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Journal articles on the topic 'Composite laminate design'
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1
Bir, Amarpreet S., Hsin Piao Chen, and Hsun Hu Chen. "Optimum Stacking Sequence Design of Composite Sandwich Panel Using Genetic Algorithms." Advanced Materials Research 585 (November 2012): 29–33. http://dx.doi.org/10.4028/www.scientific.net/amr.585.29.
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In the present study, both critical buckling load maximization and face-sheet laminate thickness minimization problems for the composite sandwich panel, subjected to bi-axial compressive loading under various imposed constraints have been investigated using genetic algorithms. In the previously published work, the optimization of simple composite laminate panels with only even number of laminae has been considered [1, 3]. The present work allows the optimization of a composite sandwich panel with both even and odd number of laminae in the face-sheet laminates. Also, the effects of the bending-twisting coupling terms (D16and D26) in bending stiffness matrix which were neglected in the previous studies [1, 2, 3], are considered in the present work for exact solutions. In addition effect of both balanced and unbalanced face-sheet laminates on the optimum solutions have also been investigated, whereas only balanced laminates were considered in the previous studies [1, 2, 3].
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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 (March 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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Mahadevan, S., and X. Liu. "Probabilistic Optimum Design of Composite Laminates." Journal of Composite Materials 32, no. 1 (January 1998): 68–82. http://dx.doi.org/10.1177/002199839803200104.
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This paper proposes a procedure for the optimum design of composite laminates under probabilistic considerations. The problem is formulated to consider the minimization of laminate weight as the objective function and the reliability requirements as the constraints. Both system-level and element-level reliabilities are considered. The first-order reliability method (FORM) is used to estimate the reliability of each ply group, and system reliability is computed based on series or parallel system assumptions. The Tsai-Wu strength criterion is adopted to derive the limit state function of individual ply groups in the laminate. The gradient and sensitivity information of the objective function and the constraints with respect to the design variables are obtained by using sensitivity analysis based on the composite plate theory. Thus the proposed procedure brings together modern concepts of reliability analysis, composite laminate behavior and nonlinear optimization to develop a rational and practical procedure for the optimum design of composite laminates. Numerical examples are presented to demonstrate the effectiveness of the proposed method.
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Chen, Z., J. J. Mecholsky, and S. Hu. "Effect of interface design on high-temperature failure of laminated composites." Journal of Materials Research 11, no. 8 (August 1996): 2035–41. http://dx.doi.org/10.1557/jmr.1996.0256.
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The fracture strength and toughness of alumina can be increased by lamination with strategically placed nickel layers and with a modified Ni/Al2O3 interface through tape casting. In order to examine the potential of this type of laminated composite in high temperature applications, the laminates were tested at elevated temperatures. This paper describes how a modified tortuous interface, instead of a smooth interface, increases the creep resistance of the laminates. Interface modification can control high temperature laminate behavior and is critical to successful composite design.
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Kumar, M. Ashok, A. M. K. Prasad, and D. V. Ravishankar. "Effect of Quasi-Static Loading on the Composite Laminates." Advanced Engineering Forum 20 (January 2017): 10–21. http://dx.doi.org/10.4028/www.scientific.net/aef.20.10.
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The low velocity impact is a common phenomenon which occurs in fiber reinforced polymer composite products like LPG cylinders, fighter aircraft fuel drop tanks, aircraft wing surfaces, sports goods etc. The consequences of low velocity impact will create a considerable damage and ultimately lead to a premature failure of the structure. Hence the polymer composites for engineering applications must be provided with a better design solution. From the literature survey it is observed that, the response of composite laminates subjected to quasi-static loading, exhibits similar results as that of low velocity impact. Polymer reinforced composites are poor in damage tolerance with better strength to weight ratio than conventional materials. However composite materials can be tailored to meet the design requirements by manipulating fiber orientations and laminae stacking sequence. In the present paper, principles of classical laminate theory are considered for analysis. FEM is implemented for thorough understanding of the failure mechanism of each laminate by layer wise. Simulated quasi-static loading tests and observed the layer wise distribution of transverse strain intensity. The experimental setup is designed and fabricated as per ASTM D 6264 standards. The E-glass/epoxy composite laminate is quasi-statically loaded at its center by a steel ball indenter of diameter 8.7mm and its response is measured by the degree of opacity or translucency in terms of interlaminar and intra-laminar damage area. The stacking sequence of composite laminates are chosen as [00/600]12, [00/750]12 and [00/900]12. The damage areas obtained from numerical analysis are in good agreement with experimental results.
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Marzuki, Haslan Fadli Ahmad, Engku Ahmadhilmi Engku Ubaidillah, Sivakumar A/l Sivarasa, Mohd Syamsul, and Mariatti Jaafar. "Study on Effect of Fiber Orientation on Flexural Properties of Glass Fiber Reinforced Epoxy Composite Laminates for Structural Applications." Solid State Phenomena 301 (March 2020): 227–37. http://dx.doi.org/10.4028/www.scientific.net/ssp.301.227.
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Composite laminate design is an important procedure in defining the mechanical properties of laminated composite structure to be used in multi-directional service loading application. Composite technologies or manufacturers who is lack of knowledge regarding the importance of laminate design, tend to develop a composite structure that will collapse or fail below the service requirement. The purpose of this study is to determine the effect of fiber orientation on flexural properties of the designed glass fiber reinforced epoxy laminated composite. Six sets of laminates with different fiber orientation and sequence were simulated using CompositeStar© software to determine its flexural properties. Samples were fabricated to verify the simulated data and were tested in accordance to ASTM D2344. Moreover, crack pattern within the samples after the flexural test is studied. From the simulated results, it shows that laminates which have fiber in tri-direction and quasi-direction display a higher flexural modulus and strength compared to laminates with fiber in uni-directional and bi-directional. In addition, data from tested fabricated laminates samples displayed the same modulus patterns against the simulated data, with variants from 8% to 35%. Additionally, it is found that samples with fiber in ±45 direction shows a transverse and shear cracking which prolonged the cracking propagation before the samples show a complete failure.
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Ali, J. S. Mohamed, and Abeid Abeid Rubeya. "LEADME: An Educational Software for Composite Laminate Analysis and Design." Advanced Materials Research 1115 (July 2015): 578–81. http://dx.doi.org/10.4028/www.scientific.net/amr.1115.578.
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LEADME ( Laminate Analysis and Design Made Easy ), an educational software useful for the analysis and design of laminated composite structure has been developed. The software encompasses both the micro and macro mechanics analysis of lamina and laminate. The highlight of this software is that, apart from usual laminate analysis, the software is capable to solve practical laminate applications such as analysis of beams and also a design module is included. The software has been developed using MATLAB-Graphical User Interface (GUI) which makes it very user friendly. The results obtained from this software have been validated. It is expected that this software will serve as an educational tool complementing textbooks for students to gain better understanding of composite structural analysis.
