The evidence clearly indicates that the neutral plane in a laminated beam keeps shifting once a lamina in the laminate has failed. The failed lamina in the laminate can hardly sustain any additional load. Thus the present experiment confirms that a total stiffness discount should be adopted in the layer-by-layer progressive failure analysis of a laminated composite. Using this discount procedure, a simulation method is highlighted in the paper. The predicted load-deflection curves up to the third-ply failure agreed reasonably with the measured ones.
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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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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 subjected to high temperatures. Thermal stress caused due to change in temperature, increase in temperature causes the changes in material properties of a plate which in turn complicates the analysis and design and may affect the structure also. Therefore, the analysis of thermal stress in design of structure is very important. A critical review of available literature for the prediction of the behaviour of laminated composites under thermal conditions is carried out and summarized. This work attempts to review the studies carried out from 2000 on laminated composite plates by representing classification based on Classical laminate plate concept, First order shear deformation theory, Higher order shear deformation theory, Layerwise theory and Thermal stress on laminated plates.
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Dissertations / Theses on the topic "Laminated"

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Austin, Travis R. "Laminated PAINT." VCU Scholars Compass, 2018. https://scholarscompass.vcu.edu/etd/5462.

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Though we may not perceive it, we are surrounded by material-in-flux. Inert materials degrade and the events that comprise our natural and social environments causally thread into a duration that unifies us in our incomprehension. Sounds reveal ever-present vibrations of the landscape: expressions of the flexuous ground on which we stand.
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Жигилій, Дмитро Олексійович, Дмитрий Алексеевич Жигилий, Dmytro Oleksiiovych Zhyhylii, Володимир Андрійович Хворост, Владимир Андреевич Хворост, and Volodymyr Andriiovych Khvorost. "Laminated composite plates." Thesis, Видавництво СумДУ, 2004. http://essuir.sumdu.edu.ua/handle/123456789/22944.

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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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Deka, Lakshya J. "Quasi-static and multi-site high velocity impact response of composite structures." Birmingham, Ala. : University of Alabama at Birmingham, 2008. https://www.mhsl.uab.edu/dt/2008p/deka.pdf.

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Thesis (Ph. D.)--University of Alabama at Birmingham, 2008.<br>Additional advisors: Krishan K. Chawla, Derrick Dean, Jong-Eun Kim, Mark Weaver. Description based on contents viewed Feb. 9, 2009; title from PDF t.p. Includes bibliographical references.
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Zehnder, Nino. "Global optimization of laminated structures /." Zürich : ETH, 2008. http://e-collection.ethbib.ethz.ch/show?type=diss&nr=17573.

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English, Brian Alan. "Laminated Gas Generator Actuator Arrays." Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/14074.

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Existing microactuator limitations prevent control of small-scale, spin-stabilized vehicles. These applications require actuators insensitive to shock that have forces on the order of Newtons and millisecond control periods. This research presents batch-fabrication lamination approaches for the realization of large arrays of high-impulse, short-duration gas generator actuators (GGAs), and system implementation approaches to integrate these GGAs into a small-scale, spin-stabilized projectile for the purpose of generating steering forces on the projectile. Electronic packaging and MEMS processing are combined to batch-fabricate millimeter-scale GGAs insensitive to large shocks. Robust, prefabricated thermoplastic and metal films are patterned by laser machining or photolithography, and multilayer devices are assembled by adhesive lamination. The GGAs remained operational after 10,000 g shocks. Optimized design and propellant selection enables control of the force profile and actuation timing. Rapid force rise times are achieved using appropriately selected solid propellants and specially designed hot-wire igniters that create a larger combustion fronts. By reshaping the combustion profile of the solid propellant, tens of Newtons are generated within milliseconds. In addition to force control, the timing of the force application was controllable to within 1 ms for optimized GGAs. Performance results demonstrate that GGA actuator arrays actuate within appropriate timescales and with enough authority to control a 40 mm projectile with a spin rate of 60 Hz. After actuator characterization, GGAs, control electronics, and power supply are mounted into a 40 mm diameter projectile, and a full flight system was flown to demonstrate divert authority of the GGAs.
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Patrick, David G. "Laminated structures for sports mouthguards." Thesis, University of Sheffield, 2005. http://etheses.whiterose.ac.uk/6068/.

