Relevant bibliographies by topics / Thick Composites

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Academic literature on the topic 'Thick Composites'

Author: Grafiati
Published: 4 June 2021
Last updated: 20 February 2023

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Journal articles on the topic "Thick Composites"

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Hadik, N., A. Outzourhit, A. Elmansouri, A. Abouelaoualim, A. Oueriagli, and E. L. Ameziane. "Dielectric Behavior of Ceramic (BST)/Epoxy Thick Films." Active and Passive Electronic Components 2009 (2009): 1–6. http://dx.doi.org/10.1155/2009/437130.

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Composite materials were made by mixing powders ofBa1−xSrxTiO3(x=0.2and 0.4) ceramics and epoxy resin with various volume fractions (vol%). Dielectric measurements of these composites were performed as a function of filler ratio in the range 100–360°K at 10 KHz. The dielectric constant of the composite increased with increasing volume fraction varies slightly with temperature. The 20 vol% of BST(0.4)-epoxy composite had the highest dielectric constant of 19.4 and dielectric loss tangent of 0.027. Among the dielectric mixing models presented, the model of Lichtenecker shows the best fit to the experimental data for both composites.
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Devikala, S., and P. Kamaraj. "Development of Polymethylmethacrylate Based Composite for Gas Sensing Application." E-Journal of Chemistry 8, s1 (2011): S165—S170. http://dx.doi.org/10.1155/2011/347163.

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Gas detection instruments are increasingly needed for industrial health and safety, environmental monitoring and process control. Conductive polymer composites have various industrial applications. The composite prepared by mixing carbon black with polymethylmethacrylate (PMMA) has very good gas sensing applications. The gas sensors based on carbon nanotube/polymer, ceramic and metal oxide composites such as epoxy, polyimide, PMMA / Barium titanate and tin oxide have also been developed. In the present work, a new composite has been prepared by using PMMA and ammonium dihydrogen phosphate (ADP). The PMMA/Ammonium dihydrogen phosphate (PMADP) composites PMADP 1 and PMADP 2 were characterized by using Powder XRD. The thick films of the composite on glass plates were prepared by using a spin coating unit at 9000 rpm. The application of the thick film as gas sensor has been studied between 0 and 2000 seconds. The results reveal that the thick film of PMADP composite can function as a very good gas sensor.
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Chang, Fu-Kuo, Jose Luis Perez, and Kuo-Yen Chang. "Analysis of Thick Laminated Composites." Journal of Composite Materials 24, no. 8 (August 1990): 801–22. http://dx.doi.org/10.1177/002199839002400802.

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Antonucci, Vincenza, Michele Giordano, Sabato Inserra Imparato, and Luigi Nicolais. "Autoclave manufacturing of thick composites." Polymer Composites 23, no. 5 (October 2002): 902–10. http://dx.doi.org/10.1002/pc.10487.

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Harris, CE, and DH Morris. "Fracture of thick laminated composites." Experimental Mechanics 26, no. 1 (March 1986): 34–41. http://dx.doi.org/10.1007/bf02319953.

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Hosur, M. V., U. K. Vaidya, A. Abraham, N. Jadhav, and S. Jeelani. "Static and High Strain Rate Compression Response of Thick Section Twill Weave S-2 Glass/Vinyl Ester Composites Manufactured by Affordable Liquid Molding Processes." Journal of Engineering Materials and Technology 121, no. 4 (October 1, 1999): 468–75. http://dx.doi.org/10.1115/1.2812403.

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Fiber reinforced composites, due to their higher specific strength and specific stiffness, are replacing many metallic structures. Of these, thick composite laminates are of high interest in various, millitary, transportation and marine applications for their use in ballistic and shock protection. One such application is in Composite Armored Vehicle (CAV) integral armor comprising of thick section composite that serves as the primary load-bearing component. The current solution of the structural backing laminate utilizes an S2-glass/epoxy system processed using automated fiber placement method. While proven structurally suitable, this method is time consuming as well as expensive. This paper presents several alternative cost-effective manufacturing solutions for fabricating composite laminates of 20 mm (0.8 in.) nominal thickness (made of 45 layer, 2 × 2 twill weave S2-glass with 933 sizing/vinyl ester C-50 resin), consisted with them CAV application in focus. They include Vacuum Assisted Resin Transfer Molding (VARTM) and Vacuum Assisted Resin Infusion Modeling (VARIM) and their variations. The effectiveness of different affordable processing approaches adopted in fabricating the structural laminate is compared in terms of static and dynamic compression response of the laminations. Static studies have been conducted on thick composites using specimen based on Army Material Technology Laboratory’s (AMTL) recommendation for thick section composites, while dynamic response is studied on cubic specimen samples using a Split Hopkinson Pressure Bar (SHPB).
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Huang, Runzhou, Xian Zhang, Zhilin Chen, Minli Wan, and Qinglin Wu. "Thermal Stability and Flame Resistance of the Coextruded Wood-Plastic Composites Containing Talc-Filled Plastic Shells." International Journal of Polymer Science 2020 (July 1, 2020): 1–9. http://dx.doi.org/10.1155/2020/1435249.

