Relevant bibliographies by topics / Laminated composite material

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  4. Book chapters
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Academic literature on the topic 'Laminated composite material'

Author: Grafiati
Published: 4 June 2021
Last updated: 28 January 2023

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Journal articles on the topic "Laminated composite material"

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Dibyajyoti, D., and B. Alfia. "Review on laminated composite plates." Proceedings of the 12th Structural Engineering Convention, SEC 2022: Themes 1-2 1, no. 1 (2022): 83–88. http://dx.doi.org/10.38208/acp.v1.477.

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A composite material is a combination of different material which can be assembled to provide required engineering properties like bending, buckling, stiffness etc. It can give better properties than those of individual components. A lamina is the building block of modern composite laminated structures. A lamina is also known as a ply, or a layer. A laminate has several layers of lamina, or laminae. Since the early years of engineering, various types of laminated composite materials have been used in various engineering fields, such as in aerospace, military and automotive industries that are subjected to high temperatures. Thermal stress caused due to change in temperature, increase in temperature causes the changes in material properties of a plate which in turn complicates the analysis and design and may affect the structure also. Therefore, the analysis of thermal stress in design of structure is very important. A critical review of available literature for the prediction of the behaviour of laminated composites under thermal conditions is carried out and summarized. This work attempts to review the studies carried out from 2000 on laminated composite plates by representing classification based on Classical laminate plate concept, First order shear deformation theory, Higher order shear deformation theory, Layerwise theory and Thermal stress on laminated plates.
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Ramadhan, Redha Akbar, Muhamad Giri Suada, and Hendri Syamsudin. "A FINITE ELEMENT ANALYSIS OF CRITICAL BUCKLING LOAD OF COMPOSITE PLATE AFTER LOW VELOCITY IMPACT." Jurnal Teknologi Dirgantara 18, no. 2 (2020): 195. http://dx.doi.org/10.30536/j.jtd.2020.v18.a3328.

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Composite is a material formed from two or more materials that macroscopically alloyed into one material. Nowadays, composite has been generally applied as lightweight structure of aircraft. This is due to the fact that composites having high strength-to-weight ratio. It means the composites have the capability to take on various loads, despite their lightweight property.Laminate composite is one type of composite that has been generally used in aircraft industries. This type of composite is susceptible to low-velocity impact induced damage. This type of damage can be happening in manufacture, operation, or even in maintenance. Low-velocity impact could cause delamination. Delamination happens when the plies of laminated composites separated at the interface of the plies. This type of damage is categorized as barely visible damage, means that the damage couldn’t be detected with visual inspection. Special method and tool would be needed to detect the damage. Delamination will decrease the strength of the laminated composite.Delamination can be predicted with numerical simulation analysis. With increasing capability of computer, it is possible to predict the delamination and buckling of laminated composite plate. This research presents the comparisons of buckling analysis results on laminated plate composite and damaged laminated plate composite. By the result of LVI simulation, it is shown that low velocity impact of 19.3 Joule causing 6398 mm2 C-Scan delamination area inside the laminated composite. The delamination causing structural instability that will affect buckling resistance of the plate. The result of analysis shows that the existence of delamination inside laminate composite will lower its critical buckling load up to 90% of undamaged laminate’s critical buckling load.Keywords : composite, laminate, delamination, buckling.
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Gajbhiye, ParamD, Vishisht Bhaiya, and YuwarajM Ghugal. "Bending Analysis of Orthotropic Plate using 5th Order Shear Deformation Theory." Proceedings of the 12th Structural Engineering Convention, SEC 2022: Themes 1-2 1, no. 1 (2022): 89–94. http://dx.doi.org/10.38208/acp.v1.478.

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A composite material is a combination of different material which can be assembled to provide required engineering properties like bending, buckling, stiffness etc. It can give better properties than those of individual components. A lamina is the building block of modern composite laminated structures. A lamina is also known as a ply, or a layer. A laminate has several layers of lamina, or laminae. Since the early years of engineering, various types of laminated composite materials have been used in various engineering fields, such as in aerospace, military and automotive industries that are subjected to high temperatures. Thermal stress caused due to change in temperature, increase in temperature causes the changes in material properties of a plate which in turn complicates the analysis and design and may affect the structure also. Therefore, the analysis of thermal stress in design of structure is very important. A critical review of available literature for the prediction of the behaviour of laminated composites under thermal conditions is carried out and summarized. This work attempts to review the studies carried out from 2000 on laminated composite plates by representing classification based on Classical laminate plate concept, First order shear deformation theory, Higher order shear deformation theory, Layerwise theory and Thermal stress on laminated plates.
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4

bin Yaakob, Mohd Yuhazri, T. T. T. Jennise, H. Sihombing, N. Mohamad, S. H. Yahaya, and M. Y. A. Zalkis. "Water Absorption and Thickness Swelling of Laminated Composite after Cured at Different Angle." Applied Mechanics and Materials 465-466 (December 2013): 86–90. http://dx.doi.org/10.4028/www.scientific.net/amm.465-466.86.