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Huang, Chunfang, Mingchang He, Yonglyu He, Jiayu Xiao, Jiangwei Zhang, Su Ju, and Dazhi Jiang. "Exploration relation between interlaminar shear properties of thin-ply laminates under short-beam bending and meso-structures." Journal of Composite Materials 52, no. 17 (December 27, 2017): 2375–86. http://dx.doi.org/10.1177/0021998317745586.
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Carbon fiber reinforced polymer matrix composite laminates with standard thickness plies (0.125 mm) usually have weak interlaminar shear strength, meanwhile, for thin-thickness laminate structures such as aircraft wing skin, it is difficult to design a balanced laminate with the standard plies. It is a possible way to improve the interlaminar shear performance of carbon fiber reinforced polymer composite laminates and enlarge the design space of the thin-thickness structures by using thin-plies technology. In this paper, the interlaminar shear strength of carbon fiber/epoxy laminates with thin prepreg thickness subjected to short-beam bending is investigated. Unidirectional, cross-ply and quasi-isotropic laminate specimens were prepared by using prepregs with different ply thicknesses. Results show that, with decreasing of the ply thickness, higher interlaminar shear strength and smaller coefficient of variation of the data are obtained. Compared to laminates made by standard thickness prepreg, the laminates with thin-thickness prepreg exhibit more homogeneous microstructures and more regularly interlaminar shear stress distribution. This indicates that inherent anisotropy of the laminate composites is weakened in the thin-ply laminates and show pseudo-isotropic behavior. Especially in the case of ply thickness less than 0.020 mm, the interlaminar shear stress distributions of the cross-ply and quasi-isotropic laminate are almost the same with that of isotropic materials according to the classic laminate theory. On the other hand, as expected, the design space of the thin-thickness laminate structures will be increased since more ply number are allowed and superior interlaminar properties can be obtained due to the pseudo-isotropic behavior of the thin plies.
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Al-Madani, Ramadan A., M. Jarnaz, K. Alkharmaji, and M. Essuri. "Finite Element Modeling of Composites System in Aerospace Application." Applied Mechanics and Materials 245 (December 2012): 316–22. http://dx.doi.org/10.4028/www.scientific.net/amm.245.316.
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The characteristics of composite materials are of high importance to engineering applications; therefore the increasing use as a substitute for conventional materials, especially in the field of aircraft and space industries. It is a known fact that researchers use finite element programs for the design and analysis of composite structures, use of symmetrical conditions especially in complicated structures, in the modeling and analysis phase of the design, to reduce processing time, memory size required, and simplifying complicated calculations, as well as considering the response of composite structures to different loading conditions to be identical to that of metallic structures. Finite element methods are a popular method used to analyze composite laminate structures. The design of laminated composite structures includes phases that do not exist in the design of traditional metallic structures, for instance, the choice of possible material combinations is huge and the mechanical properties of a composite structure, which are anisotropic by nature, are created in the design phase with the choice of the appropriate fiber orientations and stacking sequence. The use of finite element programs (conventional analysis usually applied in the case of orthotropic materials) to analysis composite structures especially those manufactured using angle ply laminate techniques or a combination of cross and angle ply techniques, as well considering the loading response of the composite structure to be identical to that of structures made of traditional materials, has made the use of, and the results obtained by using such analysis techniques and conditions questionable. Hence, the main objective of this paper is to highlight and present the results obtained when analyzing and modeling symmetrical conditions as applied to commercial materials and that applied to composite laminates. A comparison case study is carried out using cross-ply and angle-ply laminates which concluded that, if the composition of laminate structure is pure cross-ply, the FEA is well suited for predicting the mechanical response of composite structure using principle of symmetry condition. On the other hand that is not the case for angle-ply or mixed-ply laminate structure.
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Fukunaga, Hisao, and Hideki Sekine. "A Laminate Design for Elastic Properties of Symmetric Laminates with Extension-Shear or Bending-Twisting Coupling." Journal of Composite Materials 28, no. 8 (May 1994): 708–31. http://dx.doi.org/10.1177/002199839402800802.
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A laminate design method for elastic properties of symmetric laminates with extension-shear or bending-twisting coupling is presented using lamination parameters which give a complete expression of laminate configurations. The elastic properties of Young's moduli, Poisson's ratios and shear modulus are represented on the lamination parameter plane. A general method is also developed for determining laminate configurations corresponding to lamination parameters. The graphical representation clarifies the relation between laminate configurations and elastic properties. Effects of extension-shear coupling on in-plane elastic properties are discussed. The elastic properties of Young's moduli and shear modulus have the maximum values when the coupling terms vanish. Two design examples are also presented which utilize bending-twisting couplings. One is concerned with the control of a cross-coupling parameter in an aeroelastic tailoring of a composite wing, and the other is concerned with the shear buckling optimization of a symmetric laminated plate.
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Yoon, Sung-Won, Tae-Yeob Kim, Je-Hyoung Cho, Jong-Rok Ha, and Yun-Hae Kim. "Optimization winding design of a composites intermediate shaft." Modern Physics Letters B 33, no. 14n15 (May 28, 2019): 1940030. http://dx.doi.org/10.1142/s021798491940030x.
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The purpose of this study is to determine the correct estimation of the laminate patterns for composites intermediate shaft. The laminate patterns in the filament winding process are an important factor in determining the strength and life of the final structure. In this study, the structural safety was analyzed for the laminate patterns in four cases. In addition, this work evaluated the range of laminated angles for optimal thickness selection. The laminate patterns and the order of the layers were determined by considering the results of the finite element analysis. The shear stress equation of the hollow shaft for torsional loads showed that the thickness of the structure varied with the diameter ratio. At the maximum diameter ratio (the smallest shaft thickness), the required shear strength for the structure was 36.6 MPa. Also, the most stable stress distribution was selected at [Formula: see text] to [Formula: see text]. The shear modulus according to the laminated angle was considered to give the best strength value when stacked at [Formula: see text]. The research results in this study suggest that the design of an optimized intermediate shaft of composite materials can be supplemented.
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Park, Hyun Bum. "Investigation on Damage Tolerance of Thick Laminate Composite Structure." Key Engineering Materials 665 (September 2015): 149–52. http://dx.doi.org/10.4028/www.scientific.net/kem.665.149.
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This study is to investigate the compressive strength of the carbon/epoxy thick laminate after damage. Through damage tolerance of thick laminate is not standardized test because specimens exceed typical specimen thickness described in the ASTM standard, design allowable of thick laminate shall be determined by the experiment to address design criteria of the structure and incorporate functional capability with damage level. In this study, it is performed the research on damage tolerance of thick laminate adopting aircraft structure. The damage tolerance of thick laminates such as no damage and impact damage is evaluated under compression loading.
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Rao, Ananda M., Ch Ratnam, J. Srinivas, and A. Premkumar. "Optimum design of multilayer composite plates using simulated annealing." Proceedings of the Institution of Mechanical Engineers, Part L: Journal of Materials: Design and Applications 216, no. 3 (July 1, 2002): 193–97. http://dx.doi.org/10.1177/146442070221600304.
