Relevant bibliographies by topics / Laminated composite cylinder

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
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Academic literature on the topic 'Laminated composite cylinder'

Author: Grafiati
Published: 3 June 2025
Last updated: 13 July 2025

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Journal articles on the topic "Laminated composite cylinder"

1

Teshnizi, S. H. Sharifi, S. S. R. Koloor, G. Sharifishourabi, Amran Bin Ayob, and Yahya Mohd Yazid. "Effect of Ply Thickness on Displacements and Stresses in Laminated GFRP Cylinder Subjected to Radial Load." Advanced Materials Research 488-489 (March 2012): 367–71. http://dx.doi.org/10.4028/www.scientific.net/amr.488-489.367.

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The superior feature of composites such as high stiffness against low density have impelled engineers to use this material in automotive, aerospace and building industries. In the past few decades, composites shell has found applications in storage tanks and transmission pipelines. Designing laminated composite shells is challenging because of the complex mechanical behavior when combining laminate and shell theories. In this paper, the study is focused on the effect of lamina thickness on performance of the GFRP cylinder. For this purpose two 12-ply GFRP cylinders are considered with ply sequences of [0/90/45]s. The lamina thicknesses of the composite shell are assumed to be 0.1, 0.5, 1 and 1.5 mm, to evaluation of the mechanical behaviors of the cylinders and identifying one with the highest strength. The 250 mm diameter cylinders are subjected to a uniform radial patch load. A code is written for the solution based on the shell theory and classical mechanics of laminated composite using MATLAB software. The results are validated by comparing the present results with those found in literature. A good correlation justifies the study being extended to include the study on the effect of ply and shell thickness. The procedure is recommended for design and optimization for strength of various sizes of composite pipes
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Rattanawangcharoen, N., A. H. Shah, and S. K. Datta. "Reflection of Waves at the Free Edge of a Laminated Circular Cylinder." Journal of Applied Mechanics 61, no. 2 (1994): 323–29. http://dx.doi.org/10.1115/1.2901448.

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A wave function expansion method is employed to solve the reflection problem of time-harmonic elastic waves incident upon the free edge of a semi-infinite laminated circular cylinder. Wave functions are obtained using a propagator matrix approach for laminated isotropic cylinders and by a Rayleigh-Ritz type approximation for laminated composite cylinders. The least-square technique as well as the variational method are employed to evaluate the complex amplitudes and the energy flux associated with the reflected waves. To validate the solutions and present algorithm, results are compared with analytical solutions whenever available. Examples include free-end reflection of waves in an isotropic solid rod, a two-layered isotropic cylinder, and a four-ply [ + 15/ −15/ +15/ −15] graphite/epoxy cylinder. Numerical experimentation shows that the least-square method provides poor results for the laminated anisotropic cylinder compared to those obtained through the variational technique.
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Serhat, Gokhan. "Design of Circular Composite Cylinders for Optimal Natural Frequencies." Materials 14, no. 12 (2021): 3203. http://dx.doi.org/10.3390/ma14123203.

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This study concerns optimizing the eigenfrequencies of circular cylindrical laminates. The stiffness properties are described by lamination parameters to avoid potential solution dependency on the initial assumptions of the laminate configurations. In the lamination parameter plane, novel response contours are obtained for the first and second natural frequencies as well as their difference. The influence of cylinder length, radius, thickness, and boundary conditions on the responses is investigated. The lamination parameters yielding the maximum response values are determined, and the first two mode shapes are shown for the optimum points. The results demonstrate that the maximum fundamental frequency points of the laminated cylinders mostly lie at the inner lamination parameter domain, unlike the singly curved composite panels. In addition, the second eigenfrequency shows a nonconvex response surface containing multiple local maxima for several cases. Moreover, the frequency difference contours appear as highly irregular, which is unconventional for free vibration responses.
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Rouhi, Mohammad, Hossein Ghayoor, Suong V. Hoa, and Mehdi Hojjati. "The effect of the percentage of steered plies on the bending-induced buckling performance of a variable stiffness composite cylinder." Science and Engineering of Composite Materials 22, no. 2 (2015): 149–56. http://dx.doi.org/10.1515/secm-2014-0258.