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Talc is a popular filler for the fabrication of plastic composites. The presence of talc helps improve mechanical, thermal, and flame resistance properties of the composite. In this work, we report the influence of a talc-filled plastic shell layer on thermal stability and fire flammability of the core-shell structured wood high-density polyethylene (HDPE) composites manufactured through coextrusion. The result showed that morphological analysis of the char layer after combustion confirmed the formation of a continuous surface char layer with talc addition in the composites, helping block fire penetration and enhance overall fire resistance of the composites. The shell thickness averaged at 1.0±0.2 mm, which represents a fair thick shell over a 10 mm thick WPC core layer. The surface of regular wood-filled HDPE showed large cracks, allowing more rapid fire penetration and reducing its fire resistance. At 800°C, average residual weight for all composite was 21.5±13.8%, most of which was attributed to the inorganic nonvolatile talc components. With the increase of talc level, THR values of coextruded WPC decreased from 302.47 MJ/m2 (5 wt% of talc) to 262.96 kW/m2 (50 wt% of talc). When talc content in the shell layer was less than 25 wt%, the flame resistance properties were slightly enhanced compared with the composites containing unmodified HDPE shells. When talc content in the shell exceeded 25 wt%, the composite’s total heat release and its rate substantially decreased.
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Alkan, Ümit, Yaşar Karabul, Ayşe Evrim Bulgurcuoğlu, Mehmet Kılıç, Zeynep Güven Özdemir, and Orhan İçelli. "Polypropylene/basalt thick film composites: structural, mechanical and dielectric properties." e-Polymers 17, no. 5 (August 28, 2017): 417–25. http://dx.doi.org/10.1515/epoly-2017-0035.

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AbstractIn this work, polypropylene/volcanic basalt rock (PP/VBR) thick film composites with different VBR powder mass ratio varying from 0.5 wt.% to 20.0 wt.% were prepared by using the hot press technique. The effects of VBR powder doping on mechanical, structural and dielectric properties of PP were investigated by stress-strain measurements, Fourier transform infrared analysis, thermal gravimetric analysis, scanning electron microscopy and dielectric spectroscopy methods. The highest tensile strength, percentage strain and energy at break were achieved for 0.5 wt.% VBR powder doped PP composite. According to the stress-percentage strain curves of the samples, it was observed that 0.5 wt.% VBR powder doping increases the mechanical performance of PP polymer. In addition, regardless of the doping concentration level of basalt powder, the real part of complex dielectric function (ε′) of all PP composites display approximately frequency independent behavior between 100 Hz and 1 MHz. On the other hand, 0.5 wt.% VBR powder doped PP composite has also the lowest dielectric constant at the vicinity of 2.7 between 100 Hz and 1 MHz. The composite also has considerably low dielectric loss which has a crucial importance for technological applications. For these reasons, PP/0.5 wt.% VBR composite with the highest tensile strength can be considered as a suitable candidate for microelectronic devices. Furthermore, the alternative current conductivity mechanism was determined as nearly constant loss due to approximately constant dielectric loss between 10 Hz and 1 MHz.
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Hojjati, M., and S. V. Hoa. "Curing simulation of thick thermosetting composites." Composites Manufacturing 5, no. 3 (September 1994): 159–69. http://dx.doi.org/10.1016/0956-7143(94)90025-6.

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Guo, Zhan-Sheng, Shanyi Du, and Boming Zhang. "Temperature distribution of thick thermoset composites." Modelling and Simulation in Materials Science and Engineering 12, no. 3 (February 25, 2004): 443–52. http://dx.doi.org/10.1088/0965-0393/12/3/006.

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Dissertations / Theses on the topic "Thick Composites"

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Erdem, Melek Esra. "Failure Analysis Of Thick Composites." Master's thesis, METU, 2013. http://etd.lib.metu.edu.tr/upload/12615605/index.pdf.

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A three-dimensional finite element model is constructed to predict the failure of a hybrid and thick laminate containing bolted joints. The results of the simulation are compared with test results. The simulation comprises two main challenging steps. Firstly, for a realistic model, a 3D model is established with geometric nonlinearities and contact is takeninto account. The laminated composite model is constructed by 3D layered elements. The effect of different number of elements through the thickness is investigated. The failure prediction is the second part of the simulation study. Solutions with and without progressive failure approach are obtained and the effect of progressive failure analysis for an optimum simulation of failure is discussed. The most appropriate failure criteria to predict the failure of a thick composite structure is also investigated by considering various failure criteria. By comparing the test results with the ones found from the finite element analyses, the validity of the developed model and the chosen failure criteria are discussed.
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Carrasco-Munoz, Y. Guerra Jacinto. "Design exploration methodology for ultra thick laminated composites." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/8289.

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Existing test and analytical methods (theoretical and numerical) are normally restricted to thin laminate components, which cannot accurately represent the 3D stress state behaviour of the so called Ultra Thick Laminates (UTL) structures. Thus, it is necessary to expand the scope of application of the current numerical methods to accurately predict the out-of-plane delamination failure associated with these types of structures (mainly due to the transverse shear stresses and interlaminar stresses). The overall objective of this work is to address the following research objectives: • To assess the functionality, advantages and limitations of different solid element formulations, including layered solid elements that are available in commercial Finite Element codes, applied to the mechanical response prediction of UTL composite components (thicknesses up to 30 mm are considered). • To perform a design exploration and optimisation of constant thickness UTL composite component in terms of the orientation of a varying and repeatable stacking sequence of an eight ply Non-Crimped Fabric, in order to assess the design implications on performance. In order to achieve the above stated objectives a standard, flexible and expandable FE based design exploration methodology (at a ply level) for UTL composite components is proposed, which considers a commercial FE tool (ANSYS), and a data management system and optimisation tool (ISIGHT), through the use of layered solid elements (SOLID186 and SOLID191, 20-node layered solid elements). Application of manufacturing design rules (for reducing the number of feasible stacking sequences to be evaluated) is also considered, in order to reduce the computational cost of such a study, as well as to present a practical solution from the manufacturing point of view. Initially, in-plane and out-of-plane capabilities of various layered element formulations and modelling strategies where evaluated for thin and thick laminate applications against known analytic solutions (CLT, etc), in order to understand the key parameters and the accuracy limitations of each formulation. This led to practical recommendations for pre and post processing of thick laminate FE models, such as for the number of layered solid elements required as a function of the thickness of the UTL component to effectively predict the magnitude and variation in transverse shear stress across the thickness. The application of this research was demonstrated on the design exploration and performance optimisation of a UTL composite specimen (with constant thickness) under a 3-point bending test (linear static analysis), for which experimental results were available. The individual ply orientations are the design variables considered, and the performance was assessed through the vertical displacement of the component and the maximum transverse shear stress value. This exploration of the design space did identify other possible configurations that may have a better performance than the baseline (Biax), considering only the maximum transverse shear stress values as directly responsible for the delamination failure. However, these improved designs may present a higher number of plies failed or a higher failure index (Tsai-Wu failure criteria). Further experimental studies are required to further explore the design space, but this work represents the starting point and possible approaches for development of robustness and weight optimisation of UTL composites are proposed.
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Small, Peter D. (Peter David). "Ultrasonic wave propagation in thick, layered composites containing degraded interfaces." Thesis, Massachusetts Institute of Technology, 2005. http://hdl.handle.net/1721.1/33585.