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Moisture absorption is a very important factor in polymers and composite materials used for hull manufacture and stability in marine environment. High water absorption of the material will affects the mechanical properties and stability in composite. This research is carried out to study the feasibility of the gravity effects on curing position of the laminated composite structures to enhance the curing space needed. Vertical cured laminate having almost similar properties with common horizontal cured laminate able to save much space in composite industry. Horizontal cured laminates filled up spaces in which SMI lack of. Polyesters and E-glass fibers were used as the raw material in this research. Vacuum bagging technique was used to suck out the excess resin during lay-up to avoid any voids and air inside laminate and cured at different angle position in room temperature for 24 hours. Seven samples of laminated composite were fabricated and cut into specific dimension in accordance to ASTM standard. This paper will discuss about the investigation on the water absorption and thickness swelling of the thermosetting laminated composite by curing the laminate at different angle using vacuum bagging technique. From the testing, SN6 and SN7 shows to have good water resistant in physical properties.
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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 (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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Fakhruddin, Muhammad, Maskuri Maskuri, Elka Faizal, Bayu Pranoto, Hangga Wicaksono, and Hilmi Iman Firmansyah. "Pengaruh Perlakuan Permukaan Pengikatan Terhadap Sifat Mekanik Komposit Serat Kaca Dengan Laminasi Almunium." Jurnal Energi dan Teknologi Manufaktur (JETM) 4, no. 02 (2021): 27–32. http://dx.doi.org/10.33795/jetm.v4i02.79.

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Fiber metal laminates or commonly known as fiber metal laminates (FML) are composite structures made by combining 2 layers of material as the outer layer with the core material. The outer layer of this composite is called the laminate. Generally, laminated composites are produced by joining techniques under solid-state conditions, such as diffusion bonding, extrusion, friction-stir welding, and roller welding. In this study, glass fiber composites with aluminum lamination were made using the vacuum assisted resin infusion (VARI) method, using epoxy resin. The surface treatment of the aluminum laminate was carried out with the direction of roughing at certain angles and variations of the surface roughening of the laminate to test the mechanical bonding between the composite and the laminate. Mechanical bonding testing using three-point bending test method (three-point bending) and buckling test. The expected result is that by surface treatment on aluminum laminate, the best mechanical bonding to composites with glass fiber is obtained. The TKT to be achieved from this research is TKT level 3, which is an analytical study that supports the prediction of the performance of the effect of the bonding surface treatment on the mechanical properties of glass fiber composites with aluminum lamination.
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bin Yaakob, Mohd Yuhazri, T. T. T. Jennise, H. Sihombing, Qumrul Ahsan, S. T. W. Lau, and Mohd Imran bin Ghazali. "Gravity Effects on the Density of Laminated Composite due to the Differences in Angle Cured." Applied Mechanics and Materials 465-466 (December 2013): 81–85. http://dx.doi.org/10.4028/www.scientific.net/amm.465-466.81.

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This research is carried out to study the feasibility of the gravity effects on curing position of the laminated composite structures to enhance the curing space needed. Vertical cured laminate having almost similar properties with common horizontal cured laminate able to save much space in composite industry especially for developing Small and Medium Industry (SMI). Horizontal cured laminates filled up spaces in which SMI lack of. Polyesters and E-glass fibers were used as the raw material in this research. Vacuum bagging technique was used to suck out the excess resin during lay-up to avoid any voids and air inside laminate and cured at different angle position in room temperature for 24 hours. Seven samples of laminated composite were fabricated and cut into specific dimension in accordance to ASTM standard. The aim of the research was to investigate the density property of the thermosetting laminated composite by curing the laminate at different angle using vacuum bagging technique. From the testing, SN6 had the same density value with control sample, SN1 that had value of 1.46 g/cm3.
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Luo, Shen-Yi, and Faruk Taban. "Deformation of Laminated Elastomer Composites." Rubber Chemistry and Technology 72, no. 1 (1999): 212–24. http://dx.doi.org/10.5254/1.3538791.

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Abstract Flexible elastomer composites subjected to finite deformation are usually associated with significant fiber re-orientation and configuration change which cannot be described by classical composite lamination theory. Utilizing the Lagrangian description and a strain-energy density approach, this work presents a set of 2-D constitutive equations in terms of the overall deformation of laminated composites. This model includes both geometric and material nonlinearities of the laminate. Interlaminar shear deformation is addressed but not studied in this analysis. Theoretical predictions have been compared with the available experimental data about symmetric laminates with various fiber orientations in the finite deformation range. Also, a parametric study has been performed under various ratios of biaxial deformation.
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Luccioni, Bibiana M. "Constitutive Model for Fiber-Reinforced Composite Laminates." Journal of Applied Mechanics 73, no. 6 (2006): 901–10. http://dx.doi.org/10.1115/1.2200654.

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Nowadays, conventional materials have been progressively replaced by composite materials in a wide variety of applications. Particularly, fiber reinforced composite laminates are widely used. The appropriate design of elements made of this type of material requires the use of constitutive models capable of estimating their stiffness and strength. A general constitutive model for fiber reinforced laminated composites is presented in this paper. The model is obtained as a generalization of classical mixture theory taking into account the relations among the strains and stresses in the components and the composite in principal symmetry directions of the material. The constitutive equations for the laminated composite result from the combination of lamina constitutive equations that also result from the combination of fibers and matrix. It is assumed that each one of the components are orthotropic and elastoplastic. Basic assumptions of the proposed model and the resulting equations are first presented in the paper. The numerical algorithm developed for the implementation in a three-dimensional (3D) finite element nonlinear program is also described. The paper is completed with application examples and comparison with experimental results. The comparison shows the capacity of the proposed model for the simulation of stiffness and strength of different composite laminates.
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Xu, Jian, Pei Xian Zhu, Hui Yu Ma, and Sheng Gang Zhou. "Characterisation of Ti-Al and Ti-Cu Laminated Composite Electrode Materials." Advanced Materials Research 194-196 (February 2011): 1667–71. http://dx.doi.org/10.4028/www.scientific.net/amr.194-196.1667.