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AbstractThe fiber steering capability of automated fiber placement machines offers the designers more room to fully exploit the directional properties of composite materials. Circumferential stiffness tailoring by fiber steering can considerably increase the bending-induced buckling performance of laminated composite cylinders. The potential structural improvement resulting from fiber steering depends on different design parameters such as the number of plies considered for fiber steering in a laminate. In this study, the buckling performance improvement of a variable stiffness (VS) composite cylinder is investigated for different percentages of plies considered for fiber steering in a multilayered composite laminate. A surrogate-based modeling along with a multi-step optimization is used in the design procedure of this study. The improvements in the buckling performance are shown and verified using finite element analysis in ABAQUS software. The mechanisms leading to buckling performance improvement of VS composites are also investigated and presented for different percentages of fiber-steered plies.
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Ahmadi, Isa. "Edge stresses analysis in laminated thick sandwich cylinder subjected to distributed hygrothermal loading." Journal of Sandwich Structures & Materials 20, no. 4 (2016): 425–61. http://dx.doi.org/10.1177/1099636216657681.

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The boundary layer hygrothermal stresses in the thick sandwich cylinder with laminated face are investigated. Uniform and through the thickness steady-state distribution for temperature and moisture content can be considered in the analysis. A displacement based layer-wise formulation is presented for analysis of thick sandwich composite cylinders subjected to hygrothermal loading conditions. Considering a general displacement field and employing a displacement based layer-wise theory, the governing equations of thick laminated sandwich cylinder are obtained. The displacement based formulation is derived for thick sandwich cylinder, which is subjected to non-uniform hygrothermal loading conditions. The faces of the sandwich cylinder are made of laminated composite with general layer stacking. The governing equations of the system include a set of coupled differential equations on the displacement components of the numerical surfaces. A semi-analytical solution is developed and the governing equations are solved for free edge boundary conditions. The accuracy of the numerical results is validated by the results of the finite element simulation and good agreements are seen between the predicted results. The free edge interlaminar stresses distributions are presented for thin and thick sandwich composite cylinders for uniform and non-uniform loading conditions. It is concluded that the presented layer-wise formulation is efficient and accurate method for analysis of thermal and hygroscopic stresses in thick and thin sandwich cylinders with general layer stacking.
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Petreli, A. S., and N. G. Tsouvalis. "A Parametric Study of the Effect of Geometric Imperfections on the Buckling Behaviour of Composite Laminated Cylinders." Advanced Composites Letters 11, no. 3 (2002): 096369350201100. http://dx.doi.org/10.1177/096369350201100302.

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This paper presents the results of a parametric study about the type and magnitude of initial imperfections on the buckling behaviour of composite laminated cylinders under external hydrostatic load. Using the FE method, cylinders with two particular types of initial imperfections are non-linearly analysed. Results show that significant improvement of the cylinder buckling strength is observed when initial imperfections have a selected shape and magnitude, which induces a final cylinder deflected shape different from the modeshape of the geometrically perfect cylinder.
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Xi, Z. C., G. R. Liu, K. Y. Lam, and H. M. Shang. "A Strip Element Method for Analyzing Wave Scattering by a Crack in an Axisymmetric Cross-Ply Laminated Composite Cylinder." Journal of Applied Mechanics 67, no. 2 (1999): 427–29. http://dx.doi.org/10.1115/1.1303800.

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A strip element method is presented for analyzing waves scattered by a crack in an axisymmetric cross-ply laminated composite cylinder. The cylinder is at the outset discretized as axisymmetric strip elements through the radial direction. The application of the Hamilton variational principle develops a set of governing ordinary differential equations. The particular solutions to the resulting equations are found using a modal analysis approach in conjunction with the Fourier transform technique. The complementary solutions are formulated by the superposition of eigenvectors, the unknown coefficients of which are determined from axial stress boundary conditions at the tips of the crack. The summation of the particular and complementary solutions gives the general solutions. Numerical examples are given for cross-ply laminated composite cylinders with radial cracks. The results show that the present method is effective and efficient. [S0021-8936(00)00202-6]
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Teshnizi, S. H. Sharifi, S. S. R. Koloor, G. Sharifishourabi, Amran Bin Ayob, and Yahya Mohd Yazid. "Mechanical Behavior of GFRP Laminated Composite Pipe Subjected to Uniform Radial Patch Load." Advanced Materials Research 488-489 (March 2012): 542–46. http://dx.doi.org/10.4028/www.scientific.net/amr.488-489.542.