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Thesis (Nav. E.)--Massachusetts Institute of Technology, Dept. of Ocean Engineering; and, (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2005.
Includes bibliographical references.
The ultrasonic wave propagation of thick, layered composites containing degraded bonds is investigated. A theoretical one-dimensional model of three attenuative viscoelastic layers containing two imperfect interfaces is introduced. Elastic material properties and measured 'values of ultrasonic phase velocity and attenuation are used to represent E-glass and vinyl ester resin fiber-reinforced plastic (FRP) laminate, syntactic foam, and resin putty materials in the model. The ultrasonic phase velocity in all three materials is shown to be essentially constant in the range of 1.0 to 5.0 megahertz (MHz). The attenuation in all three materials is constant or slightly increasing in the range 1.0 to 3.0 MHz. Numerical simulation of the model via the mass- spring-dashpot lattice model reveals the importance of the input signal shape, wave speed, and layer thickness on obtaining non-overlapping, distinct return signals in pulse-echo ultrasonic nondestructive evaluation. The effect of the interface contact quality on the reflection and transmission coefficients of degraded interfaces is observed in both the simulated and theoretical results.
by Peter D. Small.
S.M.
Nav.E.
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Breen, Charles Edward Pitt. "Impact damage in thick carbon fibre reinforced plastic laminated composites." Thesis, University of Bristol, 2007. http://hdl.handle.net/1983/426d2091-43e8-4d4a-ae7a-b0ded8dea0e2.

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Saboktakin, Rizi Abbasali. "Integrity assessment of preforms and thick textile reinforced composites for aerospace applications." Mémoire, École de technologie supérieure, 2013. http://espace.etsmtl.ca/1267/1/SABOKTAKIN_RIZI_Abbasali.pdf.

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Les composites à renforts textiles 3D, contenant des fibres dans le plan et dans la direction de l'épaisseur, offrent certains avantages par rapport aux composites à renforts textiles 2D. Ces avantages comprennent une grande résistance à la délamination et une meilleure tolérance à l'endommagement. La plupart des textiles 3D ont été développés pour des pièces destinées à l'industrie aérospatiale telles que des panneaux d'ailes, des trains d'atterrissage, des tuyères de fusée et la capsule Orion. Cette thèse vise à évaluer l'intégrité structurelle des textiles composites en combinant des techniques d'inspection destructives et non destructives. Dans la première partie de la thèse, des techniques non destructives, y compris les rayons-X (CT) et des techniques basées sur les ultrasons (UT), ont été développées pour détecter les défauts importants comme la rupture des fibres et le désalignement des tissus. La deuxième partie porte sur l'étude de l'influence des défauts de fabrication qui se produisent dans les processus d’ touffetage sur les performances mécaniques. Des résultats expérimentaux ont montré que tomographie rayons-X facilite la détection et la caractérisation de ces deux défauts de fabrication, ainsi que de l'architecture des tissus. En outre, la modélisation méso-échelle d'un composite tissé en 2D a été réalisée avec succès pour l'analyse de l'influence du défaut de rupture des fibres et de l'architecture des fibres de propagation de l'onde. Les résultats expérimentaux montrent que le touffetage des préforme limite ou élimine le mouvement de leurs fils. En plus, la touffetage par des fils de haute résistance à la traction peut améliorer celle de leurs préforme 3D. La touffe d’un préforme fait augmenter la force de compactage des fibres. À cet effet, cette méthode est nécessaire pour augmenter le volume des fibres de plus de 50 % en comparaison d'un préforme non touffeté. La résistance à la déformation d'une préforme est influencée par l’opération de touffetage. En effet, une préforme touffetée est plus résistance à la déformation qu’une préforme non touffetée. La variation de la géométrie de la préforme a été mesurée par balayage laser. En outre, la capacité CT a été étudiée en tant que moyen pour reconnaître les formes et les emplacements des vides dans les matériaux composites. La résistance à la traction des composites avec un touffetage transversale a eu moins de réduction de que celle avec touffetage longitudinal. Les tests de fatigue à haute vitesse de déformation montrent que les composites touffetés ont une durée de vie inférieure à celle des composite non touffetés. L’opération de touffetage permet d'améliorer les propriétés mécaniques des panneaux sandwichs à noyau en nid d'abeilles sollicités en compression locale et en flexion trois points. Les dommages sont souvent initiés dans les régions riches en résine qui entourent le renfort de touffetage. L'acceptation primaire de l’utilisation des composites touffetés 3D dans les structures aérospatiales est très dépendantes de l'exactitude et de la fiabilité des données expérimentales pour identifier le degré auquel les renforts améliorent ou dégradent les propriétés mécaniques. Dans cette thèse, la corrélation entre les préformes touffues, les propriétés des composites et leurs modifications dues au touffetage sont traités pour une configuration spécifique. Les données expérimentales sont présentées à la fois sur un taux faible et à haut débit statique et des forces de fatigue à différents niveaux de contrainte. L'examen microstructural est effectué en utilisant la microscopie à haute résolution et les techniques de CT. Les résultats de cette thèse contribuent à l'enquête sur la tolérance d'intégrité et de dommage dans les matériaux composites tuftés 3D en vue d'une certification pour l'utilisation dans les futurs avions de transport. Cependant, la certification des composites tuftés pour les applications aérospatiales est toujours problématique en raison de l'absence de techniques d'évaluation non destructive fiables pour leur inspection et les facteurs de fabrication peuvent influencer considérablement leur performance, il s'agit d'un problème important auquel on doit s’attaquer dans le domaine de composite pour l’aérospatial.
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Gorris, Thibault. "Application de la méthode Thick Level Set à l'étude des composites stratifiés." Ecole Centrale de Nantes, 2012. http://www.theses.fr/2012ECDN0050.

