Relevant bibliographies by topics / Laminate; Impact; Failure

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

Academic literature on the topic 'Laminate; Impact; Failure'

Author: Grafiati
Published: 4 June 2021
Last updated: 14 February 2022

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Journal articles on the topic "Laminate; Impact; Failure"

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Zhou, Wei, Mao Sheng Cao, Hai Bo Jin, Yi Long Lei, and Ji Li Rong. "Compressive Failure of Carbon/Epoxy Laminate Composites under High Impact Loading." Key Engineering Materials 324-325 (November 2006): 1237–40. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.1237.

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The effect of strain rate on the dynamic compressive of carbon/epoxy composite materials was investigated via the split Hopkinson pressure bar (SHPB) technique. The specimens were tested in the thickness, as well as in the in-plane direction at different high strain rates. The macro- and micro-fracture morphology of the damaged laminated specimens was obtained utilizing the scanning electron microscope (SEM). The experimental results showed that the compressive properties could be significantly affected by the strain rates. The compressive strength and the ultimate strain in the in-plane direction were obviously lower than that in the thickness direction. As the strain rate increased, the laminate had not enough time to respond, the splitting failure of 0° ply of laminates loaded in-plane along 0° was firstly found, then interfacial crack and delamination were induced, the specimens were crushed to fragments at the highest strain rate. No obvious damage of laminates loaded through the thickness could be observed at strain rate below 2000 s-1. The main way of the dynamic compressive failures through the thickness was shear failure due to the brittle fracture of the fiber at 2260 s-1.
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Yuan, Q., T. Czigany, and L. Ye. "Failure Behaviour of Cross-Ply Carbon Fibre/Epoxy Laminates Subjected to Transverse Impact and Static Perforation." Advanced Composites Letters 9, no. 5 (September 2000): 096369350000900. http://dx.doi.org/10.1177/096369350000900506.

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Cross-ply carbon fibre reinforced epoxy laminates (CF/EP) were toughened with interleaf consisting of random PET fibre mat embedded in a modified epoxy resin. The interleaved laminate had a smaller delamination area but higher energy absorption than the base laminate during transverse impact perforation. In static tests, the interleaved laminate had a higher maximum load and greater deformation at the perforation, compared to the base laminate. The damage development was monitored using acoustic emission technique. The interleaved laminate had less cumulative acoustic emission events than the base laminate. The distribution of the rise time was used to identify the major failure mechanisms.
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Olsson, R. "Modelling of impact damage zones in composite laminates for strength after impact." Aeronautical Journal 116, no. 1186 (December 2012): 1349–65. http://dx.doi.org/10.1017/s0001924000007673.

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AbstractThis paper reviews findings on the type, morphology and constitutive behaviour of impact damage zones during loading after impact and their effect on the laminate strength and stability. The paper is limited to tape prepreg based monolithic laminates, although some similarities exist with impact damage in textile based laminates. Damage zones have a complex geometry with several damage types, which results in an interaction and competition between different failure mechanisms, e.g. local and global buckling, compressive failure, and delamination growth. Hence, simplified damage models may provide incorrect predictions of the failure load and failure mechanisms after impact. The constitutive behaviour of damage zones has been studied experimentally in tension and compression using an inverse method, and the results have been compared with detailed FE models of a generic impact damage. The paper is concluded with a discussion on analytical and computational models to predict the resulting strength of impacted laminates.
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Farrow, I. R., K. Potter, A. Fisher, and M. Kelly. "Impact of Adhesively Bonded Composite Joints with Edge Effect." Advanced Composites Letters 9, no. 6 (November 2000): 096369350000900. http://dx.doi.org/10.1177/096369350000900603.

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A pilot project has been carried out to investigate the effect of impact on single-lap bonded composite joints based on AS4-8552 laminates and Cybond BR4535A adhesive. Low velocity impacts at an energy level sufficient to cause barely visible impact damage, were conducted on single lap joint specimens at different joint positions. Impact caused delaminations in the upper and lower laminates and localised through-thickness cracking in the adhesive. Residual tensile joint strengths of the impacted joint specimens with near-edge damage were reduced to approximately 50% of the un-impacted value. Failure surface inspections revealed localised through-thickness adhesive shear cracking as a governor of the original impact delamination pattern in the laminates and laminate delamination as the cause of ultimate tensile failure.
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Koziol, Mateusz. "Mechanical Performance of Polymer-Matrix Laminate Reinforced with 3D Fabric during Three-Point Impact Bending." Solid State Phenomena 246 (February 2016): 193–96. http://dx.doi.org/10.4028/www.scientific.net/ssp.246.193.