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Cylindrical vessels are widely used for storage and transportation of fluids. Using composites shells can improve the corrosion resistance of the product and reduce weight therefore investigation of the mechanical behavior is important. For this purpose cylinders with 6, 12 and18-ply of GFRP , with symmetric ply sequence of [90/0/90]s, [90/0/90/0/90/0]s and, [90/0/90/0/90/0/90 /0/90]s with layer thickness 1.3 mm and mean radius 250 mm, are considered under uniform radial patch load. The analysis was based on the shell theory and classical mechanics of laminated composites. A code was written using MATLAB software to compute stress and deflection of the cylinder shell. In numerical simulation, each unidirectional composite ply is treated as an equivalent elastic and orthotropic panel. Analysis is focused on the area of cylinder where the patch load is applied. The results show that the analytical prediction compares well with numerical responses of previous literature. The procedure can be used to predict maximum stress and displacement in a multi-layer shell for various types of similar loading.
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SHAH, NAZIM SULTAN, and HARSHAL AHER. "Free Vibration Characteristics Investigation in Composite Laminated Open Cylindrical Shells." Mazedan Transactions on Engineering Systems Design 5, no. 2 (2024): 22–24. https://doi.org/10.5281/zenodo.14452000.

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The shell vibration problem is of continuing interest due to their rampant use as structural members. Often these shells are made of laminated composites. These laminated shells have a very wide range of applications, particularly in aerospace, military hardware, marine ships, and civil constructions, as well as an integral part of machines where they are subjected to dynamic loading hence their vibratory analysis, is important for efficient, reliable and failure-proof design. Composite laminated open shells in these applications are employed with various boundary conditions. Understanding the vibration characteristics of these shell components is particularly important for engineers to design suitable structures with low vibration and noise radiation characteristics. The present work investigates the free vibration characteristics of composite laminated open cylindrical shells for general boundary conditions using a unified Chebyshev-Ritz formulation. The Rayleigh-Ritz method based on the energy functional of the open cylindrical shell has been used to obtain solutions. The method has been validated with standard reference and a convergence test of this method has also been done. A parametric study has been done including the effect of aspect ratio, lamination scheme, width-to-radius ratio, thickness-to-radius ratio, and boundary conditions. The analytical results have also been compared with the numerical results obtained using finite element solver ANSYS.
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Хасанова, Г. А. "СОЗДАНИЕ МНОГОСЛОЙНОГО КОМПОЗИТА С ИСПОЛЬЗОВАНИЕМ УГЛЕРОДНЫХ ВОЛОКОН НА ОСНОВЕ МОДЕЛИ ВЫПУЧИВАНИЯ КОМПОЗИТНОГО ЦИЛИНДРА". ИЗВЕСТИЯ ВУЗОВ КЫРГЫЗСТАНА, № 3 (29 червня 2024): 3–8. https://doi.org/10.26104/ivk.2024.27.84.001.

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Высококачественные композиционные материалы ис­поль­зуются в различных областях науки и техники. Поиск лег­ких, прочных, теплопроводных и недорогих композитных ма­те­­риалов – это потребность времени. Композитные мате­риа­лы используются для снижения веса кораблей, транспорт­ных средств, строительных конструкций и самолетов. Ком­по­­зи­ционный материал из эпоксидной смолы из углеродного волокна обладает превосходной химической стойкостью и тер­мостойкостью. Еще одной характе­ристикой армирован­ных волокном материалов является свойство анизотропии. В последние годы большое внимание уделяется процессам рас­слое­­ния, деформации, вызванными остаточными напря­же­ния­ми в многослойных композитах, поскольку эти параметры имеют важное значение для качества материала. С помощью COMSOL Multiphysics мы создали ламинированный композит­ный цилиндр из углеродных волокон с учетом изменения углы вращения симметричного ламината, симметричного попе­реч­но-слоистого ламината и антисимметричного углового ла­ми­ната. Жогорку сапаттагы композиттик материалдар илим ме­нен техниканын ар кандай тармактарында колдонулат. Жеңил, бекем, жылуулук өткөрүмдүү, арзан баадагы компо­зит­­тик материалдарды табуу замандын талабы. Композит­тик материалдар кемелерде, транспортто, курулуш конст­рук­­­цияларында, учактарда салмакты азайтуу максатында кол­донулат. Көмүртек буласынан эпоксиддик чайырдан жа­сал­ган копозиттик материал мыкты химиялык туруктуу­лук­ка, каршылыкка ээ жана ысыкка чыдамдуу. Була менен бе­кем­дел­ген материалдардын дагы бир өзгөчөлүгү анизотро­пия ка­сие­­тине ээ. Акыркы жылдарда көп катмарлуу компо­зит­тер­де калдык чыңалуудан келип чыккан деламинация жана де­фор­­мация процесстерине көп көңүл бурулууда, антке­ни бул па­раметрлер материалдын сапаты үчүн маанилүү. COMSOL Multiphysics программасын колдонуп, биз симмет­риялык лами­нат­тын, симметриялык кайчылаш ламинаттын жана анти­сим­­метриялык бурч ламинаттын айлануу бурч­тарын өзгөр­түү аркылуу ламинатталган көмүртек була­сынан жасалган композиттик цилиндрди түздүк. High-quality composite materials are used in various fields of science and technology. Finding lightweight, strong, heat-con­duc­t­ing, low-cost composite materials is the need of the hour. Com­posite materials are used to reduce weight in ships, vehicles, building structures, and aircraft. Carbon fiber epoxy resin com­po­site material has excellent chemical resistance, resistance and heat resistance. Another characteristic of fiber-reinforced materials is the property of anisotropy. In recent years, much attention has been paid to the processes of delamination and deformation cau­sed by residual stresses in multilayer composites, since these para­me­ters are important for the quality of the material. Using COMSOL Multiphysics, we created a laminated carbon fiber com­po­­site cylinder by varying the rotation angles of a symmetric lami­na­te, a symmetric cross-laminated laminate, and an antisymmetric corner laminate.
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Dissertations / Theses on the topic "Laminated composite cylinder"