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We proposed using Ti-Al and Ti-Cu laminated composites instead of single Ti electrode metals, as well as studied the difference in performance between laminated composite electrode materials and pure-Ti electrode. The analysis of the conductivity and electrochemical performance of electrode matrix material indicates the result that the improvement of matrix material by using Ti-Al and Ti-Cu laminated composites, better performance for conductivity of electrode, and be beneficial to homogenize the electrode surface potential and current distribution and promote electrocatalytic activity between polar plates. Whereas comparison between Ti-Al and Ti-Cu laminated composites, Ti-Cu laminated composites is better in performance.
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Dissertations / Theses on the topic "Laminated composite material"

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Teh, Kuen Tat. "Impact damage resistance and tolerance of advanced composite material systems." Diss., This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-06062008-170512/.

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Chandrashekhara, K. "Geometric and material nonlinear analysis of laminated composite plates and shells." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/54739.

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An inelastic material model for laminated composite plates and shells is formulated and incorporated into a finite element model that accounts for both geometric nonlinearity and transverse shear stresses. The elasto-plastic material behavior is incorporated using the flow theory of plasticity. In particular, the modified version of Hill's initial yield criterion is used in which anisotropic parameters of plasticity are introduced with isotropic strain hardening. The shear deformation is accounted for using an extension of the Sanders shell theory and the geometric nonlinearity is considered in the sense of the von Karman strains. A doubly curved isoparametric rectangular element is used to model the shell equations. The layered element approach is adopted for the treatment of plastic behavior through the thickness. A wide range of numerical examples is presented for both static and dynamic analysis to demonstrate the validity and efficiency of the present approach. The results for combined nonlinearity are also presented. The results for isotropic results are in good agreement with those available in the literature. The variety of results presented here based on realistic material properties of more commonly used advanced laminated composite plates and shells should serve as references for future investigations.<br>Ph. D.
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Thielman, Scott C. "Design and optimization of a material property distribution in a laminated composite flywheel /." Thesis, Connect to this title online; UW restricted, 1997. http://hdl.handle.net/1773/7031.

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Rourk, Dave. "Geometric and material nonlinear effects in elastic-plastic and failure analyses of anisotropic laminated structures." Diss., Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/76492.

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In this study, an analytical procedure to predict the strength and failure of laminated composite structures under monotonically increasing static loads is presented. A degenerated 3-D shell finite element that includes linear elastic and plastic material behavior with full geometric nonlinearity is used to determine stresses at selected points (Gauss quadrature points in each element) of the structure. Material stiffness (constitutive) matrices are evaluated at each Gauss point, in each lamina and in each element, and when the computed stress state violates a user selected failure criterion, the material stiffness matrix at the failed Gauss point is reduced. The reduction procedure involves setting the material stiffnesses to unity. Examples of isotropic, orthotropic, anisotropic and composite laminates are presented to illustrate the validity of the procedure developed and to evaluate various failure theories. Maximum stress, modified Hills (Mathers), Tsai-Wu (F₁₂ = 0), and Hashin's failure criteria are included. The results indicate that for large length-to-thickness ratios, the geometric nonlinear effect should be incorporated for both isotropic and anisotropic structures. The nonlinear material model influences the behavior of isotropic structures with small length-to-thickness ratios, while having nearly no effect at all on laminated anisotropic structures. Of the four failure theories compared, each predicts failure at nearly the same load levels and locations. Hashin's criterion is particularly noteworthy in that the mode is also predicted.<br>Ph. D.
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Gunel, Murat. "Linear And Nonlinear Progressive Failure Analysis Of Laminated Composite Aerospace Structures." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12614033/index.pdf.

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This thesis presents a finite element method based comparative study of linear and geometrically non-linear progressive failure analysis of thin walled composite aerospace structures, which are typically subjected to combined in-plane and out-of-plane loadings. Different ply and constituent based failure criteria and material property degradation schemes have been included in a PCL code to be executed in MSC Nastran. As case studies, progressive failure analyses of sample composite laminates with cut-outs under combined loading are executed to study the effect of geometric non-linearity on the first ply failure and progression of failure. Ply and constituent based failure criteria and different material property degradation schemes are also compared in terms of predicting the first ply failure and failure progression. For mode independent failure criteria, a method is proposed for the determination of separate material property degradation factors for fiber and matrix failures which are assumed to occur simultaneously. The results of the present study show that under combined out-of-plane and in-plane loading, linear analysis can significantly underestimate or overestimate the failure progression compared to geometrically non-linear analysis even at low levels of out-of-plane loading.
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Chee, Clinton Yat Kuan. "STATIC SHAPE CONTROL OF LAMINATED COMPOSITE PLATE SMART STRUCTURE USING PIEZOELECTRIC ACTUATORS �." University of Sydney. Aeronautical Engineering, 2000. http://hdl.handle.net/2123/709.