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The paper presents the analysis of course and the results of impact 3-point bending tests conducted with use of instrumented Charpy hammer (CEAST RESIL 50 hammer + MC101 registrator + CALKA J computer program) on GFRP laminate specimens cut of the panels manufactured by RTM method on base of classic plain-woven fabric preform and 3D fabric. The specimens of the 3D laminate were cut alternatively along (W direction) and transverse (P direction) to the translaminar interweave strands. It was found that maximum force obtained in the tests is comparable for both the classic and the 3D laminates. Deformability of the 3D (W) specimen is by about 20% higher than those of the classic laminate, whereas it is higher by even 75% for 3D (P). The trend of deformability observed for the tested laminates differs from known trends characteristic for static conditions what confirms different material response mechanisms at low and higher load rate. Failure energy in the classic and in the 3D (W) specimen is on comparable level. However, 3D (P) specimen showed slightly lower summary failure energy than the classic one and almost twice a high failure initiation energy (first effects of failure occur before maksimum load is gained).
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Kumar, M. Ashok, A. M. K. Prasad, and D. V. Ravishankar. "Effect of Quasi-Static Loading on the Composite Laminates." Advanced Engineering Forum 20 (January 2017): 10–21. http://dx.doi.org/10.4028/www.scientific.net/aef.20.10.

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The low velocity impact is a common phenomenon which occurs in fiber reinforced polymer composite products like LPG cylinders, fighter aircraft fuel drop tanks, aircraft wing surfaces, sports goods etc. The consequences of low velocity impact will create a considerable damage and ultimately lead to a premature failure of the structure. Hence the polymer composites for engineering applications must be provided with a better design solution. From the literature survey it is observed that, the response of composite laminates subjected to quasi-static loading, exhibits similar results as that of low velocity impact. Polymer reinforced composites are poor in damage tolerance with better strength to weight ratio than conventional materials. However composite materials can be tailored to meet the design requirements by manipulating fiber orientations and laminae stacking sequence. In the present paper, principles of classical laminate theory are considered for analysis. FEM is implemented for thorough understanding of the failure mechanism of each laminate by layer wise. Simulated quasi-static loading tests and observed the layer wise distribution of transverse strain intensity. The experimental setup is designed and fabricated as per ASTM D 6264 standards. The E-glass/epoxy composite laminate is quasi-statically loaded at its center by a steel ball indenter of diameter 8.7mm and its response is measured by the degree of opacity or translucency in terms of interlaminar and intra-laminar damage area. The stacking sequence of composite laminates are chosen as [00/600]12, [00/750]12 and [00/900]12. The damage areas obtained from numerical analysis are in good agreement with experimental results.
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Zhang, Chen, Yunfei Rao, Zhe Li, and Wei Li. "Low-Velocity Impact Behavior of Interlayer/Intralayer Hybrid Composites Based on Carbon and Glass Non-Crimp Fabric." Materials 11, no. 12 (December 5, 2018): 2472. http://dx.doi.org/10.3390/ma11122472.

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Composites have gained wide use in structural applications; however, they are sensitive to impact damage. The use of hybrid composites is an effective way to overcome this deficiency. The effects of various hybrid structures of interlayer and intralayer warp-knitted fabrics with carbon and glass fibers on the low-velocity impact behavior of composite laminates were studied. Drop-weight impact tests were conducted on two types of interlayer, sandwich and intralayer hybrid composite laminates, which were compared with homogenous composite laminates. During low-velocity impact tests, the time histories of impact forces and absorbed energy by laminate were recorded. The failure modes were analyzed using the micro-CT (computed tomography) and C-scan techniques. The results revealed that the hybrid structure played an important role in peak force and the absorbed energy, and that the hybrid interface had an influence on damage modes, whereas the intralayer hybrid composite laminate damage was affected by the impact location. The intralayer hybrid laminate with C:G = 1:1 exhibited better impact resistance compared to the other hybrid structures.
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Schwab, Martin, Melanie Todt, and Heinz E. Pettermann. "A multiscale approach for modelling impact on woven composites under consideration of the fabric topology." Journal of Composite Materials 52, no. 21 (February 14, 2018): 2859–74. http://dx.doi.org/10.1177/0021998318755865.