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Talbot, Casey A. "Axisymmetric Finite Element Modeling of Adhesive Joint Between a Laminated Composite and Metal Cylinder." DigitalCommons@USU, 2011. https://digitalcommons.usu.edu/etd/1080.

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In order to incorporate fiber-reinforced composite materials in space structures, adhesive joining techniques are required. Because analytical models have a hard time capturing the complex stress state inherent to adhesively joining dissimilar materials, a different modeling technique was deemed necessary. A two-dimensional axisymmetric finite element model capable of capturing the three-dimensional stress state of cylindrical adhesive joints was developed. In order to rigorously validate the model, testing was undergone to ensure the model accurately predicted joint displacements. Displacement data was acquired via an Epsilon axial extensometer. Load data was taken simultaneously via the load cell incorporated in the Tinius Olsen tensile test machine used. The measured force vs. displacement data was found to agree with the model’s predicted displacement for a given load. Displacement data was also taken, again with the extensometer, as the joints were rapidly cooled to liquid nitrogen temperature. It was found that the joints behave much like laminated plates in that after the first several cycles they “settle down”. The term “settle down”, in this context, means that after the first several cycles the displacements of the joints when placed from a room temperature environment to a cryogenic environment become consistent and smooth. This result allows for the joints to be modeled. The finite element model was shown to accurately predict the settled down displacement given the prescribed temperature change. The joints were also shown to maintain structural integrity post thermal cycling. Transient temperature tensile tests were performed until sample failure. One result with major design implication coming from this test was that the material properties do not change significantly enough over the temperature range tested to affect the joint’s behavior. The same properties used in the room temperature model were used to model the measured data of the transient temperature data and were found to match satisfactorily. Having validated that the developed axisymmetric finite element model accurately predicts cylindrical joint displacement fields, the model becomes an invaluable tool in design. The model can now be used in confidence, in conjunction with design requirements for a specific joint, to reduce the maximum displacements below any specified operating requirements.
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Zhuang, Wei. "Numerical modeling for elastodynamic problems in laminated composite cylinders." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp03/NQ35049.pdf.

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Kugler, Danielle. "Experimental investigation of the effect of changes in processing history on compositie laminates and cylinders /." Digital version accessible at:, 1998. http://wwwlib.umi.com/cr/utexas/main.

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Johnson, Wayne Michael. "Structural acoustic optimization of a composite cylindrical shell." Diss., Available online, Georgia Institute of Technology, 2004:, 2004. http://etd.gatech.edu/theses/available/etd-06072004-131213/unrestricted/johnson%5Fwayne%5Fm%5F200405%5Fphd.pdf.

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Zhuang, Wei. "Numerical modeling for elastodynamic problems in laminated composite cylinders." 1998. http://hdl.handle.net/1993/1609.