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The application of static shape control was investigated in this thesis particularly for a composite plate configuration using piezoelectric actuators. A new electro-mechanically coupled mathematical model was developed for the analysis and is based on a third order displacement field coupled with a layerwise electric potential concept. This formulation, TODL, is then implemented into a finite element program. The mathematical model represents an improvement over existing formulations used to model intelligent structures using piezoelectric materials as actuators and sensors. The reason is TODL does not only account for the electro-mechanical coupling within the adaptive material, it also accounts for the full structural coupling in the entire structure due to the piezoelectric material being attached to the host structure. The other significant improvement of TODL is that it is applicable to structures which are relatively thick whereas existing models are based on thin beam / plate theories. Consequently, transverse shearing effects are automatically accounted for in TODL and unlike first order shear deformation theories, shear correction factors are not required. The second major section of this thesis uses the TODL formulation in static shape control. Shape control is defined here as the determination of shape control parameters, including actuation voltage and actuator orientation configuration, such that the structure that is activated using these parameters will conform as close as possible to the desired shape. Several shape control strategies and consequently algorithms were developed here. Initial investigations in shape control has revealed many interesting issues which have been used in later investigations to improve shape controllability and also led to the development of improved algorithms. For instance, the use of discrete actuator patches has led to greater shape controllability and the use of slopes and curvatures as additional control criteria have resulted in significant reduction in internal stresses. The significance of optimizing actuator orientation and its relation to piezoelectric anisotropy in improving shape controllability has also been presented. Thus the major facets of shape control has been brought together and the algorithms developed here represent a comprehensive strategy to perform static shape control.
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Gordon, Neal A. "Material Health Monitoring of SIC/SIC Laminated Ceramic Matrix Composites With Acoustic Emission And Electrical Resistance." University of Akron / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=akron1414835900.

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Gu, Hanfeng. "Multigrid methods for 3D composite material simulation and crack propagation modelling based on a phase field method." Thesis, Lyon, 2016. http://www.theses.fr/2016LYSEI090/document.

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Avec le développement des techniques d’imagerie telles que la tomographie par rayons X au cours des dernières années, il est maintenant possible de prendre en compte la microstructure réelle dans les simulations des matériaux composites. Cependant, la complexité des composites tels que des fibres inclinées et brisées, les vides, exige un grand nombre des données à l’échelle microscopique pour décrire ces détails et amène ainsi des problèmes difficiles en termes de temps de calcul et de mémoire lors de l’utilisation de méthodes de simulation traditionnelles comme la méthode Eléments Finis. Ces problèmes deviennent encore plus sérieux dans la simulation de l’endommagement, comme la propagation des fissures. Par conséquent, il est nécessaire d’étudier des méthodes numériques plus efficaces pour ce genre de problèmes à grande échelle. La méthode Multigrille (MG) est une méthode qui peut être efficace parce que son coût de calcul est proportionnel au nombre d’inconnues. Dans cette thèse, un solveur de MG efficace pour ces problèmes est développé. La méthode MG est appliquée pour résoudre le problème d’élasticité statique basé sur l’équation de Lamé et aussi le problème de la propagation de fissures basé sur une méthode de champ de phase. La précision des solutions MG est validée par une solution analytique classique d’Eshelby. Ensuite, le solveur MG est développé pour étudier le processus d’homogénéisation des composites et ses solutions sont comparées avec des solutions existantes de la littérature. Après cela, le programme de calcul MG est appliqué pour simuler l’effet de bord libre dans les matériaux composites stratifiés. Une structure stratifiée réelle donnée par tomographie X est d’abord simulé. Enfin, le solveur MG est encore développé, combinant une méthode de champ de phase, pour simuler la rupture quasi-fragile. La méthode MG présente l’efficacité à la fois en temps de calcul et en mémoire pour résoudre les problèmes ci-dessus<br>With the development of imaging techniques like X-Ray tomography in recent years, it is now possible to take into account the microscopic details in composite material simulations. However, the composites' complex nature such as inclined and broken fibers, voids, requires rich data to describe these details and thus brings challenging problems in terms of computational time and memory when using traditional simulation methods like the Finite Element Method. These problems become even more severe in simulating failure processes like crack propagation. Hence, it is necessary to investigate more efficient numerical methods for this kind of large scale problems. The MultiGrid (MG) method is such an efficient method, as its computational cost is proportional to the number of unknowns. In this thesis, an efficient MG solver is developed for these problems. The MG method is applied to solve the static elasticity problem based on the Lame's equation and the crack propagation problem based on a phase field method. The accuracy of the MG solutions is validated with Eshelby's classic analytic solution. Then the MG solver is developed to investigate the composite homogenization process and its solutions are compared with existing solutions in the literature. After that, the MG solver is applied to simulate the free-edge effect in laminated composites. A real laminated structure using X-Ray tomography is first simulated. At last, the MG solver is further developed, combined with a phase field method, to simulate the brittle crack propagation. The MG method demonstrates its efficiency both in time and memory dimensions for solving the above problems
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Bovicelli, Federico. "On the influence of polymeric nanofibers in laminated composite materials. Studio dell'influenza di nanofibre polimeriche in materiali compositi laminati." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2014. http://amslaurea.unibo.it/6784/.