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This paper proposes the use of a simulated annealing (SA) approach to the optimal design of multilayered composite plate structures. The orientation fibres and the number of layers in laminated composites play a major role in determining strength and stiffness. Therefore, the basic design problem is to determine the optimum stacking sequence of the composite laminate. The SA technique is employed to obtain the optimum fibre orientation of multilayered composite plates, so as to maximize fundamental natural frequency. The composite plate is discretized and analysed by a finite element (FE) analysis procedure using a computer program written in C language. The inverse iteration method is employed to obtain the fundamental frequency of a laminated plate with a given number of layers and fibre orientations in each layer. Both symmetric and antisymmetric fibre angles are considered. The optimum results of fibre orientations are compared with the conventional random walk (RW) method.
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Harik, Vasyl Michael. "Control of Damage in Composite Laminates by Ply-Stacking Designs: Characteristic Failure Signatures and Safety Criteria." Journal of Engineering Materials and Technology 125, no. 4 (September 22, 2003): 385–93. http://dx.doi.org/10.1115/1.1605771.
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Structural designs for composite laminated systems can be optimized for a fail-safe in-service performance by introducing the built-in cumulative-damage-indicators for the progressive degradation of material properties. This design methodology is based on the concepts of the characteristic failure signature (CFS), cumulative-damage states and a load-drop sequence that characterize the stress-strain response and progressive accumulation of damage. The cumulative damage mechanics is based on the three-dimensional laminate analysis that is used to predict nonlinear response of composites, accumulation of damage and failure behavior. An earlier-developed nonlinear analysis involves an incremental formulation that couples the three-dimensional laminate analysis with a progressive ply-failure methodology, which has been tested in the World-Wide Exercise on Composites Failure Theories. The failure signatures are shown to have unique “safety features” that depend on the ply stacking sequence and predominant loading. To refine the analysis of micromechanical damage a model for the macro-to-micro coupling is introduced. Various examples of failure envelopes, characteristic failure signatures, a safety criterion and the “safe” CFSs that lead to the desired controlled failures are discussed for symmetric balanced laminates.
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Haavajõe, Anti, Madis Mikola, and Meelis Pohlak. "Design and Manufacturing of Variable Angle Tow Laminate." Key Engineering Materials 674 (January 2016): 59–64. http://dx.doi.org/10.4028/www.scientific.net/kem.674.59.
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Variable angle tow (VAT) laminates have shown enhanced stiffness/strength performance compared to conventional straight fiber laminates. Employment of VAT allows utilizing variable stiffness design of composite structure, thus it widens the design possibilities. As a result, composite structure with improved mechanical characteristics can be manufactured. The main aims of the current study are to give an overview on methods and algorithms used for analysis and design of VAT laminates, and to develop technology and equipment for manufacturing laminate with improved structural performance. In order to improve the accuracy of the compaction process, a set of experiments were carried out using a simple testing device. For measuring the compaction force, a pneumatic cylinder, pressure regulator and digital manometer were used. The temperature of the consolidation area and the heat distribution were screened with the thermal camera. Infrared heater was used as a heating source. Material used in the experiment was carbon fiber reinforced polyamide.Findings show that in addition to the main parameters – the compaction force and temperature, there are many minor factors, such as the compaction wheel diameter, material and surface roughness of the compaction roller, the material and surface roughness of the mold and the pretension in the laminating tape and also the laminating speed, all influence the quality of the final product.Key words: Advanced Fiber Placement Technology, Automated Fiber Placement, Automated Tape Laying, Fiber Reinforced Composites, Laminates
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Liu, Zhi Qiang, Zhu Feng Yue, Fu Sheng Wang, and Yao Yao Ji. "Optimizations of Flame Spraying Aluminum Thickness and Laminate Plies for Composite Lightning Protection." Advanced Materials Research 915-916 (April 2014): 698–703. http://dx.doi.org/10.4028/www.scientific.net/amr.915-916.698.
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Anti-lightning strike protection for composite structures is catching great attention to design optimum lightning protection solution. Based on lightning direct effect, optimizations of flame spraying aluminum thickness and composite laminate plies were conducted by combining electrical-thermal analysis procedure and corresponding optimization programs. Optimized thickness was acquired for flame spraying aluminum layer. Meanwhile, non-uniform thick plies and optimized stacking angles were given for anti-lightning strike composite laminate. Comparisons were conducted to investigate changes of lightning direct effects on composite laminates fore and after optimization. Synergetic protections of flame spraying aluminum and laminate plies design were listed. The conclusions can be used as suggestions for lightning strike protection of advanced aircraft.
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Serhat, Gokhan. "Design of Circular Composite Cylinders for Optimal Natural Frequencies." Materials 14, no. 12 (June 10, 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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McKinnon, Mark B., Yan Ding, Stanislav I. Stoliarov, Sean Crowley, and Richard E. Lyon. "Pyrolysis model for a carbon fiber/epoxy structural aerospace composite." Journal of Fire Sciences 35, no. 1 (November 21, 2016): 36–61. http://dx.doi.org/10.1177/0734904116679422.
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Carbon fiber laminate composites have been utilized in the aerospace industry by replacing lightweight aluminum alloy components in the design of aircraft. By replacing low flammability aluminum components by carbon fiber laminates, the potential fuel load for aircraft fires may be increased significantly. A pyrolysis model has been developed for a Toray Co. carbon fiber laminate composite. Development of this model is intended to improve the understanding of the fire response and flammability characteristics of the composite, which complies with Boeing Material Specification 8–276. The work presented here details a methodology used to characterize the composite. The mean error between the predicted curves and the mean experimental mass loss rate curves collected in bench-scale gasification tests was calculated as approximately 17% on average for heat fluxes ranging from 40 to 80 kW m−2. During construction of the model, additional complicating phenomena were investigated. It was shown that the thermal conductivity in the plane of the composite was approximately 15 times larger than the in-depth thermal conductivity, the mass transport was inhibited due to the high density of the laminae in the composite, and oxidation did not appear to significantly affect pyrolysis at heat fluxes up to 60 kW m−2.
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Imran, Malik M., Farrukh Mazhar, and Riaz Ahmad. "Multivariate Optimization of Fiber Reinforced Laminate Using Ant Colony Optimization Algorithm." Materials Science Forum 867 (August 2016): 116–20. http://dx.doi.org/10.4028/www.scientific.net/msf.867.116.
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Fiber reinforced laminate design is a challenging problem in the field of composite laminates. It provides us a systematic way to design the laminates of desired properties while conveniently incorporating the thick-ness and mass constraints. In this paper, we pursue the multivariate graphite fiber reinforced laminate design problem using Ant Colony Optimization (ACO) algorithm. Classical lamination theory is used to determine mid-plane strains, curvatures and stresses in individual lamina under applied biaxial loading conditions. The fiber orientations, lamina thickness, number of layers and fiber volume fractions of lamina are considered as the optimization variables. Failure of the lamina is analyzed by Tsai–Wu failure criterion. Objective of the study is to maximize the load carry capacity of the composite laminate structure and minimize the areal mass density under multivariate/multiobjective optimization.