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The aims and objectives of this study are to examine the role of mouthguards and the materials that are used for their manufacture, the heating process they undergo during manufacture and how the lamination of different materials into a multi-layered system to form a composite structure may affect the impact absorbing capabilities. The effect of heat on pEVA during the manufacturing process was investigated using an instrumented dropweight impact testing rig and a polariscope to observe internal stress as it was felt that the physical properties of the material could be adversely affected by this part of the process. Laminated structures, using several different materials, (pEVA, PMMA, silicone rubber, synthetic wax, modelling clay, soft denture lining material and a semi-solid synthetic rubber) were tested as it was felt that the lamination of different materials with a range of physical properties would exhibit less deformation and transmit less of the impact energy. To ascertain how a mouthguard may react during an impact event by simulation tests in the impact test rig. Methods: For the heat treatment of pEVA a furnace was used to heat the test material to near its' glass transition temperature (Tg) of 84'C ±3 'C. The material was brought up to Tg and held at that point for 10 minutes. The specimens were then removed from the furnace and allowed to cool to room temperature. Heat treated and non-heat treated samples were placed in a polariscope to observe stress within the material. Dropweight impact tests were conducted on all samples using an instrumented impact testing rig. All samples were circularly clamped and force-time and displacement-time plots obtained. The samples were placed again in the polariscope and any changes in stress were noted. To observe the processing effects of the manufacturing procedure five mouthguards were made on the same cast and were brought to various stages of completion. Different 'lay-ups' of pEVA along with laminations and sandwiches of pEVA, PMMA, silicone rubber, synthetic wax, modelling clay, semi-solid synthetic rubber and denture soft lining were also tested using the dropweight impact tester. For the impact simulation tests samples of 50mm. diameter were placed on top of a PMMA substrate, that was clamped in the impact rig, to see how the test sample would protect the substrate during impact. Results: The Peak Impact Force (PIF) of heat treated pEVA was lower (PIF<140N) than that of untreated pEVA (PIF=160N). The displacement of the heat treated sample during impact increased by 66%, (untreated pEVA>18mm centre displacement, heat treated pEVA >30mm centre displacement). Digital photographic images from the polariscope show that the heat treatment of pEVA virtually eliminates stress and following impact the amount of stress, seen photoelastically, was also reduced. Images of material in the polariscope also indicate that the finishing techniques employed during the manufacturing process have a direct effect on the stress distribution within the mouthguard. A 5mm laminated structure of pEVA, PMMA and silicone rubber was able to absorb more impact energy (PIF = 275N) and exhibited less deformation (1.4mm) than that of a monolithic structure of 5mrn heat treated pEVA (PIF <140N, displacement >30mm). Simulation tests showed that the 5mm. thick pEVA protected the PMMA better (PIF = 325, displacement 6.8mm) than the Imm pEVA (PIF = 340, displacement 7.7mm). Conclusions: The mouthguard forming process has a direct effect on the internal stresses of pEVA and therefore its physical response. When pEVA is laminated with PMMA and silicone rubber the impact absorbing capabilities are better than a monolithic structure of pEVA. Mouthguards for use in contact sports, therefore, should incorporate a laminated section of pEVA, PMMA and silicone rubber. Simulation tests show that 5mm thick samples protect a substrate more effectively than I- 4mm test samples.
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Hassani, Abolfazl. "Bitumin laminated reinforced concrete pavements." Thesis, University of Westminster, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.305266.

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Jeong, Han Koo. "Reliability of laminated composite plates." Thesis, University of Southampton, 1999. https://eprints.soton.ac.uk/21869/.

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This thesis deals with reliability analysis of laminated composite plates subjected to transverse lateral pressure loads. Input parameters to strengths of the plates such as applied transverse lateral pressure loads, elastic moduli, geometric and ultimate strength values of the plates are treated as basic design variables, and specific probability distributions are applied to them to take into account the variability nature of these basic design variables. Based on the statistical information on the basic design variables, these variables are pseudo-randomly generated in accordance with the corresponding probability distributions by using statistical sampling techniques. Generated random values of the basic design variables corresponding to the applied loads, elastic moduli and geometric values are substituted into various laminated plate theories which can accommodate different lamination schemes and boundary conditions to assess the probabilistic strengths of the plates. The limit state equations are developed by using maximum stress, maximum strain, Tsai-Hill, Tsai-Wu, Hoffman and Azzi-Tsai-Hill failure criteria. Calculated probabilistic plate strengths and generated random values of the ultimate strength basic design variables of the plates are substituted into the developed limit state equations to define the failure or survival state of the plates. In solving the limit state equations, structural reliability techniques are adopted and evolved appropriately for the reliability analysis of the plates. Developed reliability analysing algorithms are applied to laminated plates from experiment to check its validity. Finally, the EUROCOMP Design Code is compared with the developed reliability analysis procedures by applying the both approaches to the strengths of laminated plates.
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Bloomfield, Mark William. "Efficient optimization of laminated composites." Thesis, University of Bristol, 2010. http://hdl.handle.net/1983/716153ce-1826-4c80-b7fa-369a29f45a9e.