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Propagation and scattering of elastic waves in laminated composite cylinders are studied in this thesis. Axisymmetric steady-state elastodynamic Green's functions for laminated composite cylinders are constructed by the superposition of numerically generated modal solutions from an eigensystem, which is based on a semi-analytical finite element formulation. Boundary element method is employed to investigate scattering of waves due to circumferential flaws in laminated composite cylinders. Also, a hybrid method, which combines axisymmetric finite element modeling in an interior bounded region containing arbitrary inclusions with a spectral representation in exterior regions, is formulated to analyze more varied wave scattering problems. These methods are demonstrated through solving wave scattering problems with circumferential joints, surface breaking cracks, and V-shaped weldments with interface cracks. Three-dimensional wave propagation problem in laminated composite cylinders is decomposed into a series of two-dimensional problems, which are associated with the circumferential wave numbers. Two methods are proposed to construct explicit expressions of three-dimensional steady-state elastodynamic Green's functions. One is based on an integral transform. The other is by means of imposing symmetric/antisymmetric conditions on the cross-section containing the source load for a cylinder with cylindrically monotropic properties. The second method, being more restrictive with respect to material properties, is intended primarily as a cross-check of the integral transform version of Green's functions. Numerical implementation details are discussed in terms of two example thickness profiles to exploit the essential keys for the convergence and accuracy of Green's functions.
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Books on the topic "Laminated composite cylinder"

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Butler, Theresa Ann. The structural response of unsymmetrically laminated composite cylinders. National Aeronautics and Space Administration, 1989.

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Butler, Theresa Ann. The structural response of unsymmetrically laminated composite cylinders. National Aeronautics and Space Administration, 1989.

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United States. National Aeronautics and Space Administration., ed. Axisymmetric deformations and stresses of unsymmetrically laminated composite cylinders in axial compression with thermally-induced preloading effects. Carderock Division, Naval Surface Warfare Center, 1993.

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Hyer, M. W. Innovative design of composite structures: Axisymmetric deformations of unsymmetrically laminated cylinders loaded in axial compression : semiannual status report. College of Engineering, Virginia Polytechnic Institute and State University, 1990.

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Center, Langley Research, ed. An analytical study of the effects of transverse shear deformation and anisotropy on natural vibration frequencies of laminated cylinders. National Aeronautics and Space Administration, Langley Research Center, 1988.

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Center, Langley Research, ed. An analytical study of the effects of transverse shear deformation and anisotropy on natural vibration frequencies of laminated cylinders. National Aeronautics and Space Administration, Langley Research Center, 1988.

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National Aeronautics and Space Administration (NASA) Staff. Structural Response of Unsymmetrically Laminated Composite Cylinders. Independently Published, 2018.

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National Aeronautics and Space Administration (NASA) Staff. Innovative Design of Composite Structures: Axisymmetric Deformations of Unsymmetrically Laminated Cylinders Loaded in Axial Compression. Independently Published, 2018.

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An analytical study of the effects of transverse shear deformation and anisotropy on natural vibration frequencies of laminated cylinders. National Aeronautics and Space Administration, Langley Research Center, 1988.

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Book chapters on the topic "Laminated composite cylinder"

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Pagano, N. J. "Stress Gradients in Laminated Composite Cylinders." In Solid Mechanics and Its Applications. Springer Netherlands, 1994. http://dx.doi.org/10.1007/978-94-017-2233-9_13.

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MAEKAWA, I., H. SHIBATA, M. NAKAYAMA, and A. KOBAYASHI. "STRESS WAVE PROPAGATION BEHAVIOR IN LAMINATED COMPOSITE HOLLOW CYLINDER." In Mechanical Behaviour of Materials VI. Elsevier, 1992. http://dx.doi.org/10.1016/b978-0-08-037890-9.50064-8.

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"Characteristics of Waves in Composite Cylinders." In Elastic Waves in Anisotropic Laminates. CRC Press, 2001. http://dx.doi.org/10.1201/9781420040999.ch15.

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"Wave Scattering by Cracks in Composite Cylinders." In Elastic Waves in Anisotropic Laminates. CRC Press, 2001. http://dx.doi.org/10.1201/9781420040999.ch16.

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Conference papers on the topic "Laminated composite cylinder"

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Idan, Muayad Mohammed. "Low Velocity Impact Response of Laminated Composite Cylinder." In 2019 2nd International Conference on Engineering Technology and its Applications (IICETA). IEEE, 2019. http://dx.doi.org/10.1109/iiceta47481.2019.9012986.

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Anderson, Jacob P., and M. Cengiz Altan. "Properties of Composite Cylinders Fabricated by Bladder Assisted Composite Manufacturing (BACM)." In ASME 2011 International Mechanical Engineering Congress and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/imece2011-65285.