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Cette étude considère l’endommagement des composites stratifiés par une méthode proposant la propagation d’un front de levelset épais (TLS : Thick LevelSet). Un modèle élements finis est généralisé pour étudier l’ensemble des dommages dans un composite : fissuration transverse dans la couche 90, délaminage en pointe de fissure et délaminage entre les deux couches. La génération de nouvelles fissures est contrôlée à l’aide du taux de restitution d’énergie locale Y. L’étude porte sur l’espacement critique entre plusieurs fissures au sein de stratifié verre/époxy, carbone/époxy. Le travail de thèse étudié dans ce manuscrit propose donc d’appliquer et d’améliorer une nouvelle méthode de modélisation de l’endommagement des composites stratifiés avec différents empilements. Les travaux portent plus particulièrement dans des empilements 0 et 90 du fait de la limitation au cas 2D. L’objectif est ici de déterminer les outils nécessaires à la description discrète de la microfissuration transverse et du délaminage, puis d’en identifier les différents paramètres ainsi que leur influence pour enfin valider le travail par la comparaison avec des résultats expérimentaux obtenus dans la littérature. L’étude aborde également la fissuration dans les plis de peau
This work presents a study of damage in cross-ply laminates by a new thick levelset (TLS) approach. A generalised finite element model is developped to study the various kinds of damage in a composite : transverse cracking in the 90 layer, delamination at crack-tip and at the interface between plies. Generation of new cracks is controlled by the local energy release rate Y. With this model, we can predict critical crack spacing in glass/epoxy or carbon/epoxy laminates. Various stacking sequences are considered, but we focus on cross-ply (0 and 90 orientation) laminates models. We determine the var-ious modeling elements necessary to a discrete description of transverse micro-cracking and delamination, identify necessary parameters and check their influence, finally validat-ing our work by comparaison with results from literature
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Bin, Ahmad Sobri Sharizal. "Mechanical and laser drilling of thick carbon fibre reinforced polymer composites (CFRP)." Thesis, University of Manchester, 2018. https://www.research.manchester.ac.uk/portal/en/theses/mechanical-and-laser-drilling-of-thick-carbon-fibre-reinforced-polymer-composites-cfrp(e5c5182e-a8b2-49c9-bceb-bd7ba9342eb1).html.