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During the last years an increased interest about the reinforcement of laminated composites by means of polymeric nanofibers has been growth. During this master-degree-thesis work, unidirectional and plane-textile composites have been interleaved with Nylon 6.6, PCL and mixed (Nylon 6.6+PCL) nanofibrous mats and the DCB (mode I interlaminar fracture toughness), ENF (mode II interlaminar fracture toughness and DMA (damping capability) tests have been performed. Regarding the interlaminar fracture toughness, marked increases have been recorded; while further investigation about damping capability is requested.
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Padoin, Eduardo. "Otimização topológica de cascas compostas laminadas com atuador piezelétrico para o controle de vibrações." reponame:Biblioteca Digital de Teses e Dissertações da UFRGS, 2014. http://hdl.handle.net/10183/115273.

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Este trabalho apresenta uma metodologia de otimização topológica de atuadores piezelétricos em estruturas compostas laminada com o objetivo de atenuar as vibrações estruturais induzidas por excitações externas. Para isso, utiliza-se técnicas de controle ótimo, como o regulador linear quadrático (LQR) e o controlador linear quadrático gaussiano (LQG). Os estados não mensuráveis são estimados através do uso de observadores de estados de ordem completa, usando o filtro de Kalman para a escolha ótima da matriz de ganhos do observador de estados. O problema de otimização topológica é formulado para a localização ótima do atuador piezelétrico composto MFC (Macro Fiber Composite) na camada ativa da placa, determinando a localização mais vantajosa do material MFC através da maximização do índice de controlabilidade. Para o modelo estrutural, é proposto neste trabalho um modelo para a interação entre o atuador MFC e a estrutura. Assume-se que o MFC é uma das lâminas de material ortotrópico que sofre uma deformação inicial a partir da aplicação de um potencial elétrico e que essa deformação terá efeitos sobre o restante da estrutura. Dessa maneira, não é necessário modelar o campo elétrico gerado através dos eletrodos, uma vez que o efeito eletromecânico é considerado analiticamente. A rigidez e a massa do atuador MFC são considerados no modelo estrutural. Os resultados numéricos mostram que o modelo estrutural proposto para representar a interação entre o atuador MFC e a estrutura apresenta boa concordância com resultados experimentais e numéricos encontrados. Além disso, os resultados mostram que a partir do posicionamento ótimo do atuador MFC na estrutura, a técnica de controle implementada permite atenuar as vibrações estruturais. As simulações para uma força de um degrau unitário permitem concluir que a estratégia de controle usando o controlado LQG apresenta melhor desempenho em termos de tempo de assentamento, sobre resposta, amortecimento e sinal de controle, quando comparado com o controlador LQR.<br>This work presents a topologic optimization methodology of piezoelectric actuators in laminated composite structures with the objective of controlling external perturbation induced by structural vibrations. The Linear Quadratic Regulator (LQR) and Linear Quadratic Gaussian (LQG) optimal control techniques are used. The states are estimated through of the full order state observers, using the Kalman filter to the observer gain matrix. The topology optimization is formulated to find the optimum localization of the Macro Fiber Composite (MFC) active piezoelectric patch, determining the most advantageous location of the MFC, through of the maximization of the controllability index. For the structural model, this work proposes a simplified MFC/structure interaction model. It is assumed that the MFC is one of the orthotropic material layers which has an initial strain arising from the application of an electric potential; this strain acts on the remainder of the structure. This way, modeling the electromechanical interaction between the piezoelectric material and the electric field is unnecessary because this effect is considered analytically. Both the stiffness and the mass of the MFC are taken into account in the structural model. Numerical results show that proposed MFC-structure interaction model presents good agreement with experiments and numerical simulations of models that uses the electromechanical effect. Actuator location optimization results show that the technique implemented improves the structural vibration damping. The response simulations to an unit step force allows to conclude that the control strategy using the LQG controller presents better performance in terms of settling time, overshoot, damping and control signal energy when compared to the LQR controller.
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Books on the topic "Laminated composite material"

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Harris, C. E. Preliminary report on tests of tensile specimens with a part-through surface notch for a filament wound graphite/epoxy material. National Aeronautics and Space Administration, Langley Research Center, 1985.

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Pettermann, Heinz. Derivation and finite element implementation of constitutive material laws for multiphase composites based on Mori-Tanaka approaches. VDI Verlag, 1997.

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Mechanics of composite materials. 2nd ed. Taylor & Francis, 1999.

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R, White S., ed. Stress analysis of fiber-reinforced composite materials. WCB McGraw-Hill, 1998.

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Air Force Wright Aeronautical Laboratories. Cumulative damage model for advanced composite materials. Materials Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1985.

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Reddy, J. N. A higher-order theory for geometrically nonlinear analysis of composite laminates. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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Reddy, J. N. A higher-order theory for geometrically nonlinear analysis of composite laminates. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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Reddy, J. N. A higher-order theory for geometrically nonlinear analysis of composite laminates. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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Reddy, J. N. A higher-order theory for geometrically nonlinear analysis of composite laminates. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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Staab, George H. Laminar composites. Butterworth-Heinemann, 1999.

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Book chapters on the topic "Laminated composite material"

1

Borri, A., E. Speranzini, and R. Vetturini. "Optimum Design of Laminated Composite Material Structures." In Computer Aided Design in Composite Material Technology III. Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2874-2_31.