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Valido, Aníbal J. J., and João Barradas Cardoso. "Design variation of thin-walled composite beam cross-section properties." Multidiscipline Modeling in Materials and Structures 12, no. 3 (October 10, 2016): 558–76. http://dx.doi.org/10.1108/mmms-12-2015-0081.
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Purpose The purpose of this paper is to present a design sensitivity analysis continuum formulation for the cross-section properties of thin-walled laminated composite beams. These properties are expressed as integrals based on the cross-section geometry, on the warping functions for torsion, on shear bending and shear warping, and on the individual stiffness of the laminates constituting the cross-section. Design/methodology/approach In order to determine its properties, the cross-section geometry is modeled by quadratic isoparametric finite elements. For design sensitivity calculations, the cross-section is modeled throughout design elements to which the element sensitivity equations correspond. Geometrically, the design elements may coincide with the laminates that constitute the cross-section. Findings The developed formulation is based on the concept of adjoint system, which suffers a specific adjoint warping for each of the properties depending on warping. The lamina orientation and the laminate thickness are selected as design variables. Originality/value The developed formulation can be applied in a unified way to open, closed or hybrid cross-sections.
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Abdi, Behzad, Yob Saed Bin Ismail, Ayob Amran, R. A. Abdullah, and Mohd Yazid bin Yahya. "Multi-Objective Optimization of Filament Wound Composite Pressure Vessels Based on Weight and Matrix Cracking/ Burst Pressure Using Imperialist Competitive Algorithm." Applied Mechanics and Materials 234 (November 2012): 34–38. http://dx.doi.org/10.4028/www.scientific.net/amm.234.34.
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The most important concern in design of filament-wound composite pressure vessels reflects on the determination of the optimum shape and optimum laminate stacking sequence of composite vessels based on the matrix cracking pressure and burst pressure of composite laminates. In this study the Imperialist Competitive Algorithm (ICA) is used to find the optimum laminate stacking sequence of composite vessels that the design considerations are stability and strength constraints. the matrix cracking pressure of filament-wound composite pressure vessels made of different number of helical layers and different layers of Circumferential layers was calculated by using orthotropic material formulae and then, the burst pressure of composite vessels was calculated by using netting analysis. The optimum laminate stacking sequence of filament winding composite was found to maximize the matrix cracking pressure and the burst pressure by using Imperialist Competitive algorithm.
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Sebaey, TA, and Ahmed Wagih. "Flexural properties of notched carbon–aramid hybrid composite laminates." Journal of Composite Materials 53, no. 28-30 (June 11, 2019): 4137–48. http://dx.doi.org/10.1177/0021998319855773.
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Hybrid composite laminates are currently receiving researchers’ attention due to their specific advantages in designing laminates with improved specific strength and stiffness. One of the main disadvantages of polymeric laminated composites is their high sensitivity to notches, which cannot be avoided in design. This paper presents a comparison between two common hybridization techniques, namely sandwich and intra-ply hybridization. The study adopts experimental observations to investigate the influence of hybridization method on the flexural properties of notched carbon–aramid hybrid laminates. After four-point bending tests, the results show that the damage nature in both laminates is different. A catastrophic damage is observed for intra-ply hybrid laminates, while sandwich laminates show progressive damage. In terms of the strength, sandwich specimens show 1.3 times higher specific strength, compared to intra-ply specimens. Moreover, the bottom layers of the laminate manufactured in the sandwich fashion show minimal damage due to the high capability of the aramid/epoxy core to absorb the energy in deformation and concentrate the damage at the top layers (the compression side).
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Taheri-Behrooz, Fathollah, and Nima Bakhshi. "Neuber’s rule accounting for the material nonlinearity influence on the stress concentration of the laminated composites." Journal of Reinforced Plastics and Composites 36, no. 3 (November 23, 2016): 214–25. http://dx.doi.org/10.1177/0731684416680302.
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Since holes comprise the necessary features of many structural components, a comprehensive understanding of the behavior of composite plates containing an open hole is a crucial step in their design process. In the present manuscript, an extensive numerical study has been conducted in order to investigate the effects of material nonlinearity on the stress distribution and stress concentration factors in unidirectional and laminated composite materials. To attain this objective, various models with different configurations were studied. In unidirectional composites, the maximum deviation of stress distribution around the hole (from the linear solution) happens in 45° lamina in which includes a high level of shear stress. However, the maximum difference in the stress concentration factor occurs in 15° lamina and is 15.1% at the onset of failure. In composite laminates, the maximum deviation of nonlinear stress concentration factor from the linear solution is reported 24.3% and it occurs in [+45/−45] s laminate. In the last section, Neuber’s rule is employed to find the stress concentration factors of the laminated composites, with a reasonable accuracy.
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Lee, Myoung Keon, Chang Min Cho, and Se Yong Jang. "HALE UAV Composite Wing Structure Design." Advanced Materials Research 123-125 (August 2010): 105–8. http://dx.doi.org/10.4028/www.scientific.net/amr.123-125.105.
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HALE (High Altitude Long Endurance) UAVs are aircraft systems for surveillance and reconnaissance for over 25 hours. Most of UAVs consist of fuselage and high aspect ratio wing because of long-endurance flight mission. The structural weight of HALE UAV is one of the most critical design requirements. In addition, the structural stiffness for the high aspect ratio wing is another critical design requirement because the UAV has to keep the minimum clearance between wing tip and ground when the UAV is being towed. For above design requirements, the wing structure of the UAV has been designed by intermediate modulus Gr/Ep composite materials. The goal of this research is to present the optimized design concepts for the composite wing structure of the UAV. Although there are many design parameters for the composite structure of the aircraft, this research is focused on composite structure strength and buckling analysis for the plate type structures, such as cover panel skins and spar webs, which are loaded in in-plane shear and/or compression. This research presents that the wing structural weight can be reduced when the material allowables based on tape laminate are applied instead of unidirectional lamina allowables. For the buckling analysis, this report has a trade off study to find an optimized lay-up design and stacking sequence with 0°, ±45° and 90° plies. This research shows that the critical buckling load is a function of the number of ±45° plies and the position of the ±45° plies through the laminate thickness using a typical Gr/Ep composite tape material. The structural design of the UAV composite wing regarding buckling analysis is more effective when the laminates are stacked up with high percent of ±45° plies and the ±45° plies are located toward outside through the laminate.
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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 (March 1, 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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Gandhi, Yogesh, Alessandro Pirondi, and Luca Collini. "Optimal Design of Shape Memory Alloy Composite under Deflection Constraint." Materials 12, no. 11 (May 28, 2019): 1733. http://dx.doi.org/10.3390/ma12111733.