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Carbon fibre reinforced polymer, or CFRP composite materials, play an increasingly important role in modern manufacturing. They are widely used in aerospace, and their use is currently spreading to other industries where high strength-to-weight ratios are required. However, machining of composites is still a challenging task and often hampered by poor quality. Despite the extensive research that was conducted on the machining of composite materials over the last few years, mechanical drilling still suffers from delamination, fibre pull-out and poor surface finish, whereas laser cutting produces microstructured defects and a taper problem. This thesis reports on the drilling of CFRP composites by demonstrating the possibility of drilling small diameter holes (i.e. 8mm) into 25.4mm thick carbon fibre reinforced polymer composites (CFRPs) using mechanical drilling and laser drilling as stand-alone processes and as a sequential combination. The research involved four main phases of experimental testing. The first part of Phase 1 involved!preliminary experiments of drilling thick CFRP to identify the most suitable drilling strategy. Three mechanical drilling strategies conducted in the same parameter by using a 2-flute uncoated WC twist drill that was assessed with respect to feasibility of drilling thick CFRP. The results showed that the single-step strategy was the most feasible strategy to drill thick CFRP compared to 2- and 4-peck drilling strategies. The second part of Phase 1 concerned the influence of speed-feed combinations on hole quality by utilising three twist drills with different materials and geometries in both an uncoated and coated condition. The results indicated that a significant increase in peel-up delamination was found with increasing feed rate. In contrast, using a constant feed rate but increasing the spindle speed seemed to reduce peel-up delamination. Furthermore, the hole entry for 2-flute uncoated WC drill bits was an uncommon study finding because most of the previous researchers experienced more damages at the hole exit and their investigation focused on the hole exit only. Currently, implementation of laser technology in cutting and drilling composites is becoming popular as an alternative solution. Various experiments were conducted with the goal of identifying the effects of machining parameters on key output measures (i.e. heat affected zone (HAZ), hole depth and other damages) in drilling of 25.4 mm thick CFRP by using a fibre laser. Phase 2 involved a number of machining parameters selected to identify the potential of a fibre laser in drilling thick CFRP composites (i.e. laser power, scanning speed, focal point plane position (FPP), assisted-gas type and gas pressure). The results proved that a fibre laser could penetrate thick CFRP to a 22mm depth only. Moreover, the spiral trepanning strategy was able to penetrate 80% out of the total thickness of the CFRP in continuous wave (CW) mode, whereas the modulated laser beam (i.e. laser pulse mode) can penetrate 67% only. This result was a major recorded breakthrough because previous research attempts cut up to 5mm only. Laser power proved to be the most influential factor for hole depth in laser drilling of thick CFRP when the spiral trepanning strategy was applied. Machining trials were conducted in Phase 3 by using a 16kW fibre laser in modulated pulsed laser mode. In this phase, laser power of more than 1kW was attempted to cut the whole thickness of CFRP composites in CW mode, but it was unsuccessful. However, a new parameter was discovered (i.e. the cooling time between passes in modulated pulsed mode), which proved a considerable reduction of HAZ when the higher cooling time was imposed. Finally, phase 4 involved the experiments of sequential laser-mechanical drilling. A 1kW fibre laser was selected as a pre-drilling or initial step and followed by mechanical drilling as the final step. The sequential drilling method successfully reduced thrust force and torque for mechanical drilling by an overall average of 61%, resulting in high productivity and decreasing the thermal and mechanical stresses in the cutting tool and, in turn, promoting higher tool life. The highest delamination factor (Fda) ratio was experienced by the sequential laser 8mm – mechanical 8mm for both tools (i.e. 2- and 3-flute uncoated tungsten carbide) and laser pre-drilling strategies (i.e. single- and double-side). Thus, a novel laser-mechanical sequential drilling technique was developed, evaluated and tested in the drilling of thick CFRP composites; this is the first time ever in drilling thick CFRP (i.e. 25.4mm).
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Dogra, Jasween. "The development of a new compression test specimen design for thick laminate composites." Thesis, Imperial College London, 2011. http://hdl.handle.net/10044/1/7121.

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A new specimen design for determining the compression strength of thick unidirectional laminate composites has been developed using finite element simulations and validated by experimental testing. The computational models included parts of the testing fixture. The materials used for experiments were carbon fibre/epoxy T300/914 from Hexcel Composites and IM7/8552. An understanding has been developed to explain why, using the standard, parallel sided design, for testing specimens in compression and using the ICSTM fixture, specimens using a laminate thicker than 2 mm do not fail in an acceptable way. Initially, simulation and experimental parametric studies were carried out to investigate the effects of loading and design conditions on the fixture and specimen in order to change the stress distribution in the 2 mm thick, parallel sided, 10 mm x 10 mm gauge section specimen. In addition, in order to optimise the specimen itself, different adhesives for bonding end tabs to the laminate were investigated, as were the end tab design and material used in their manufacture. Subsequent simulations showed that the use of an extended and waisted gauge length of either circular or s-shaped profile both caused thick laminate specimens to fail close to the centre of the gauge length. The predicted strength being similar to that measured for a 2 mm thick, parallel sided specimen using the optimised design. Experimental compression strength data from thick laminate specimens with the circular and s-shaped profiles machined into the gauge section validated the finite element results; the strengths achieved being almost identical to those for the 2mm thick laminates. Results from the analysis of the standard design and some preliminary work on the waisted design were presented at a conference [52]. Results for further work on the waisted design and experimental details have been reported in [51] and [75].
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Vel, Senthil S. "Analytical Solutions for the Deformation of Anisotropic Elastic and Piezothermoelastic Laminated Plates." Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/30003.

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The Eshelby-Stroh formalism is used to analyze the generalized plane strain quasistatic deformations of an anisotropic, linear elastic laminated plate.The formulation admits any set of boundary conditions on the edges and long faces of the laminate. Each lamina may be generally anisotropic with as many as 21 independent elastic constants. The three dimensional governing differential equations are satisfied at every point of the body.The boundary conditions and interface continuity conditions are satisfied in the sense of a Fourier series. Results are presented for three sample problems to illustrate the versatility of the method. The solution methodology is generalized to study the deformation of finite rectangular plates subjected to arbitrary boundary conditions. The effect of truncation of the series on the accuracy of the solution is carefully examined. Results are presented for thick plates with two opposite edges simply supported and the other two subjected to eight different boundary conditions. The results are compared with three different plate theories.The solution exhibits boundary layers at the edges except when they are simply supported. Results are presented in tabular form for different sets of edge boundary conditions to facilitate comparisons with predictions from various plate theories and finite element formulations. The Eshelby-Stroh formalism is also extended to study the generalized plane deformations of piezothermoelastic laminated plates. The method is capable of analyzing laminated plates with embedded piezothermoelastic patches. Results are presented for a thermoelastic problem and laminated elastic plates with piezothermoelastic lamina attached to its top surface. When a PZT actuator patch is attached to an elastic cantilever substrate, it is observed that the transverse shear stress and transverse normal stress are very large at the corners of the PZT-substrate interface. This dissertation is organized in the form of three self-contained chapters each of which will be submitted for possible publication in a journal.
Ph. D.
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Nunes, Stephanie Gonçalves. "Processamento por infusão a vácuo de compósitos espessos aramida/epóxi e análise do desempenho sob impacto." reponame:Biblioteca Digital de Teses e Dissertações da UFRGS, 2018. http://hdl.handle.net/10183/180659.