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Adali, Sarp. "Optimization of Laminated Composites and Overview of Smart Material Applications." In Modern Trends in Composite Laminates Mechanics. Springer Vienna, 2003. http://dx.doi.org/10.1007/978-3-7091-2544-1_5.

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Brito, F. M. "The Boundary Between the Concepts of Material and Structure in the Plate and Shell Theories for Laminated Media." In Composite Structures 4. Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-009-3457-3_9.

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Han, J., and S. V. Hoa. "Three Dimensional Composite Elements for Finite Element Analysis of Anistropic Laminated Structures." In Computer Aided Design in Composite Material Technology III. Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2874-2_16.

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Machado, R. D., and C. S. Barcellos. "A First Modified Local Green’s Function Method Approach to Orthotropic Laminated Plates." In Computer Aided Design in Composite Material Technology III. Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2874-2_27.

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Olhoff, Niels, and Bin Niu. "Discrete Material Optimization of Vibrating Laminated Composite Plates for Minimum Sound Emission." In Topology Optimization in Structural and Continuum Mechanics. Springer Vienna, 2014. http://dx.doi.org/10.1007/978-3-7091-1643-2_15.

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

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AbstractFiber reinforced metal laminates (FMLs) are a kind of interlaminar hybrid composites made of metal sheets and fibers alternately stacked and cured at a certain pressure and temperature. In this paper, through the simulation of ABAQUS finite element software and recording the change of projectile velocity, the energy loss of projectile is calculated and the impact resistance is judged. Through the comparison of three groups of simulation experimental results, the energy absorbed by carbon fiber reinforced metal laminate is about 300 times that of aluminum alloy plate, which fully shows that carbon fiber reinforced metal composite has excellent impact resistance compared with aluminum alloy. After adding 1 wt% carbon nanotubes to carbon fiber reinforced metal laminates, the absorbed energy is about 10 times that of the original, which shows that carbon nanotubes improve the ultimate yield stress of resin and materials in epoxy resin and enhance the weakness that the composites are easy to delamination under impact load.
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Muzakkar, M. Z., S. Ahmad, M. A. Yarmo, A. Jalar, and M. Bijarimi. "Shear Strength of Single Lap Joint Aluminium-Thermoplastic Natural Rubber (Al-TPNR) Laminated Composite." In Recent Trends in Physics of Material Science and Technology. Springer Singapore, 2014. http://dx.doi.org/10.1007/978-981-287-128-2_10.

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Groppetti, R., A. Armanni, A. Cattaneo, and G. Franceschini. "Contribution to the Study of the Delamination of Carbon Fibre Reinforced Plastic (CFRP) Laminated Composites during Piercing and Cutting by Hydro Jet Machining (HJM) and Hydro Abrasive Jet Machining (HAJM)." In Computer Aided Design in Composite Material Technology III. Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2874-2_13.

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Le, Quoc-Cuong, and Ba-Duy Nguyen. "Buckling and Vibration Analysis Based on a Novel Unified Model for Laminated Composite Beams." In Proceedings of the 2nd Annual International Conference on Material, Machines and Methods for Sustainable Development (MMMS2020). Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-69610-8_57.

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Conference papers on the topic "Laminated composite material"

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Jung, Dongho, Hyeonju Kim, Moonho Tak, Kyungjae Lee, and Taehyo Park. "Dynamic Structural Analysis of a Large-Diameter Riser Consisting of Laminated Composite Material With a Hybrid Numerical Scheme." In ASME 2013 32nd International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/omae2013-10868.

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A hybrid numerical scheme is developed to analyze the structural dynamic behavior of a large-diameter riser made of a laminated composite material. The global dynamic behavior of the riser, considered as a beam element subjected to a wave and current, is solved with the finite element analysis method in the time domain. The equivalent elastic modulus of a laminated composite riser for the global dynamic analysis is calculated from the stress-strain relation of a laminate structure with a different elastic modulus. For elements in large displacement and stresses estimated from the dynamic analysis, local structural analysis is performed with the finite element analysis method to examine the structural safety of the laminates of the composite riser, which is considered as a hexahedral element. The developed hybrid numerical tool can contribute to structural safety verification of large-diameter risers composed of laminated composites.
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Arıko¨k, Rifat, and Zahit Mecitog˘lu. "Large Deflection of a Laminated Composite Plate With Different Extensional and Flexural Material Properties." In ASME 2010 International Mechanical Engineering Congress and Exposition. ASMEDC, 2010. http://dx.doi.org/10.1115/imece2010-40592.

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This paper presents the large deflection elastic analysis of the hand lay-up composite plates with different extensional and flexural modulus including geometric nonlinearity effects that are taken into account with the von Ka´rma´n large deflection theory of thin plates. Governing equations of the motion are derived by means of the virtual work principle. Then the Galerkin method is applied to reduce the nonlinear coupled differential equations into a nonlinear algebraic equation system. The MATLAB and MATHEMATICA software are used to solve the equation system. Because of the common nonuniformities in hand lay-up fabric laminates such as resin surface layers and unequal layer thickness, the flexural and extensional modulus of such laminated composites are different. By the way, since the bending and in-plane effects are together affect to the nonlinear behavior of a composite laminate, it should give more reliable results when using different flexural and extensional modulus in the analysis. In this study, the results of approximate analysis, ANSYS finite element analysis and experimental study are obtained and compared for a fully-clamped laminated composite plate subjected to a uniform pressure load. The material properties used in the analysis are determined tension and three-point bending tests.
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Vinogradov, Aleksandra M. "Buckling Characteristics of Regular and Irregular Asymmetric Laminated Composites." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-0883.