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Shape-adaptive or morphing capability in both aerospace structures and wind turbine blade design is regarded as significant to increase aerodynamic performance and simplify mechanisms by reducing the number of moving parts. The underlying bistable behavior of asymmetric cross-ply composites makes them a suitable candidate for morphing applications. To date, various theoretical and experiential studies have been carried out to understand and predict the bistable behavior of asymmetric laminates and especially the curvature obtained in their stable configurations. However, when the bi-stable composite plate is integrated with shape memory alloy wires to control the curvature and to snap from a stable configuration to the other (shape memory alloy composite, SMAC), the identification of the design parameters, namely laminate edge length, ply thickness and ply orientation, is not straightforward. The aim of this article is to present the formulation of an optimization problem for the parameters of an asymmetric composite laminate integrated with pre-stressed shape memory alloys (SMA) wires under bi-stability and a minimum deflection requirement. Wires are modeled as an additional ply placed at the mid-plane of the composite host plate. The optimization problem is solved numerically in MATLAB and optimal design variables are then used to model the SMAC in ABAQUS™. Finite element results are compared against numerical results for validation.
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Liu, Thomas Jin Chee, Jin Wei Liang, Wei Long Chen, and Teng Hui Chen. "Stacking Design of Composite Laminate in Wheelchair Structure under Seat Loading." Advanced Materials Research 1025-1026 (September 2014): 336–44. http://dx.doi.org/10.4028/www.scientific.net/amr.1025-1026.336.
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For designing the wheelchair structure under the seat loading, the stresses and failure indexes in each ply of the composite laminate are obtained by the finite element analysis. Using the Tsai-Wu criterion and delamination criterion, the stacking sequence [04/904/454/-45]sis the final optimal design for the wheelchair frame. On the contrary, the uni-directional laminates, i.e. [9013] s, [4513] s and [-4513] s, are bad designs.
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A R, Sreadha, and Chitaranjan Pany. "Static, Free Vibration and Buckling Analysis of Composite Panels; A Review." Advanced Journal of Graduate Research 9, no. 1 (November 27, 2020): 21–45. http://dx.doi.org/10.21467/ajgr.9.1.21-45.
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A composite material is generally a combination of materials differing in composition or form on a macro scale for the purposes of attaining specific characteristics and properties. The developments in the field of composite materials have granted significant weight reduction in structural design. When compared to metallic materials, composites offer many advantages, especially high strength, stiffness to weight ratio, excellent fatigue properties, and corrosion resistance. Plates, curved panels, the cylindrical shell-shaped forms of models are being broadly used in many structural packages of engineering structure. For design the structure, it is important to know the behaviour of these under static, free vibration, buckling condition. The present paper aims to review the literature on static, free vibration, and buckling analysis of composite flat panel, curved panel, and cylindrical shell. Further, the testing procedure of laminate, design guidelines of laminates and cost estimations with mechanical properties comparison of laminate with metal, CLT (classical lamination theory) basis including thermal and moisture expansion for stiffness evaluation are also summarised in this paper.
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Lee, Sang Jin, and Sang Ho Lee. "High-Toughening Alumina Composites Weakened by Metastable Hexacelsian Interphases." Key Engineering Materials 345-346 (August 2007): 721–24. http://dx.doi.org/10.4028/www.scientific.net/kem.345-346.721.
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New laminate design for improved toughness in hexacelsian-alumina composite is introduced. The composite is based on crack deflection in a weak interphase in the alumina matrix and hexacelsian interphase. The strength and toughness of the laminated composite were studied both qualitatively by electronic microscopy and measuring flexure strength. The metastable hexacelsian interphases had partially microcracks to provide crack deflection in the composite, and the crack deflection noticeably proceeded along the meta-stable hexacelsian interphase. Load-deflection curve for the laminate showed improved work of fracture of 2.23 kJ/m2.
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Rubio-González, C., E. José-Trujillo, F. Chávez, and A. Ruiz. "Low velocity impact response of composites and fiber metal laminates with open holes." Journal of Composite Materials 51, no. 6 (July 28, 2016): 797–810. http://dx.doi.org/10.1177/0021998316653817.
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Low-velocity impact response of glass/epoxy composite plates and fiber metal laminates with and without holes is investigated. The critical parameters that affect the delamination characteristics of laminates are impact energy, holes separation distance, type and directionality of fibers. An experimental investigation has been conducted to evaluate the effect of the presence of holes and the incorporation of aluminum layers in the extent of delamination. The extent of damage introduced during the impact event was observed on images obtained from C-scan non-destructive ultrasonic technique. Results indicate that fiber metal laminate made with aluminum layers exhibits an improved dynamic response in comparison with that of conventional laminates. The beneficial effect of using aluminum layers to reduce the extent of delamination produced by impact loading especially on laminates with holes is demonstrated. Furthermore, fiber metal laminates show better load carrying capability than conventional composite plates. The better response of fiber metal laminate with multidirectional fabric in comparison with fiber metal laminate with woven fabric is also examined. These results may be useful to better design the location of holes in composite structures.
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Hsu, F. J. K., and E. P. Fahrenthold. "Evaluation of the Vanishing Fiber Diameter Model for Composite Plasticity." Journal of Engineering Materials and Technology 113, no. 4 (October 1, 1991): 465–74. http://dx.doi.org/10.1115/1.2904127.
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The Vanishing Fiber Diameter (VFD) model for composite plasticity offers a computationally efficient approach to composite structural analysis and design problems. However this material model provides rather inaccurate predictions of composite deformation in a direction transverse to the fiber reinforcement. Empirical modification of the model is generally required to account for mesomechanical effects not present in the basic theory. Although systematic empirical modification of the VFD approach can provide accurate models of unidirectional composites, similarly accurate models of more complex laminates do not necessarily follow. The results suggest that laminate material models based on orthotropic lamina substructures do not in general provide a suitable basis for elastic-plastic structural design.
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Wang, Man, Rui Xiang Bai, and Ru Wang. "Tensile Test of Composite Laminates and Specimen's Improvement." Advanced Materials Research 738 (August 2013): 73–77. http://dx.doi.org/10.4028/www.scientific.net/amr.738.73.
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To obtain the material parameters for the composite laminate structure based on the general strength theory and failure criterion, a series of strength experiments are required to be carried out for some typical laminated fiber reinforced composite laminate plate. Due to complexity of stress state of specimen, some unexpected failure modes will often appear in the tensile test process of composite laminated plate. In this paper, according to the tensile test, the analysis for the failure mechanism of the specimen was executed by using finite element method. The suggestion for suitable geometry of the specimen was put forward, and the experimental results proved that the improvement for the specimen design was effective, thus the success rate of test was improved.
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Ghasemnejad, H., H. Hadavinia, and E. Lewis. "Crushing Behaviour of CFRP Composite Structure." Key Engineering Materials 385-387 (July 2008): 85–88. http://dx.doi.org/10.4028/www.scientific.net/kem.385-387.85.