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An innovative manufacturing method, BACM (Bladder Assisted Composite Manufacturing), to fabricate geometrically complex, hollow parts made of polymeric composite materials is presented. BACM uses an internally heated bladder to provide the consolidation pressure at the required cure temperature, and thus produces high quality components. The feasibility of this manufacturing method is demonstrated by fabricating laminated composite cylinders using multiple cure pressures and wall thicknesses. The mechanical properties, energy consumed during the curing, and void content of the composite cylinders, are investigated in detail. The curing of composite cylinders was carried out by circulating heated air inside the bladder. Using the described heating method a number of 2-, 4-, and 6-ply composite cylinders made of E-glass/epoxy prepreg (Newport 321/7781) were prepared as test samples. Cylinders were cured at 121°C (250°F) for 2 hours using bladder pressures of 207 kPa (30 psi), 345 kPa (50 psi), 483 kPa (70 psi), and 621 kPa (90 psi). The mechanical behavior of the cylinders were characterized by compressing sample rings and loading ring segments in three-point bending. The fiber volume fraction and the void content of the cylinders were determined from resin burn-off experiments and density measurements. The cylinders produced using the BACM process were found to exhibit excellent surface quality. The elastic moduli, failure strength, and void contents of the cylinders were comparable to the values obtained from flat laminates produced by hot plate molding. Compared to conventional bladder manufacturing methods, the BACM process reduced the energy required to cure the cylinder by more than 50%.
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Katsuo, Masahide, Toshiyuki Sawa, Koji Kawaguchi, and Hiroshi Kawamura. "Axisymmetrical Thermal Stress Analysis of Laminated Composite Finite Hollow Cylinders Restricted at Both Ends in Steady State." In ASME 1996 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/imece1996-0860.

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Abstract The thermal stress distributions of laminated composite finite hollow cylinders restricted at both ends and at one end of the cylinders are analyzed using the thermoelastic displacement potential and Michell’s stress functions based on the axisymmetrical theory of elasticity. In the numerical calculations, the thermal stress distributions in the laminated composite finite hollow cylinders are examined. The effects of restrictions at the end of the cylinders on the thermal stress distributions are clarified. The analytical results are compared with the results obtained from the plain strain the ory. It can be seen that the differences in the stresses between the inner cylinder and the outer cylinder increase near the restricted end. The hoop and the axial stresses distribute discontinuously at the interface of the cylinders. The difference in the hoop stress at the interface is minimal in the case of the plain strain theory. For verification, the strains were measured and the analytical results were in fairly good agreement with the experimental results.
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Yousuf, Louay S. "Nonlinear Dynamics Investigation of Bending Deflection Of Stiffened Composite Laminated Plate Using Lyapunov Exponent Conception." In ASME 2021 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/imece2021-67448.

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Abstract In this paper, the nonlinear dynamics behavior of the bending deflection of stiffened composite laminated plate is investigated using largest Lyapunov exponent parameter. Wolf algorithm is used to quantify largest Lyapunov exponent in the presence of aspect ratios and fiber volume fractions. A power spectrum analysis has been added using the amplitude of Fast Fourier Transform (FFT) to detect the non-periodic motion of the stiffened plate. Numerical simulation is carried out using ANSYS software. The combined loading are the in-plane compression (uniaxial) mechanical load and shear force. The experiment setup has been done using buckling test machine whereas the upper head is moved downwards by servo hydraulic cylinder. The nonlinear dynamics behavior is increased with the increasing of aspect ratios and fiber volume fractions. The nonlinear dynamics behavior of stiffened composite laminated plate is decreased with the increasing of number of stiffeners.
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Li, H. Y., H. Li, S. D. Hu, and Z. B. Chen. "Experiment on Active Vibration Isolation of a Conical Shell Isolator." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-37850.