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Abstract The paper examines the effects of composite material properties on the nonlinear buckling response of irregular asymmetric composite structures through the analysis of asymmetric laminated beam-columns composed of an arbitrary number of different material layers. The nonlinear buckling behavior of the structures subjected to combined compression and bending is examined as a function of the number, orientation and stacking sequence of the layers that make up the laminate. The analysis demonstrates that, typically, buckling of asymmetric composites is initiated immediately at the load application, however, under certain conditions, the structures exhibit bifurcation. In such cases, the critical load can be optimized through tailoring the material properties of the laminates.
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Nandi, Soumitra, Zahed Siddique, and M. Cengiz Altan. "A Grammatical Approach for Customization of Laminated Composite Materials." In ASME 2010 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/detc2010-28589.

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The wide range of properties covered by the manufacturable fiber-matrix combinations of composite materials, along with their directional property characteristics, provides designers with material selection flexibility during designing composite material products. Meeting multiple property goals, however, complicates the design process as both the composite material selection and the component shape formation become complicated because the loading conditions and matrix calculations are needed to determine theoretical value of composite material properties. This paper presents a grammatical approach to simultaneously consider the shape and selection composite materials for a load-bearing component. Selection of composites involve determining the fiber and matrix, their volume fraction, and number of layers in different location of the component. A hip-replacement joint is designed using composite material to illustrate the approach.
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SNYDER, ALEXANDER D., ZACHARY J. PHILLIPS, and JASON F. PATRICK. "SELF-HEALING OF WOVEN COMPOSITE LAMINATES VIA IN SITU THERMAL REMENDING." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35785.

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Fiber-reinforced polymer composites are attractive structural materials due to their high specific strength/stiffness and excellent corrosion resistance. However, the lack of through-thickness reinforcement in laminated composites creates inherent susceptibility to fiber-matrix debonding, i.e., interlaminar delamination. This internal damage mode has proven difficult to detect and nearly impossible to repair via conventional methods, and therefore, remains a significant factor limiting the reliability of composite laminates in lightweight structures. Thus, novel approaches for mitigation (e.g., self-healing) of this incessant damage mode are of tremendous interest. Self-healing strategies involving sequestration of reactive liquids, i.e. microcapsule and microvascular systems, show promise for the extending service- life of laminated composites. However, limited heal cycles, long reaction times (hours/days), and variable stability of chemical agents under changing environmental conditions remain formidable research challenges. Intrinsic self- healing approaches that utilize reversible bonds in the host material circumvent many of these limitations and offer the potential for unlimited heal cycles. Here we detail the development of an intrinsic self-healing woven composite laminate based on thermally-induced dynamic bond re-association of 3D-printed polymer interlayers. In contrast to prior work, self-repair of the laminate occurs in situ and below the glass-transition temperature of the epoxy matrix, and maintains &gt;85% of the elastic modulus during healing. This new platform has been deployed in both glass and carbon-fiber composites, demonstrating application versatility. Remarkably, up to 20 rapid (minute-scale) self-healing cycles have been achieved with healing efficiencies hovering 100% of the interlayer toughened (4-5x) composite laminate. This latest self-healing advancement exhibits unprecedented potential for perpetual in-service repair along with material multi-functionality (e.g., deicing ability) to meet modern application demands.
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Naik, Tushar, and Zhong Hu. "Computer Simulation of Deep Drawing Process for a Laminated Composite Cup." In ASME 2007 International Mechanical Engineering Congress and Exposition. ASMEDC, 2007. http://dx.doi.org/10.1115/imece2007-41593.

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The anisotropic nature of laminated composites creates a unique opportunity and also a great challenge for tailoring their behavior during the forming processes according to the design requirements. In this work, design and simulation of a deep drawing process for fiber-reinforced laminated composites were conducted by using finite element analysis. The effects of the fiber orientation and stacking order on the deep drawing process were investigated based on the basic understanding of forming process of the isotropic aluminum alloy (Al-1100) and laminated composite material (Grilon RVZ-15H nylon/glass). A three dimensional finite element model incorporating layered structural laminates with various fiber orientations was developed. The load-stroke relationship, changes in thickness, and stress-strain distribution were investigated and compared for both aluminum alloy and laminated composites of [0]12, [0/90]6 and [0/90/45/135]3, which can be employed for detailed design and process optimization.
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Lund, Erik. "Buckling Topology Optimization of Laminated Multi-Material Composite Structures." In ASME 8th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2006. http://dx.doi.org/10.1115/esda2006-95753.