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The present paper investigates specific sustained crushing stress (SSCS) of various composite laminate designs and stiffened boxes under axial crushing test. In this regard, an optimum composite crash box design is sought by studying the effect of laminate design and stiffeners on SSCS. Crash boxes were fabricated from carbon/epoxy twill-weave fabrics of [0]4, [45]4 and [0,45]2. The progressive failure with three distinct crushing modes of transverse shearing, lamina bending and brittle fracture was observed for three laminate designs. Two new assembled composite boxes were made from channels and V-shape stiffener and tested in quasi-static condition. Adhesive bonding was used in joining the channelled and stiffened boxes. Measured amount of SSCS for all models were compared to find an optimum crash box. It was found SSCS increases with increasing proportion of 0° plies in the laminate.
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Wang, Gong Dong, Jun Wang, and Hao Chen. "Application of Operator Libraries on Laminate Strength Optimization of Composites." Advanced Materials Research 853 (December 2013): 686–92. http://dx.doi.org/10.4028/www.scientific.net/amr.853.686.
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An improved Memetic algorithm is applied in this article. Mathematical model is proposed to optimize the laminate strength. The composites laminate strength optimization system with local operator library and rule operator library has been developed by the object-oriented programming with C++. The local operator has contributed to increase the convergence rate and the rule operators have contributed to implement practical design aspects in optimization of laminated composite plates. A numerical example demonstrates the validity of optimization model and practical applicability of the improved Memetic algorithm; hence, exhibiting the improvement of the method in tackling the stacking sequence.
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Wu, Xiang-Fa, and Oksana Zholobko. "Experimental Study of the Probabilistic Fatigue Residual Strength of a Carbon Fiber-Reinforced Polymer Matrix Composite." Journal of Composites Science 4, no. 4 (November 21, 2020): 173. http://dx.doi.org/10.3390/jcs4040173.
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Degradation of the mechanical properties of fiber-reinforced polymer matrix composites (PMCs) subjected to cyclic loading is crucial to the long-term load-carrying capability of PMC structures in practice. This paper reports the experimental study of fatigue residual tensile strength and its probabilistic distribution in a carbon fiber-reinforced PMC laminate made of unidirectional (UD) carbon-fiber/epoxy prepregs (Hexcel T2G190/F263) with the ply layup [0/±45/90]S after certain cycles of cyclic loading. The residual tensile strengths of the PMC laminates after cyclic loading of 1 (quasistatic), 2000, and 10,000 cycles were determined. Statistical analysis of the experimental data shows that the fatigue residual tensile strength of the PMC laminate follows a two-parameter Weibull distribution model with the credibility ≥ 95%. With increasing fatigue cycles, the mean value of the fatigue residual strength of the PMC specimens decreased while its deviation increased. A free-edge stress model is further adopted to explain the fatigue failure initiation of the composite laminate. The present experimental study is valuable for understanding the fatigue durability of PMC laminates as well as reliable design and performance prediction of composite structures.
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Kajale, Pranali Yogesh. "Design Optimization of Composite Lay-up Sequence and Orientation to Achieve Minimum Weight for Racing Seat." International Journal of Recent Technology and Engineering (IJRTE) 10, no. 3 (September 30, 2021): 157–63. http://dx.doi.org/10.35940/ijrte.c6453.0910321.
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Composites have proved their usefulness in the automotive industry during recent years. Many automobile companies use them in different parts to reduce weight without hampering strength. In a composite material, Lay-up sequence and orientation highly affects the properties of the laminate. Therefore, it is important to perform design optimization on a component to achieve high strength in minimum weight. This paper deals with the optimization of lay-up for composite Racing Seat using finite element analysis. Different lay-up sequences for laminates including, cross-ply [0/90]n, angle-ply [±α]n, and [0/90/±α]n are analysed. The lay-up sequence, orientation and ply number are optimized using composite material carbon fibre/Epoxy. Driver’s ergonomics and impact sustainability are considered constraints for weight optimization. Driver’s ergonomics were based on 95th percentile male and 5th percentile female rule. Force analysis is performed on the seat according to SFI 39.2 to evaluate the strength requirement. Finite element analysis of composite racing seat is performed via commercial finite element code ANSYS and using the capabilities of ANSYS Composite PrepPost (ACP) to form desired composite lay-up. A finite element code is based on classical lamination theory; including Puck’s failure criterion for first-ply failure. The seat is divided into three portions with a different number of layers considering the values and specific nature of acting forces; which resulted in different thicknesses in different regions. The optimization results show that for all the angles of Angle-ply laminate considered, Angle-ply laminates with an angle of 45⁰ provides a more optimum design. The minimum weight obtained is 10.15 kg.
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Moazed, Reza, Mohammad Amir Khozeimeh, and Reza Fotouhi. "Simplified Approach for Parameter Selection and Analysis of Carbon and Glass Fiber Reinforced Composite Beams." Journal of Composites Science 5, no. 8 (August 18, 2021): 220. http://dx.doi.org/10.3390/jcs5080220.
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In this study, a simplified approach that can be used for the selection of the design parameters of carbon and glass fiber reinforced composite beams is presented. Important design parameters including fiber angle orientation, laminate thickness, materials of construction, cross-sectional shape, and mass are considered. To allow for the integrated selection of these parameters, structural indices and efficiency metrics are developed and plotted in design charts. As the design parameters depend on mode of loading, normalized structural metrics are defined for axial, bending, torsional, and combined bending-torsional loading conditions. The design charts provide designers with an accurate and efficient approach for the determination of stiffness parameters and mass of laminated composite beams. Using the design charts, designers can readily determine optimum fiber direction, number of layers in a laminate, cross-sectional shape, and materials that will provide the desired mass and stiffness. The laminated composite beams were also analyzed through a detailed finite element analysis study. Three-dimensional solid elements were used for the finite element modelling of the beams. To confirm design accuracy, numerical results were compared with close-form solutions and results obtained from the design charts. To show the effectiveness of the design charts, the simplified method was utilized for increasing the bending and torsional stiffness of a laminated composite robotic arm. The results show that the proposed approach can be used to accurately and efficiently analyze composite beams that fall within the boundaries of the design charts.
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Liu, G. R., K. Y. Lam, and E. S. Chan. "Stress Waves in Composite Laminates Excited by Transverse Plane Shock Waves." Shock and Vibration 3, no. 6 (1996): 419–33. http://dx.doi.org/10.1155/1996/382362.
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A simple 1-dimensional model is presented to investigate elastic stress waves in composite laminates excited by underwater explosion shocks. The focus is on the elastic dynamic stress fields in the composite laminate immediately after the action of the shock wave. In this model, the interaction between the laminate and the water is taken into account, and the effects of the laminate-water interaction on the stress wave fields in the laminate are investigated. In the formulation of the model, wave fields in the laminate and the water are the first obtained in the frequency domain and then transferred into the time domain using the Fourier transform techniques. A quadrature technique is used to deal with the Fourier transform integrals in which the integrands have very sharp peaks on the integral axis. Numerical examples for stress waves in a steel plate and a glass reinforced plastic sandwich laminate are presented. The technique and the results presented in this article may be used in the design of ship hull structures subjected to underwater explosions.