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Em aplicações que requerem solicitações de impacto, compósitos de matriz polimérica reforçados com fibra de aramida se destacam, principalmente em relação aos metais, devido a propriedades como alta resistência e rigidez específicas, que dão origem a sistemas mais leves e de alta performance. Quando voltados para aplicações de impacto, principalmente a alta velocidade, tais compósitos são, em sua maioria, moldados por compressão ou autoclave, a partir de pré-impregnados. No entanto, tais combinações de processamentos e matéria-prima acarretam em estruturas de elevado custo, tornando a infusão a vácuo uma opção atrativa, além de permitir a obtenção de peças grandes e complexas, dimensionalmente acuradas e partes integradas. Porém, a obtenção de um compósito espesso reforçado por fibra de aramida com elevado desempenho ao impacto por tal método de fabricação ainda é um desafio. Neste contexto, este trabalho aborda o efeito da espessura no processamento por infusão a vácuo de compósitos aramida/epóxi e seu desempenho em aplicações que requerem solicitações de impacto (baixa e alta velocidade) Para isso, foram produzidos compósitos com 5, 8, 13, 18, 23 e 28 camadas de aramida e caracterizados por ultrassom C-scan, microscopia ótica, densidade, teor de constituintes, testes mecânicos (flexão, short beam e indentação quase-estática) e cargas de impacto de baixa e alta velocidade (drop-weight e balístico). Todos os compósitos apresentaram boa homogeneidade na distribuição da matriz ao longo do reforço, com um teor de fibra de ≈60%, e valores de resistência short beam elevados (17,3 - 23,6 MPa). A performance sob impacto (baixa e alta velocidade) foi comparável à de compósitos fabricados por compressão ou autoclave, tendo os compósitos a partir de 18 camadas resistido ao projétil 9 mm Luger FMJ e o de 28 camadas resistido ao projétil .357 Magnum FMJ, podendo ser classificados como nível FB2 e FB3, respectivamente, de acordo com a norma europeia EN 1522. Portanto, o processamento de infusão a vácuo mostrou ser uma alternativa adequada para produzir compósitos espessos de aramida/epóxi (até 12 mm), substituindo rotas de processamento mais caras.
In applications that require impact solicitations, polymer matrix composites reinforced with aramid fiber stand out, especially in relation to metals, due to properties such as high specific strength and stiffness, which give rise to lighter and high-performance systems. When used for impact applications, especially at high speed, such composites are mostly molded by compression or autoclaved, from prepregs. However, such combinations of processing and raw material lead to high cost structures, making vacuum infusion an attractive option, as well as allowing the production of large, complex, dimensionally accurate and integrated parts. Nonetheless, obtaining a thick composite reinforced by aramid fiber with high impact performance by such manufacturing method is still a challenge. In this context, this work addresses the effect of the thickness in the vacuum infusion processing of aramid/epoxy composites and its performance in applications that require impact solicitations (low and high speed) For this, composites with 5, 8, 13, 18, 23 and 28 layers of aramid were produced and characterized by ultrasonic C-scan, optical microscopy, density, constituent content, mechanical tests (flexion, short beam and quasi-static indentation) and low- and high-speed impact loads (drop-weight and ballistic). All composites presented good homogeneity in the matrix scattering along the reinforcement, with a fiber content of ≈ 60%, and high short beam resistance values (17.3 - 23.6 MPa). The performance under impact (low and high speed) was comparable to that of composites processed by compression or autoclave, the composites with 18 layers resisted to the 9 mm Luger FMJ projectile and the one with 28 layers resisted to the .357 Magnum FMJ projectile, being classified as level FB2 and FB3, respectively, according to the European standard EN 1522. In summary, vacuum infusion processing proved to be a suitable alternative to produce thick aramid/epoxy composites (up to 12 mm), replacing more expensive processing routes.
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Books on the topic "Thick Composites"

1

H, Williams James. Modes of vibration on square fiberglass epoxy composite thick plate. [Washington, D.C.?]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Y, Rajapakse, American Society of Mechanical Engineers. Applied Mechanics Division., and Joint Mechanics Meeting of ASME, ASCE, SES (1st : 1993 : Charlottesville, Va.), eds. Mechanics of thick composites: Presented at the 1st Joint Mechanics Meeting of ASME, ASCE, SES, MEET'N '93, Charlottesville, Virginia, June 6-9, 1993. New York: American Society of Mechanical Engineers, 1993.

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Peretz, Friedmann, Kosmatka J. B, American Society of Mechanical Engineers. Aerospace Division., and American Society of Mechanical Engineers. Winter Meeting, eds. Recent advances in the structural dynamic modeling of composite rotor blades and thick composites: Presented at the Winter Annual Meeting of the American Society of Mechanical Engineers, Anaheim, California, November 8-13, 1992. New York: ASME, 1992.

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Lee, Sung W., ed. Advances in Thick Section Composite and Sandwich Structures. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-31065-3.

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Arnold, S. M. A thermoelastic transversely isotropic thick walled cylinder/disk application: An analytical solution and study. Cleveland, Ohio: Lewis Research Center, 1989.

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Damage Tolerance of Thick-Section Composites Subjected to Ballistic Impact. Storming Media, 2001.

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C, Smith, Lumban-Tobing F, and Langley Research Center, eds. Analysis of thick sandwich shells with embedded ceramic tiles. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

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United States. National Aeronautics and Space Administration, ed. Ultrasonic evaluation of mechanical properties of thick, multilayered, filament wound composites. [Washington, D.C: National Aeronautics and Space Administration, 1985.