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Conical shells have advantages such as light weight, higher stiffness and strength, its stiffness ratio between axial and transverse directions can be easily adjusted by changing its apex angle. Thus conical shell can be utilized as an isolator to protect precision payloads and equipment from severe dynamic loads. In this study, vibration isolation performance of a conical shell isolator laminated with piezoelectric actuators is investigated. The conical shell isolator is manufactured from epoxy resin. The payload is at the minor of the isolator. The major end of the isolator is fixed at a flange installed on a shaker. Macro fiber composite (MFC) is used as actuator, which is laminated on the outer surface of the conical isolator. The sensing signals from sensors on the isolator is transferred to a dSPACE system and the control voltage is transferred to a power amplifier and then to the MFC actuator. The control voltage is calculated in the Matlab/Simulink environment. Both negative velocity feedback and optimal controllers are employed in the active vibration control. The payloads are simplified to be a rigid cylinder, and two payloads with different weight are investigated in the study. Experimental results show that the proposed conical shell isolator is effective for vibration isolation of payloads, and vibration amplitude of the payload can be significantly reduced.
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6

Silva, Joao F., Joao P. Nunes, and Joao C. Velosa. "Using Thermoplastic (HDPE) Liners and Glass Fiber Reinforced Thermosetting and Thermoplastic Structural Wall Matrices to Produce Filament Wound Pressure Vessels." In ASME 2010 Pressure Vessels and Piping Division/K-PVP Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/pvp2010-25826.

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Polymer composites are an excellent alternative to replace more traditional materials in the fabrication of pressure cylinders for common applications. They minimize the weight and improve the mechanical, impact and corrosion behavior, which are relevant characteristics for almost all current and future large scale pressure cylinder applications, such as liquid filters and accumulators, hydrogen cell storage vessels, oxygen bottles, etc. A new generation of composite pressure vessels has been studied in this work. The vessels consist on a thermoplastic liner wrapped with a filament winding glass fiber reinforced polymer matrix structure. A conventional 6-axis CNC controlled filament winding equipment was used to manufacture the thermosetting matrix composite vessels and adapted for production of thermoplastic matrix based composite vessels. The Abaqus 6.4.2 FEM package was used to predict the mechanical behavior of pressure vessels with capacity of approximately of 0.068 m3 (68 liters) for a 0.6 MPa (6 bar) pressure service condition according to the requirements of the EN 13923 standard, namely, the minimum internal burst pressure. The Tsai-Wu and von-Mises criteria were used to predict composite laminate and thermoplastic liner failures, respectively, considering the elasto-plastic behavior of the HDPE liner and the lamina properties deducted from the micromechanical models for composite laminates. Finally, the results obtained from the simulations were compared with those obtained from the experimental pressure tests made on the thermoplastic liners and final composite vessels.
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7

Xiao, J. R., B. A. Gama, and J. W. Gillespie. "Progressive Damage and Delamination in Plain Weave S-2 Glass/SC-15 Composites Under Quasi-Static Punch Shear Loading." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-82261.

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Quasi-static punch-shear tests are carried out on plain weave (PW) S-2 glass/SC-15 epoxy composite laminates with a right circular cylinder punch to identify the sequence and extent of damage and the corresponding displacements at which they occur for a wide range of laminate thicknesses. Two different support spans of 25.4 mm (1 in) and 101.6 mm (4 in) diameter with different layers (0.6 mm ply thickness) of composite laminates are tested under quasi-static loading to identify compression-shear and tension-shear dominated modes of damage. Numerical punch shear experiments are conducted using LS-DYNA 970. The numerical modeling is carried out using a newly developed composite damage model, namely MAT 162, which has been incorporated into LS-DYNA. MAT 162 uses damage mechanics principle for progressive damage and material degradation. Input data required in MAT 162 have been calibrated to match the experimental results of 22-layer composite plate of both spans (25.4 mm and 101.6 mm). The calibrated material properties have been used to simulate other thicknesses, and the simulated results show good agreement with experiment results. It has been found that the dominant damage mechanisms are delamination and fiber breakage due to shear and tension.
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8

Kim, Ran Y., Allan S. Crasto, and Gregory A. Schoeppner. "Dimensional Stability of Composite in a Space Thermal Environment." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-1169.

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Abstract Composites are steadily replacing metals in weight-critical space structures primarily because of their high specific moduli. Many space structures require not only high stiffness but precision alignment and dimensional stability as well. These parameters are sensitive to thermal strains caused by the mismatch in coefficients of thermal expansion (CTE) of the constituents, anisotropy in ply CTE, and variations in service temperature. The CTE of a laminate can change in service as a result of mechanically or thermally induced microcracking and this may result in undesirable distortion of the composite structure. In this work, changes in the CTE of a representative space structural material-XN-70/RS3 graphite/cyanate-ester were studied using strain gages. The longitudinal and transverse CTEs of unidirectional and crossply ([0/90]2s) laminates were initially determined over the temperature range of −157°C to 121°C. Specimens were then subjected to thermal cycles from −150°F to 250°F to induce microcracking. The specimen CTE was again measured in the same location after 25, 50, 100, 200, 500 and 1000 cycles, and the corresponding crack density (in the vicinity of the strain gage) was determined by microscopic examination of a polished specimen edge. Predictions of CTE variation with crack density were made using the axisymmetric formulation of a large-radius, hollow, layered-cylinder model, which is equivalent to the flat laminate formulation. The experimental results compared fairly well with the predictions for a [0/90]2s cross-ply laminate. This paper also includes a discussion of the statistical variation of the measured CTEs.
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9