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Books on the topic "Laminated"

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InformationCentre, Laminated Glass, ed. Laminated glass. Laminated Glass Informantion Centre, 1992.

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Mikhasev, Gennadi I., and Holm Altenbach. Thin-walled Laminated Structures. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-12761-9.

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BARCHARTS, INC. Reflexology-Laminated. QuickStudy, 2014.

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BARCHARTS, INC. Anatomy-Laminated. QuickStudy, 2013.

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Smith, Evelyn E. Laminated Woman. Start Publishing LLC, 2016.

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Virtanen, Pirjo Kristiina. Laminated Poster. Klett (Ernst) Verlag,Stuttgart, 1999.

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McNally & co. [from old catalog] Rand. Rand McNally Laminated Atlanta Map (Laminated Rolled Map). Rand McNally & Company, 1997.

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Borch. Austria Laminated Map. Borch, 2006.

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Berndtson, Berndtson &. Peru Laminated Map. 6th ed. Berndtson & Berndtson, 2005.

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Berndtson;Borch. Aruba Laminated Map. Berndtson/Borch, 2006.

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Book chapters on the topic "Laminated"

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Huang, Minchao, Jianjun Wu, Jian Li, and Yuqiang Cheng. "Simulation of the Heating of Laminated Heat Exchanger Core Under Variable Operating Conditions." In Solar Thermal Thruster. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-7490-6_6.

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AbstractThe laminated heat exchange core is the main part that heats the propellant/working fluid in a solar thermal propulsion (STP) system. In this chapter, through a simulation and analysis of the working process of a heat exchanger core with a laminate structure, the laminate heating characteristics of the STP system under variable operating conditions are obtained.
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Kemp, Alan. "Laminated Sediments." In Encyclopedia of Marine Geosciences. Springer Netherlands, 2014. http://dx.doi.org/10.1007/978-94-007-6644-0_185-4.

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Conway, J. H., and N. J. A. Sloane. "Laminated Lattices." In Grundlehren der mathematischen Wissenschaften. Springer New York, 1988. http://dx.doi.org/10.1007/978-1-4757-2016-7_6.

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Conway, J. H., and N. J. A. Sloane. "Laminated Lattices." In Grundlehren der mathematischen Wissenschaften. Springer New York, 1993. http://dx.doi.org/10.1007/978-1-4757-2249-9_6.

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Conway, J. H., and N. J. A. Sloane. "Laminated Lattices." In Grundlehren der mathematischen Wissenschaften. Springer New York, 1999. http://dx.doi.org/10.1007/978-1-4757-6568-7_6.

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Emary, A. B. "Laminated Components." In Site Carpentry and Advanced Joinery. Macmillan Education UK, 1985. http://dx.doi.org/10.1007/978-1-349-06901-9_20.

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Kumar, Rajesh. "Laminated Sediments." In Encyclopedia of Earth Sciences Series. Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-90-481-2642-2_319.

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Gooch, Jan W. "Laminated, Cross." In Encyclopedic Dictionary of Polymers. Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-6247-8_6761.

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Gooch, Jan W. "Laminated Fabric." In Encyclopedic Dictionary of Polymers. Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-6247-8_6762.

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Gooch, Jan W. "Laminated Glass." In Encyclopedic Dictionary of Polymers. Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-6247-8_6763.

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Conference papers on the topic "Laminated"

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Herman, Mélanie, Christian Hochard, Jean-Marc Besson, Jean-Paul Charles, Nassira Boulebbad-Gomez, and Noël Lahellec. "Development of Techniques for Composite Parts Failure Analysis in Static and Fatigue Mode - Application on Thermoset and Thermoplastic Materials for Rotorcraft Main Rotor Hub Analysis." In Vertical Flight Society 74th Annual Forum & Technology Display. The Vertical Flight Society, 2018. http://dx.doi.org/10.4050/f-0074-2018-12887.

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A model defined at the ply scale to predict the failure of laminated composites for static or fatigue loading is proposed. The model describes the loss of strength in the fiber direction for a significant level of transverse damage. This meso-scale model has been characterized on woven ply laminates used for rotorcraft dynamic components, such as glass/epoxy of Starflex®, carbon fiber/epoxy, and carbon fiber/PEEK of H160 main rotor hub. Failure behavior prediction at coupon level has been validated regarding static and fatigue failure mode in tension for epoxy resin woven ply laminates. Characterizations have been also provided for PEEK resin in balanced woven ply laminate, regarding static or fatigue failure mode. Those activities are crucial to increase the level of confidence in failure model, to rely on virtual testing at coupons level, and to better predict damage and failure at component level. This work intends to support the building block approach during development and certification of such critical applications for rotorcraft.
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He, Xiaoling. "Nonlinear Thermal Vibration Analysis of a Thin Laminated Microstructure." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-85326.