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C, Marques Elizabeth R., Lee Samson S, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Massachusetts Institute of Technology, and Lewis Research Center, eds. Modes of vibration on square fiberglass epoxy composite thick plate. [Washington, D.C.?]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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T, Nettles A., and George C. Marshall Space Flight Center., eds. A novel method of testing the shear strength of thick honeycomb composites. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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Book chapters on the topic "Thick Composites"

1

Nassar, Sayed A., Jianghui Mao, Xianjie Yang, and Douglas Templeton. "Cylindrical Bending of Bonded Layered Thick Composites." In Composite Materials and Joining Technologies for Composites, Volume 7, 59–69. New York, NY: Springer New York, 2013. http://dx.doi.org/10.1007/978-1-4614-4553-1_7.

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Teller, Cecil M., and Christopher M. Fortunko. "NDE Requirements for Thick Marine Composites." In Review of Progress in Quantitative Nondestructive Evaluation, 1599–606. Boston, MA: Springer US, 1991. http://dx.doi.org/10.1007/978-1-4615-3742-7_60.

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Lu, Yichi, and Jan D. Achenbach. "Localization of Ultrasound in Thick Composites." In Review of Progress in Quantitative Nondestructive Evaluation, 1379–86. Boston, MA: Springer US, 1990. http://dx.doi.org/10.1007/978-1-4684-5772-8_177.

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Papadakis, E. P., T. Patton, Y. M. Tsai, and D. O. Thompson. "The Elastic Moduli of Thick Composites." In Review of Progress in Quantitative Nondestructive Evaluation, 1387–94. Boston, MA: Springer US, 1990. http://dx.doi.org/10.1007/978-1-4684-5772-8_178.

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Papadakis, Emmanuel P., Thadd Patton, Yu-Min Tsai, R. Bruce Thompson, and Donald O. Thompson. "Some Elastic Moduli of Three Thick Composites." In Review of Progress in Quantitative Nondestructive Evaluation, 1615–22. Boston, MA: Springer US, 1991. http://dx.doi.org/10.1007/978-1-4615-3742-7_62.

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Hsu, David K., and Ali Minachi. "Defect Characterization in Thick Composites by Ultrasound." In Review of Progress in Quantitative Nondestructive Evaluation, 1481–88. Boston, MA: Springer US, 1990. http://dx.doi.org/10.1007/978-1-4684-5772-8_190.

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Gajbhiye, Param D., Vishisht Bhaiya, and Yuwaraj M. Ghugal. "Buckling Analysis of Thick Plates Using 5th Order Shear Deformation Theory." In Composites Science and Technology, 453–83. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2424-8_19.

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Sachse, Wolfgang. "Towards a Quantitative Ultrasonic NDE of Thick Composites." In Review of Progress in Quantitative Nondestructive Evaluation, 1575–82. Boston, MA: Springer US, 1991. http://dx.doi.org/10.1007/978-1-4615-3742-7_57.

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Daniel, I. M., S. C. Wooh, and I. Komsky. "Characterization of Porosity in Thick Graphite/Epoxy Composites." In Review of Progress in Quantitative Nondestructive Evaluation, 1607–14. Boston, MA: Springer US, 1991. http://dx.doi.org/10.1007/978-1-4615-3742-7_61.

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Minachi, Ali, and David K. Hsu. "Model-Based Iterative Flaw Sizing for Thick Composites." In Review of Progress in Quantitative Nondestructive Evaluation, 1647–54. Boston, MA: Springer US, 1991. http://dx.doi.org/10.1007/978-1-4615-3742-7_66.

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Conference papers on the topic "Thick Composites"

1

Hamada, Hiroyuki, Asami Nakai, Kazuya Eto, and Kenichi Sugimoto. "Mechanical Properties of Matrix Hybrid Thick-Composites." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-62305.

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For the purpose of more safety boats, the large thickness of outer plates is required to increase flexural stiffness, strength and impact properties. Some problems in mechanical properties are generated by increasing in thickness because the effect of interlaminar shearing of Thick-composites on whole mechanical properties is greater than that of thin-composites. We have investigated the matrix hybrid composite with two kinds of unsaturated polyester, one was hard type resin with low toughness and the other was flexible type resin with low modulus and high toughness. In this study, matrix hybrid composite was focused and applied to Thick-composites. First, the flexural properties were investigated and the micro fracture progress was precisely observed with in-situ observation using replica method. Then, impact properties of the Thick-composites were examined and the availability of matrix hybrid composite was investigated. It was concluded that the matrix hybrid composite achieved high performance in both static and impact load.
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Kennedy, Graeme, and Jorn Hansen. "Composite Processing Optimization for Residual Stress Reduction in Thick Composites." In 11th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-7044.

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MIYASE, AKIRA, KING HIM LO, and SU SU WANG. "In-Situ Interface Bond Strength Determination in Thick Adhesive Bonded Box Beam." In American Society for Composites 2017. Lancaster, PA: DEStech Publications, Inc., 2017. http://dx.doi.org/10.12783/asc2017/15177.

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Haque, A., J. Johnson, U. K. Vaidya, and S. Jeelani. "Fatigue Damage of Glass/Vinyl Ester Thick Composites." In ASME 1997 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/imece1997-1051.