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Mastrogiannakis, Iakovos, and George-Christopher Vosniakos. "EXPLORING STRUCTURAL DESIGN OF THE FRANCIS HYDRO-TURBINE BLADES USING COMPOSITE MATERIALS." Facta Universitatis, Series: Mechanical Engineering 18, no. 1 (March 27, 2020): 043. http://dx.doi.org/10.22190/fume190609001m.
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Composite materials are increasingly exploited in industry especially replacing metallic structures due to their strength/weight ratio. Amongst the notable applications, for which composite materials have not challenged metals yet are hydro-turbines, which are overwhelmingly made of steel or copper alloys. Replacing blade material by laminate composites can reduce weight and inertia, as well as achieve smaller cross-sectional thicknesses, better fatigue strength, damping, and resistance to cavitation. Manufacturing techniques are mature enough to respond to the challenge, provided that the laminate composite blades are properly designed. In the current work, the design of the Francis carbon blades was studied by employing finite element analysis. The blades were designed sub-optimally with various stratification patterns and different failure and maximum displacement limitations following a systematic methodology for gradual addition of laminate layers or patches. The methodology is still of a trial and error nature driven by the designer but guesses in the individual steps are much more informed due to model analysis and optimization tools available.
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Groh, R. M. J., and P. M. Weaver. "Deleterious localized stress fields: the effects of boundaries and stiffness tailoring in anisotropic laminated plates." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 472, no. 2194 (October 2016): 20160391. http://dx.doi.org/10.1098/rspa.2016.0391.
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The safe design of primary load-bearing structures requires accurate prediction of stresses, especially in the vicinity of geometric discontinuities where deleterious three-dimensional stress fields can be induced. Even for thin-walled structures significant through-thickness stresses arise at edges and boundaries, and this is especially precarious for laminates of advanced fibre-reinforced composites because through-thickness stresses are the predominant drivers in delamination failure. Here, we use a higher-order equivalent single-layer model derived from the Hellinger–Reissner mixed variational principle to examine boundary layer effects in laminated plates comprising constant-stiffness and variable-stiffness laminae and deforming statically in cylindrical bending. The results show that zigzag deformations, which arise due to layerwise differences in the transverse shear moduli, drive boundary layers towards clamped edges and are therefore critically important in quantifying localized stress gradients. The relative significance of the boundary layer scales with the degree of layerwise anisotropy and the thickness to characteristic length ratio. Finally, we demonstrate that the phenomenon of alternating positive and negative transverse shearing deformation through the thickness of composite laminates, previously only observed at clamped boundaries, can also occur at other locations as a result of smoothly varying the material properties over the in-plane dimensions of the laminate.
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Jin, Peng, Bi Feng Song, and Xiao Ping Zhong. "Aeroelastic Tailoring of Blended Composite Panels with Lamination Parameters." Applied Mechanics and Materials 401-403 (September 2013): 571–77. http://dx.doi.org/10.4028/www.scientific.net/amm.401-403.571.
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An optimization method for blended composite panels with aeroelastic constraint is presented in this paper. On the basis of composite panel sub-region division, the lamination parameters of a guide laminate and length indicator of each ply of the guide laminate are introduced as design variables using parallel genetic algorithm (GA) for optimization. For each individual, the inverse problem of obtaining laminate configuration to target the lamination parameters is solved by another GA. The method of defining design variables can reduce the number of design variables obviously compared with previous work. And the numerical results indicate that the present method is capable of producing fully blended designs of composite wing with aeroelastic performance improvement and weight reduction.
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Wang, Gong-Dong, Jun Wang, Sayed K. M. Hossain, and Hao Chen. "Research on design rules for composite laminate." Science and Engineering of Composite Materials 22, no. 3 (May 1, 2015): 315–23. http://dx.doi.org/10.1515/secm-2013-0251.
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AbstractA methodology of laminate design rules is proposed to incorporate constraint in genetic algorithm (GA). It can provide optimization result that conforms to the composite design rules. Several methods such as replacement approach, swap approach, combined approach, and zero fitness approach are introduced to execute the laminate design rules concept. Effects are analyzed in terms of fitness value and convergence rate. Using rule operators, the convergence speed of the GA is increased. The proposed solutions will be more suitable than standard GA for some particular application with their conformance to the design rules. As a result, these methods are successfully applied and a practical optimal stacking sequence is obtained with the most appropriate for design rules.
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Mohd Zairil Hafizi, Mohd Zailani, Mohd Din Muhamad Irwan, Mohd Adnan Zurri Adam, and Jamaluddin Mahmud. "A Framework for Experimental-Numerical Analysis of Woven Laminates Failure." Applied Mechanics and Materials 680 (October 2014): 245–48. http://dx.doi.org/10.4028/www.scientific.net/amm.680.245.
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Woven composite laminates have been widely used in various application and rapidly replacing unidirectional composite laminates. Thus, it is vital to understand clearly their material parameters and characteristic. Apparently, it is very difficult to analyse the design parameters of a unidirectional composite laminate, and thus due to its weaving structure, analysing numerically the parameters of a woven composite laminate is even more difficult. Therefore, this paper aims to review the work related to woven laminates with respect to its testing and simulations. During the initial stage, a tensile test is conducted according to ASTM D3039 on the 2×2 twill weave carbon fibre woven prepeg where the material constants (E1, E2, G12 and ν12) and the deformation behaviour will be obtained. The later stage will involve the development of a finite element modelling and simulation by means of commercial finite element package ANSYS 14.0 to replicate the experimental set-up. Ultimately, the outcomes and findings between the experimental and numerical approaches will be compared and reported.
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Jin, P., X. Zhong, J. Yang, and Z. Sun. "Blending design of composite panels with lamination parameters." Aeronautical Journal 120, no. 1233 (August 30, 2016): 1710–25. http://dx.doi.org/10.1017/aer.2016.88.
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ABSTRACTIn this paper, a new optimisation method incorporating lamination parameters and a guide-based blending model is proposed. Lamination parameters for a guide laminate and ply number of each panel are employed as design variables for optimisation with a parallel real-coded genetic algorithm incorporating structure behaviour and manufacturing constraints. During the optimisation process, with a form of least squares fitting adopted, another genetic algorithm is used to obtain the guide stacking sequence of the guide laminate from the guide lamination parameters, and then the laminate configurations of each panel are obtained from the guide stacking sequence and number of plies for each panel. The proposed framework is demonstrated via design of an 18-panel horseshoe configuration, where each panel is optimised individually with a buckling constraint. Numerical results indicate that the present algorithm is capable of obtaining fully blended designs.