FUCHS, HANNES, and MICHAEL HYER. "The nonlinear bending response of thin-walled laminated composite cylinders." In 33rd Structures, Structural Dynamics and Materials Conference. American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-2230.

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10

Hyer, Michael W., and Jaret C. Riddick. "Displacement Response of Segmented-Stiffness Composite Cylinders." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-1192.

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Abstract With advanced manufacturing technology such as tow placement devices and filament winders, cylindrical composite structures may well be constructed in such a fashion that the lamination sequence varies with circumferential location around the cylinder. For example, the stacking sequence at the top and bottom of the cylinder may be axially stiff to resist bending and axial loads, while the sides of the cylinder may be designed to resist shear loads. The variation in stacking sequence may be continuous, with the stacking sequences on the top and bottom making a smooth transition to another stacking sequence on the sides. Alternatively, as a manufacturing convenience the cylinder may be constructed in circumferential sections, or segments, using more conventional manufacturing technology. There would then be discrete changes in laminate stacking sequence at specific locations around the circumference which would result in stepwise changes in laminate properties at the circumferential locations where the different segments join. In reality, there may be stiffeners incorporated into the cylinder, particularly at the locations where the segments join. For the present work stiffeners will not be considered and as a result of the discrete change in stiffness rather unusual displacement response will occur, even for simple loadings. The present paper examines the response of a segment-stiffness composite cylinder to compressive axial end shortening and internal pressure. For more conventional nonsegmented construction where the cylinder is constructed of a single laminate, these loadings cause axisymmetric response, at least in the range of linear response. The specific cylinder considered has its top and bottom segments made of the same laminate, and the sides made of another laminate. It is further assumed that the bending-twisting stiffnesses D16 and D26 are negligible. As a result, the problem exhibits quarter symmetry and this feature is exploited in the analysis. For pedagogical reasons an infinitely long cylinder is initially studied. This problem can be solved in closed form and the solution indicates that the primary feature that distinguishes the response of an infinitely-long segmented-stiffness cylinder from that of a more conventional single-laminate cylinder is the existence of circumferential displacements. For the case of axial end shortening, it is the difference in Poisson’s ratios between the various segments that is responsible for the existence of circumferential displacements. For the case of internal pressure, it is the difference in the extensional stiffnesses that causes the circumferential displacements. In both cases the radial displacement is independent of circumferential location, and therefore an infinitely long round cylinder remains round. Motivated by the results for an infinitely long cylinder, a finite-length cylinder is studied by using the principle of minimum total potential energy in combination with the Kantorovich approach. For the application of the latter approach, the dependence of the response on the circumferential coordinate is assumed to be harmonic, and the dependence on the axial coordinate is solved for from the resulting system of ordinary differential equations that are obtained by taking the first variation of the total potential energy. Like the infinite-length cylinder, circumferential displacements characterize the response, but the boundary conditions greatly influence the magnitude of the circumferential displacement. Also, unlike the infinite-length cylinder, the finite-length cylinder does not stay round, rather, the radial displacements are a function of the circumferential location. The eigenvalues of the system of ordinary differential equations indicate that the characteristic lengths (St. Venant effect) for the circumferential and radial displacements are not the same. There is a bending boundary layer associated with the radial displacements, as with nonsegmented construction, but there is no boundary layer associated with the circumferential displacements. These eigenvalues help explain the behavior of the finite-length cylinder.
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Reports on the topic "Laminated composite cylinder"

1

Blake, H. W., and J. M. Starbuck. Hydrostatic testing of thick laminated composite cylinders for performance model validation. Office of Scientific and Technical Information (OSTI), 1993. http://dx.doi.org/10.2172/10151163.

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2

Blake, H. W., and J. M. Starbuck. Hydrostatic testing of thick laminated composite cylinders for performance model validation. Office of Scientific and Technical Information (OSTI), 1993. http://dx.doi.org/10.2172/6855310.

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