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Abstract The focus of this study is to investigate the compression-compression fatigue damage of S2-glass/vinyl ester woven composites manufactured through Vacuum Assisted Resin Transfer Molding (VARTM). The compressive behavior and the relevant failure modes of composites are investigated prior to applying the cyclic load. The panels of thicknesses (0.15 in./3.81mm – 0.45 in./11.43 mm) are considered to quantify the process related defect such as void contents and fiber waviness in the thick composite laminates. Void content of each panel is determined through a bum-off test method using a Thermal Gravitational Analyzer (TGA). An optical microscope attached with a grid pattern transparent film is used to measure the waviness parameters of the laminate. The ultrasonic C-scan, A-scan and microscopic examinations are used to identify the manufacturing flaws related to VARTM. The effects of such defects on static compression and compression-compression cyclic behavior of thick composites are investigated. The failure strength, failure strain, modulus and number of cycles to failure at different stress levels for various laminate thicknesses are determined. Weibull plots are generated using both static compression strength and fatigue life cycles. Although the range of the thickness of the laminate was in the ratio of one to three, the variation in compressive strength data was rather nominal. The fatigue performance is observed to improve with the increase in thickness. In-situ monitoring of progressive damage under compressive and cyclic loading is conducted using acoustic emission (AE) method. AE parameters in the form of amplitude, energy and time plots are generated. The compressive and fatigue failure modes are identified by optical and scanning electron microscopic examinations. These failure modes are correlated with acoustic emission Non Destructive Evaluation (NDE) parameters.
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ALMS, JUSTIN B., and RONALD J. BROWN. "Aspects of Prepreg Layer Friction on Defect Formation on Thick-Walled Composite Manufacturing." In American Society for Composites 2017. Lancaster, PA: DEStech Publications, Inc., 2017. http://dx.doi.org/10.12783/asc2017/15361.

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RAO, PRABHAKAR M., MARK R. GURVICH, NALINDA W. WAAS, UPUL R. PALLIYAGURU, and WARUNA SENEVIRATNE. "Progressive Damage Mechanisms in Thick 3D Composite Structures Under Static and Fatigue Loading." In American Society for Composites 2020. Lancaster, PA: DEStech Publications, Inc., 2020. http://dx.doi.org/10.12783/asc35/34970.

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Littles, Jr., Jerrol W. "Ultrasonic Characterization of Damage in Thick FRP Composites." In Engineering Mechanics Conference 2000. Reston, VA: American Society of Civil Engineers, 2000. http://dx.doi.org/10.1061/40495(302)11.

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Todoroki, Akira. "Electric Current Analysis for Thick Laminated CFRP Composites." In 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
20th AIAA/ASME/AHS Adaptive Structures Conference
14th AIAA. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-1897.

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Hii, A., B. El Said, and S. Hallett. "Second-order Computational Homogenisation for Thick Shell Models: Application to Non-linear Multiscale Analysis of Composites." In VIII Conference on Mechanical Response of Composites. CIMNE, 2021. http://dx.doi.org/10.23967/composites.2021.022.

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Chun, H. J., S. W. Lee, and I. M. Daniel. "Analysis of Nonlinear Flexural Behavior of Thick Composites With Fiber Waviness." In ASME 1999 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/imece1999-0899.

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Abstract A finite element analysis model was developed to predict flexural behavior of thick composites with uniform, graded and localized fiber waviness. In the analyses, material and geometrical nonlinearties due to fiber waviness were incorporated into the model utilizing energy density and an incremental method. In the model, two kinds of geometrical nonlinearity were considered, one due to reorientation of fibers and the other due to difference of curvatures from one finite element to another during deformation. The finite element analyses utilize the iterative mapping method to incorporate these geometrical nonlinear factors. The model was used to predict not only the flexural behavior of a flat thick composite plate but also of a thick composite plate with initial curvature. Flat composite specimens with various degrees of fiber waviness were fabricated and four-point flexural tests were conducted. The predicted nonlinear behavior by the current model was compared with results from the thin slice model [7] and experiments. Good agreement was observed among them.
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Reports on the topic "Thick Composites"

1

Hahn, H. T., M. Kang, M. Lin, D. Shin, and F. Sonmez. Intelligent Processing of Thick Composites. Fort Belvoir, VA: Defense Technical Information Center, March 1999. http://dx.doi.org/10.21236/ada390234.

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Blake, H. W., H. J. Grimsby, J. M. Starbuck, and D. E. Welch. Development of performance models for thick composites in compression. Office of Scientific and Technical Information (OSTI), November 1991. http://dx.doi.org/10.2172/10106720.

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Blake, H. W., H. J. Grimsby, J. M. Starbuck, and D. E. Welch. Development of performance models for thick composites in compression. Office of Scientific and Technical Information (OSTI), November 1991. http://dx.doi.org/10.2172/6110846.

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DeTeresa, S. The structural integrity of affordable thick-section fiber composites. Office of Scientific and Technical Information (OSTI), June 1999. http://dx.doi.org/10.2172/9806.

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Fink, Bruce K., Ahmed M. Monib, John W. Gillespie, and Jr. Damage Tolerance of Thick-Section Composites Subjected to Ballistic Impact. Fort Belvoir, VA: Defense Technical Information Center, May 2001. http://dx.doi.org/10.21236/ada394856.

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Boyd, Steven E., and James P. Wolbert. Multi-Impact Durability and Processing of Thick-Section Carbon-Glass/Epoxy Hybrid Composites Toughened With Thermoplastic Polyurethane Inter-Layer Films. Fort Belvoir, VA: Defense Technical Information Center, September 2012. http://dx.doi.org/10.21236/ada570176.

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Gama, Bazle A., Jia-Run Xiao, Md J. Haque, Chian-Fong Yen, and John W. Gillespie Jr. Experimental and Numerical Investigations on Damage and Delamination in Thick Plain Weave S-2 Glass Composites Under Quasi-Static Punch Shear Loading. Fort Belvoir, VA: Defense Technical Information Center, February 2004. http://dx.doi.org/10.21236/ada421310.

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

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9

Frame, B. J., and W. G. Dodge. Wet-filament winding fabrication of thick carbon fiber/polycyanate resin composite. Office of Scientific and Technical Information (OSTI), June 1997. http://dx.doi.org/10.2172/565219.

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

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