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The design problem of maximizing the buckling load factor of laminated multi-material composite shell structures is investigated using the so-called Discrete Material Optimization (DMO) approach. The design optimization method is based on ideas from multi-phase topology optimization where the material stiffness is computed as a weighted sum of candidate materials, thus making it possible to solve discrete optimization problems using gradient based techniques and mathematical programming. The potential of the DMO method to solve the combinatorial problem of proper choice of material and fiber orientation simultaneously is illustrated for a multilayered plate example and a simplified shell model of a spar cap of a wind turbine blade.
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Chuang, Shui-Nan. "Probabilistic Analysis for the Mechanical Properties of Cross-Ply Fiber-Reinforced Composite Laminate." In ASME 2006 International Mechanical Engineering Congress and Exposition. ASMEDC, 2006. http://dx.doi.org/10.1115/imece2006-13060.

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A probabilistic micromechanics model had been developed for the unidirectional fiber-reinforced composite material design screening. In which, we used the predicted mechanical properties of IM-7 carbon fiber from the existing IM-7/5250-4 composite material system together with the observed 977-3 matrix mechanical properties to predict the probability density functions for the mechanical properties of IM-7/977-3 unidirectional composite. To include the material design in the structural design process, we had extended the probabilistic analysis to predict the probability density functions for the off-axis mechanical properties. The angle-ply and cross-ply laminates have been used extensively in aerospace structural designs. It is logical to extend the probabilistic analysis to predict the probability density functions for the mechanical properties of the laminated composite. We had provided the probabilistic analysis for a symmetric regular angle-ply laminate of IM-7/5250-4 composite laminate. In this report, we will focus on the probabilistic analysis of symmetric and anti-symmetric regular cross-ply laminates of IM-7/5250-4 fiber-reinforced composite with odd-number plies parallel to and even-number plies perpendicular to the laminate principal axes. These probabilistic micromechanics models provide a design-screening tool to help material producers to eliminate the unnecessary time-consuming and costly material fabrications and to reduce the numbers of testing to a minimum but enough to verify the model prediction. They also provide a structural analysis tool to help the structural designer to manage the structural and material uncertainties during the structural design process. And consequently, it provides a means to accelerate the insertion of materials into AF productions.
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Christoph, Jake E., Colin M. Gregg, Jordan R. Raney, and David A. Jack. "Low Velocity Impact Testing of Laminated Carbon Fiber/Carbon Nanotube Composites." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-52984.

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Carbon fiber laminated thermoset composites have become the industry standard for applications dictating a high strength-to-weight ratio. However, the brittle nature of the carbon fiber composite structure limits its energy dissipation characteristics, often leading to catastrophic failure under low energy impact loadings. This research examines the potential effects of including vertically aligned multi-walled carbon nanotube forests within a layered laminate structure with the goal being to increase the energy dissipation of the structure with attention given to the increase in the aerial density as a result of including the insert. These nanotube forests are of interest due to their broader application in coupled scenarios requiring tenability of structural, thermal and electrical properties. These nanotube forests have unique energy dissipative effects due to their hierarchical architecture (see e.g., Dario et al. (2006), Zeng et al. (2010) and Raney et al. (2011)). We synthesize vertically aligned nanotubes (VACNTs) on a single crystalline silicon wafer. After separation with the wafer, the VACNTs are placed within a carbon fiber laminated structure prior to resin infusion using vacuum assisted resin transfer molding (VARTM). Drop tower tests similar to ASTM D7136 are performed on carbon fiber laminates, carbon fiber laminates with nanotube forests, and carbon fiber laminates with several alternative materials. Results show an improved damage tolerance of the laminate with each of the investigated inserts, with the CNT system showing an increase of 13% in mean peak force. These results show a similar improvement to the alternative inserts while maintaining the potential for their broader application as a multifunctional material.
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Erbil, Emre, and Ramazan Karakuzu. "Sleeve Design for Clinching Process on Laminated Composite Structures." In 6th International Students Science Congress. Izmir International Guest Student Association, 2022. http://dx.doi.org/10.52460/issc.2022.042.

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The lightweight composite materials bring out several opportunities besides some challenges. One of the most important challenges is to provide a strong and reliable joint for sensitive composite structures by preserving their specifications without any damage. Conventional fasteners are mostly designed for sheet metals, such as rivets, bolts, and clinched fixings are often incompatible with composites or require additional work. Moreover, interface materials may be required for additional functions like shock-absorbing, sealing, etc. For instance, a rivet can damage fiber or matrix during the installation process. Or a bolt may become embedded in the composite plate resulting in a fracture under its seating surface. Hence, these additional materials must keep corresponding materials safe in the assembly process, and after they must remain fully functional at the end of their service life. Therefore, the mechanical and damage properties of these additional materials must be known well for better and more reliable designs. In this context, the Cockroft &amp; Latham ductile damage parameter for AISI 304L material was obtained per the experimental data in [1].
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Reports on the topic "Laminated composite material"

1

Spera, D. A., J. B. Esgar, M. Gougeon, and M. D. Zuteck. Structural properties of laminated Douglas fir/epoxy composite material. Office of Scientific and Technical Information (OSTI), 1990. http://dx.doi.org/10.2172/6492500.

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Groves, S. E. Preliminary evaluation of the strength of pin-joints in laminated composite materials. Office of Scientific and Technical Information (OSTI), 1989. http://dx.doi.org/10.2172/7072288.

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Alexander, A., J. T. Tzeng, W. H. Drysdale, and B. P. Burns. Effective Three-Dimensional (3-D) Finite Element Material Stiffness Formulation for Modeling Laminated Composites. Defense Technical Information Center, 1996. http://dx.doi.org/10.21236/ada306454.

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