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Nonlinear deformation can occur in thin laminated structures due to thermal fields present in the laminates. Thermally induced laminate response in buckling and vibration has been previously studied in nonlinear dynamics by approximations that compromise the total energy of the system. In this paper, this problem is studied based on the nonlinear thermal mechanical analysis of a thin laminated structure using a Galerkin type approach, with total energy conservation. Equation of motion for laminates in orthotropic and isotropic structures in thermal buckling response in a simply supported boundary condition is obtained in a decoupled modal form of the Duffing equation, with consideration of both non-uniform in-plane and transverse temperature variations, in steady state and transient state. Analysis is made for the thermal buckling behavior of an isotropic laminate with respect to the steady-state and transient thermal fields. In particular, chaos and instability due to the transient thermal field are investigated.
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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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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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Ye, R., H. S. Tzou, and J. Tani. "Control of Semicircular Shells With Thermal Shock and Mechanical Excitations." In ASME 1996 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/imece1996-0937.

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Abstract Shell-type components and structures are very common in many mechanical and structural systems, e.g., nozzles, pressure vessels, storage tanks, rockets, antenna dishes, etc. Modeling and analysis of adaptive piezothermoelastic shell laminates represents a high level of sophistication and complexity. Accordingly, a numerical method is developed to investigate the complicated temperature, mechanical, and control interactions of piezothermoelastic shell composites in this study. Constitutive equations, governing equations, and boundary conditions of a generic piezothermoelastic continuum are defined first. Strain-displacement relations, electric field-potential relations, thermal gradient-temperature relations of laminated shell composites are then defined. A new piezothermoelastic composite triangular shell finite element is formulated and developed. Matrix equations of the piezothermoelastic shell laminate are derived, in which mechanical, temperature, and electric force vectors are also defined. The electric force vector is used in active control of the shell laminates. Finite element solutions of a piezoelectric laminated composite plate are compared with experimental data and numerical solutions first. Distributed control of a piezoelectric laminated semicircular shell subjected to mechanical and temperature (thermal shock) excitations is investigated and control effectiveness evaluated.
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Allen, David H., and Chad R. Searcy. "Modeling Damage Accumulation in Laminated Composites Subjected to Impact." In ASME 2000 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/imece2000-1962.

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Abstract Because of their high strength-to-weight ratio, laminated composites continue to be an attractive alternative to conventional monolithic media in the design of impact resistant structures. Unfortunately, the high cost of production has been a major limiting factor in the usage of laminated composites in design applications. Contributing to this cost is the complexity of the design process, which calls for an increased number of parameters necessary for the optimal design of impact resistant laminated composite structures. One way to address this complexity is through the use of damage models. Properly constructed damage models have the potential to reduce the cost of design and promote the increased usage of laminated composites in design applications. This paper demonstrates the effective use of cohesive zone modeling to determine the optimal laminate configurations for impact resistant composites. A nonlinear finite element algorithm equipped with a micromechanically-based viscoelastic cohesive zone model is used to predict the cumulative damage in composite laminates subjected to impact. Several composite layups have been studied to determine an optimal design configuration. Some analytical predictions have been provided for a comparison with the numerical results.
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Jung, Dongho, Hyeonju Kim, Moonho Tak, Kyungjae Lee, and Taehyo Park. "Dynamic Structural Analysis of a Large-Diameter Riser Consisting of Laminated Composite Material With a Hybrid Numerical Scheme." In ASME 2013 32nd International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/omae2013-10868.

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A hybrid numerical scheme is developed to analyze the structural dynamic behavior of a large-diameter riser made of a laminated composite material. The global dynamic behavior of the riser, considered as a beam element subjected to a wave and current, is solved with the finite element analysis method in the time domain. The equivalent elastic modulus of a laminated composite riser for the global dynamic analysis is calculated from the stress-strain relation of a laminate structure with a different elastic modulus. For elements in large displacement and stresses estimated from the dynamic analysis, local structural analysis is performed with the finite element analysis method to examine the structural safety of the laminates of the composite riser, which is considered as a hexahedral element. The developed hybrid numerical tool can contribute to structural safety verification of large-diameter risers composed of laminated composites.
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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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BUENROSTRO, JAVIER, SANDI G. MILLER, TRENTON M. RICKS, and J. MICHAEL PERIERA. "DAMAGE INITIATION OF CONTINUOUS FIBER LAMINATED THERMOPLASTIC COMPOSITES." In Proceedings for the American Society for Composites-Thirty Eighth Technical Conference. Destech Publications, Inc., 2023. http://dx.doi.org/10.12783/asc38/36674.