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A computationally efficient multiscale modelling approach for predicting impact damage within fabric reinforced laminated composites is presented. In contrast to common ply-level approaches, the topology of a multi-layered fabric reinforced laminate is resolved at tow-level for a sub-domain embedded in a shell layer with homogenised representation of the laminate. The detailed sub-domain is entirely modelled using shell elements, where material nonlinearities such as damage and plasticity-like behaviour of the tows, inelastic behaviour of unreinforced resin zones up to failure and delamination between plies are accounted for. To exemplify the capabilities of the approach, an explicit finite element simulation of a laminated plate consisting of eight carbon fabric reinforced epoxy plies with eight harness satin weaving style in a drop weight impact test setup is conducted. The spatial and temporal distribution of intra- and inter-ply damage is predicted and the total energy absorption by the plate, as well as the contributions of individual damage mechanisms are evaluated. The predictions show very good agreement with corresponding experimental data from the literature and give insight into the impact behaviour of the laminate beyond the capability of usual experiments. The new approach allows to resolve the stress concentrations due to fabric topology in detail. Compared to common ply-level approaches this is reflected in different predicted energy absorptions per mechanism although, the total energy absorption hardly differs. This is especially important when the post impact behaviour of laminates is predicted as it is strongly influenced by the extent of the individual damage mechanisms.
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Hasan, Md Zahid. "Interface Failure of Heated GLARETM Fiber–Metal Laminates under Bird Strike." Aerospace 7, no. 3 (March 17, 2020): 28. http://dx.doi.org/10.3390/aerospace7030028.

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Many high-strength composite materials have been developed for aircraft structures. GLAss fiber REinforced aluminum (GLARE) is one of the high-performance composites. The review of articles, however, yielded no study on the impact damage of heated GLARE laminates. This study, therefore, aimed at developing a numerical model that can delineate the continuum damage of GLARE 5A-3/2-0.3 laminates at elevated temperatures. In the first stage, the inter-laminar interface failure of heated GLARE laminate had been investigated at room temperature and 80 °C. The numerical analysis employed a three-dimensional GLARE 5A-3/2-0.3 model that accommodated volumetric cohesive interfaces between mating material layers. Lagrangian smoothed particles populated the projectile. The model considered the degradation of tensile and shear modulus of glass fiber reinforced epoxy (GF/EP) at 80 °C, while incorporated temperature-dependent critical strain energy release rate of cohesive interfaces. When coupled with the material particulars, an 82 m/s bird impact at room temperature exhibited delamination first in the GF/EP 90°/0° interface farthest from the impacted side. Keeping the impact velocity, interface failure propagated at a slower rate at 80 °C than that at room temperature, which was in agreement with the impact damage determined in the experiments. The outcomes of this study will help optimize a GLARE laminate based on the anti-icing temperature of aircraft.
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Kim, Jae Hoon, Duck Hoi Kim, Hu Shik Kim, and Byoung Jun Park. "A Study on Low Velocity Impact of Woven Glass/Phenolic Composite Laminates Considering Environmental Effects." Key Engineering Materials 297-300 (November 2005): 1303–8. http://dx.doi.org/10.4028/www.scientific.net/kem.297-300.1303.

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The objectives of this study are to evaluate the internal damage and compressive residual strength of composite laminate by impact loading. To investigate the environmental effects, as-received and accelerated-aged glass/phenolic laminates are used. UT C-Scan is used to determine the impact damage characteristics and CAI tests are carried out to evaluate quantitatively the reduction of compressive strength by impact loading. The damage modes of the woven glass/phenolic laminates are evaluated. In the case of the accelerated-aged laminates, as aging time increases, initial failure energy and residual compressive strength decrease.
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Dissertations / Theses on the topic "Laminate; Impact; Failure"

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Hallett, Stephen Richard. "Small specimen impact testing and modelling of carbon fibre T300/914." Thesis, University of Oxford, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.363953.

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Schwarzer, Norbert, and Peggy Heuer-Schwarzer. "Failure analysis on laminate structures of windsurfing boards using thin film modelling techniques." Universitätsbibliothek Chemnitz, 2006. http://nbn-resolving.de/urn:nbn:de:swb:ch1-200600125.

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Within this paper recently developed mathematical tools for the modelling of contact problems on thin film structures [1] for multilayers and gradient coatings are adapted to allow the investigation of laminate structures of transversal isotropy. Applying series approaches using Bessel and Sinus functions complete three dimensional solutions can be found for relatively complex laminate structures allowing to model quasistatic contact, impact and bending loads. Worked into a small computer program the approach can be used to model laminate structures with up to 100 different layers on an ordinary personal computer in an acceptable calculation time. The new tool is applied to analyse a variety of load problems typically occurring in windsurfing and leading to damage of the boards consisting of a laminated shell and an polymer foam core. [1] N. Schwarzer: „Modelling of the mechanics of thin films using analytical linear elastic approaches“, habilitation thesis of the TU-Chemnitz 2004, department “Physics of solid bodies”, http://archiv.tu-chemnitz.de/pub/2004/0077
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Romariz, Luiz André. "Dano em placas laminadas devido ao impacto a baixas velocidades." Universidade de São Paulo, 2008. http://www.teses.usp.br/teses/disponiveis/3/3151/tde-10112008-110839/.