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Yan, Li, Xue Feng An, Chen Qian Zhang, and Xiao Su Yi. "Impact Damage Behavior of Composite Stiffened Plates." Applied Mechanics and Materials 117-119 (October 2011): 954–57. http://dx.doi.org/10.4028/www.scientific.net/amm.117-119.954.
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Damage behavior of composite stiffened plates of structure I and structure II at different positions and under different impact energy subjected to low-velocity impact testing was studied in this paper. Visual observation and ultrasonic C-scanning were also employed to inspect the damage size. The results showed that damage behavior of composite stiffened plates was not only related to damage behavior of laminates, but also related to damage between stringer and laminate and damage of stringer itself. It was found that the mechanism of absorbing energy varies with the impact position, as well as the damage behavior. When the impact position was near stringer, partial energy was absorbed by stringer to make stringer and laminate disengage and damage area of laminates was smaller. Damage behavior of composite stiffened plates varies with the structure. Damage area of samples of structure II was smaller than that of samples of structure I. It was estimated preliminarily that design of structure II was better than that of structure I.
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Peeters, Daniël, and Mostafa Abdalla. "Design Guidelines in Nonconventional Composite Laminate Optimization." Journal of Aircraft 54, no. 4 (July 2017): 1454–64. http://dx.doi.org/10.2514/1.c034087.
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Ijaz, Hassan, L. Gornet, M. A. Khan, W. Saleem, K. Nisar, and S. R. Chaudry. "Prediction of Delamination Crack Growth in Carbon/Fiber Epoxy Composite Laminates Using a Non-Local Cohesive Zone Modeling." Advanced Materials Research 570 (September 2012): 25–36. http://dx.doi.org/10.4028/www.scientific.net/amr.570.25.
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The global behavior of composite materials is strongly influenced by the quality of adhesion between different components. A component can be single phase, like fibers or particles used as reinforcement in a homogenous matrix, or a multiphase material like a layer in long-fiber laminate. In the latter case the degradation of adhesion implies the separation of the layers, known as delamination. Among all different failure mechanisms, Delamination is considered to be the most prominent mode of failure in fiber-reinforced laminates as a result of their relatively weak inter-laminar strength. When laminated structures are subjected to static, dynamic or cyclic loadings, the inter-laminar adhesion strength between individual plies tends to deteriorate significantly and act as the origin of the final failure. Therefore, an efficient and reliable design tool capable of predicting delamination could improve the durability for composite laminates. There exist damage mechanics based formulations capable of simulating the delamination crack growth in carbon/glass fiber epoxy based composite laminates. The present study is focused on taking a step forward in this respect. At first, already existed local interface models effectiveness is tested and results are successfully compared with available experimental data for UD IMS/924 Carbon/fiber epoxy composite laminate. Next, a non-local integral-type regularization scheme is introduced to overcome the spurious localization problem associated to the existing local model. Basic concepts and mathematical modeling of Non-Local damage evolution law are comprehensively studied and presented in this study. Finite Element simulation results based on proposed model are discussed in detail and are compared with experimental results.
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Chen, Z., and J. J. Mecholsky. "Control of strength and toughness of ceramic/metal laminates using interface design." Journal of Materials Research 8, no. 9 (September 1993): 2362–69. http://dx.doi.org/10.1557/jmr.1993.2362.
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The fracture strength and toughness of alumina can be increased by lamination with strategically placed nickel layers and by controlling the geometry of the interfaces. This paper describes the interface design of a ceramic/metal bonded system produced by changing the surface topography of the interface between the metal and ceramic layers in order to vary the strength of bonding. The tortuosity of the interface is described quantitatively using fractal geometry. Experiments and models of single ductile layer laminates show that the work of fracture of ductile layers which contribute to the increment of toughness of ceramic/metal laminates is dependent on the tortuosity of the interface. The more tortuous the interface, the stronger the laminate; the smoother the interface, the tougher the laminate. The results are used to design a ceramic/metal multilayer composite. The strength and toughness of the laminates can be controlled by the tortuosity of the interface and characterized using the fractal dimension.
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Magar, Ashok, and Achchhe Lal. "Progressive failure analysis of laminated plate containing elliptical cutout." International Journal of Structural Integrity 12, no. 4 (April 9, 2021): 569–88. http://dx.doi.org/10.1108/ijsi-10-2020-0092.
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PurposeThe prediction of accurate failure strength and a composite laminate failure load is of paramount importance for reliable design. The progressive failure analysis helps to predict the ultimate failure strength of the laminate, which is more than the first ply failure (FPF) strength. The presence of a hole in the laminate plate results in stress concentration, which affects the failure strength. The purpose of the current work is to analyze the stress variation and progressive failure of a symmetric laminated plate containing elliptical cutouts under in-plane tensile loading. The effect of various parameters on FPF and last ply failure (LPF) strength is studied.Design/methodology/approachThe ply-by-ply stresses around elliptical cutouts are obtained analytically using Muskhelishvili's complex variable formulation. To predict the progressive failure, Tsai–Hill (T-H) and Tsai–Wu (T-W) failure criteria are used, and depending on the mode of failure, lamina modulus is degraded.FindingsThe study has revealed that fiber orientation and stacking sequence for given loading have the most significant effect on the laminate's failure strength.Originality/valueComplex variable method and conformal mapping are simple and proficient for studying failure analysis of a laminated plate with elliptical cutout.
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Naidubabu, Y., G. Mohana Rao, K. Rajasekhar, and B. Ratna Sunil. "Design and simulation of polymethyl methacrylate-titanium composite bone fixing plates using finite element analysis: Optimizing the composition to minimize the stress shielding effect." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 231, no. 23 (September 8, 2016): 4402–12. http://dx.doi.org/10.1177/0954406216668550.
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Stress shielding is a mechanical phenomenon usually found in load-bearing bone implants. Difference in mechanical properties between the natural bone and the artificial implant leads to stress shielding problem. In the present work, polymethyl methacrylate and commercial pure titanium were selected to design laminate and particulate composites. Optimum composition was theoretically obtained that exhibits mechanical properties close to that of natural human bone. Bone fixing plate was designed for femur bone using computer-aided design. Finite element analysis was adopted to analyze the stress distribution in the bone and implant under static load conditions. Fixing plate with three screws was modeled and simulated using finite element analysis to investigate the stress distribution. Simulation was also done considering 316 L stainless steel as fixing implant and compared with the present optimized composition. Laminate composite with 0.3 volume fraction of titanium has shown mechanical properties close to the bone compared with other combinations. The results have clearly shown that the von-Mises stress induced in the bone with polymethyl methacrylate-titanium laminate composite plates was increased compared with the bone implanted with 316 L steel. Interestingly, laminate composites exhibited higher stresses in the bone compared with particulate composites. From the present design and simulation, it is clearly demonstrated that the laminate composites of polymethyl methacrylate–30% titanium can be an optimum choice for load-bearing implant materials with reduced stress shielding effect.