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The use of advanced thermoplastic composites (TPC) for structural applications in the aerospace and automotive industries has grown increasingly popular due to their high performance, high manufactured part output, and sustainability. Advanced manufacturing processes of thermoplastic composites allow for the building of complex optimized structural geometries with both continuous and discontinuous fibers. With more complex parts and processes comes the need for established qualification methodologies. Characterization of damage evolution from different manufacturing processes needs to be further explored to better understand the behavior of TPC for aerospace environments. Investigation into the differences in the damage behavior of continuous and discontinuous laminated TPC in tension and compression is important for aerospace applications where impact and crush damage is likely. Experiments using continuous fiber laminated IM7/PEKK TPC, [±45]4s specimens loaded in tension and [90/0]3s specimens loaded in compression, are performed to obtain stress vs strain curves with Digital Image Correlation (DIC) and acoustic emission (AE) transducers to monitor damage initiation and evolution. Next, interrupted low-cycle mechanical tests are performed on [±45]4s laminates with optical microscopy in between cycles to support characterization and understanding of the relevant damage mechanisms needed for material models. The damage mechanisms in laminated composites are of interest to better understand the effects of different fiber architectures on the laminate scale behavior, which can be used to calibrate continuum damage mechanics models.
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Viviani, L. "Fractional viscoelastic characterization of laminated glass." In AIMETA 2022. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902431-18.

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Abstract. Glass façades are often required to withstand against explosive events due to premeditated or accidental causes. Laminates made by glass plies bonded by thin polymeric foils (laminated glass) need to be used to avoid catastrophic breakage. The paradigmatic case study considered is that of a rectangular three-layer laminate, made of two glass plies, modelled as Kirchhoff-Love plates, sandwiching a thin viscoelastic polymeric interlayer. Its time-dependent response under the action of a blast wave is described via fractional calculus operators, whose main advantage is that only two material constants are needed for an exhaustive characterization. The dynamic equations are treated à la Galёrkin and their integration in time relies on the Grünwald-Letnikov approach. The fractional characterization presents noteworthy advantages from a computational point of view. We find that the maximum stress peak is mildly affected by the viscosity of the interlayer, which instead dictates the subsequent rebounding oscillations.
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Reports on the topic "Laminated"

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Harris, Chioke, Heather Goetsch, and Swaroop Atnoorkar. Cross-Laminated Timber Workshop: Pathways and Priorities for Cross-Laminated Timber Building Systems. Office of Scientific and Technical Information (OSTI), 2022. http://dx.doi.org/10.2172/1868051.

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Burov, A., and V. Lebedev. Impedances of Laminated Vacuum Chambers. Office of Scientific and Technical Information (OSTI), 2011. http://dx.doi.org/10.2172/1021483.

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Hammerand, Daniel Carl. Laminated composites modeling in ADAGIO/PRESTO. Office of Scientific and Technical Information (OSTI), 2004. http://dx.doi.org/10.2172/919118.

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Thies, Walter G., and Rona N. Sturrock. Laminated root rot in western North America. U.S. Department of Agriculture, Forest Service, Pacific Northwest Research Station, 1995. http://dx.doi.org/10.2737/pnw-gtr-349.

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Swab, Jeffrey, and Parimal Patel. Fracture Analysis of a Laminated Window Structure. DEVCOM Army Research Laboratory, 2022. http://dx.doi.org/10.21236/ad1161194.

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Shafer, R. E. Coupling impedance of laminated magnets in the booster. Office of Scientific and Technical Information (OSTI), 1986. http://dx.doi.org/10.2172/5334017.

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Wang, A. S. Fracture Analysis of Matrix Cracking in Laminated Composites. Defense Technical Information Center, 1985. http://dx.doi.org/10.21236/ada170486.

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Hartman, Quinn. MIL-STD-1660 Testing of Laminated Wood Pallets. Defense Technical Information Center, 1989. http://dx.doi.org/10.21236/ada244939.

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Folias, E. S. Failure in Laminated Composite Plates Containing a Hole. Defense Technical Information Center, 1990. http://dx.doi.org/10.21236/ada227307.

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Kotov, Nicholas A. Engineering of High-Toughness Carbon Nanotubes Hierarchically Laminated Composites. Defense Technical Information Center, 2012. http://dx.doi.org/10.21236/ada564047.

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