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Materiais compósitos laminados possuem uma alta eficiência estrutural, mas que é comprometida pela baixa resistência a cargas de impacto. O objetivo deste trabalho é o desenvolvimento de uma metodologia de simulação numérica para a estimativa de danos causados por cargas de impacto a baixas velocidades em placas de material compósito laminado. Ensaios experimentais foram realizados em placas reforçadas com tecidos de fibra de carbono e matriz de resina epóxi. Foram avaliadas três espessuras. Os carregamentos de impacto com uma massa em queda livre foram pontuais e transversais à placa, com intervalos de energia variando entre 5J e 94J, com velocidades inferiores a 6 m/s. As simulações numéricas utilizaram um programa comercial de elementos finitos com integração explícita. Foram avaliados dois critérios de falha da lâmina. O primeiro é o critério de máxima tensão. O segundo é uma proposta de modificação no critério de falha de Hashin, para sua aplicação em laminados reforçados com tecidos bidirecionais. Também foram avaliados quatro diferentes critérios de degradação da lâmina. As evoluções das forças de contato entre o impactador e a placa foram muito bem representadas numericamente. As áreas e os comprimentos dos danos numéricos foram similares ou maiores que os medidos nos resultados experimentais.
Laminate composite materials have high structural efficiency, however it is jeopardized due the low strength to impact loads. The objective of this work is to develop a numerical simulation methodology that estimates the damage in laminate plates caused by low velocity impact. Experimental tests were performed on laminate plates reinforced with weaven carbon fibers and epoxi resine. Three thickness plates were evaluated. The impact loads were transversal and punctual. They were done with drop-test, the impact energy range is between 5J and 94J, and the velocities were lower than 6m/s. The numerical simulations were done with FEM commercial code with explict integration. Two lamina failure criteria were evaluated. The first is the maximum stress. The second is a proposed modification of the Hashin failure criterion in order to be applied on the fabric laminates. Four lamina degradation criteria were evaluated too. The numerical contatct loads between the plate and impactor were well represented. The numerical damaged areas and lengths were similar or greater than the experimental results.
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Kalluri, Ravi Shankar. "Failure of transparent polymer composite laminated glass panels under impact loading." Diss., Columbia, Mo. : University of Missouri-Columbia, 2007. http://hdl.handle.net/10355/4902.

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Thesis (M.S.)--University of Missouri-Columbia, 2007.
The entire dissertation/thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file (which also appears in the research.pdf); a non-technical general description, or public abstract, appears in the public.pdf file. Title from title screen of research.pdf file (viewed on March 27, 2008) Includes bibliographical references.
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Kalay, Yunus Emre. "Low Velocity Impact Characterization Of Monolithic And Laminated Aa 2024 Plates By Drop Weight Test." Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/1096726/index.pdf.

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The objective of this study was to investigate the low velocity impact behavior of both monolithic and laminated aluminum alloy plates. For this purpose, a drop-weight test unit was used. The test unit included the free fall and impact of an 8 kg hammer with an 8 mm punching rod from 0.5 m to 4 m. The relationship between the change in static mechanical properties (hardness, ultimate tensile strength, yield strength, strain hardening rate) and low velocity impact behavior of monolithic aluminum plates were investigated. Tested material was AA 2024, heat treatable aluminum alloy, which was artificially aged to obtain a wide range of mechanical properties. In the second stage of the study, the relationship between the low velocity impact behavior of laminated plates was compared with that of monolithic aluminum plates at identical areal densities. For this purpose, a series of AA 2024 thin plates were combined with different types of adhesives (epoxy, polyurethane or tape). Finally, fracture surface of the samples and microstructure at the deformation zone were examined with both scanning electron microscope and optical microscope. It is found that the ballistic limit velocities of AA 2024 plates increase with increase in hardness, yield strength and ultimate tensile strength. It is also found that a linear relation exists between the ballistic limit velocity and strain hardening rate or hardness. When the low velocity impact behaviors of laminated and monolithic targets were compared, it was seen that monolithic targets have a higher ballistic limit velocity values for from the 2.5 to 10 mm thick targets. It was also observed that adhesives are not so effective to strengthen the low velocity impact performance. On the other hand, with increasing Charpy impact energy, penetration and perforation behaviors are getting worse in 10 to 30 joules energy range. Different types of failure mechanisms involving, plugging, dishing, stretching and bending were determined. For high strength and thick plates plugging type deformation was leaded. In contrast, for thinner and weaker targets bending, stretching and dishing type failures were dominating. For laminated targets also dishing type failure was determined.
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Gopinath, Gautam. "Progressive damage and failure of unidirectional fiber reinforced laminates under impact loading with composite properties derived from a micro-mechanics approach." Diss., Virginia Tech, 2011. http://hdl.handle.net/10919/37534.

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Micromechanics theories have been used to develop macro-level constitutive relations for infinitesimal elastoplastic deformations of unidirectional fiber reinforced laminates. The matrix is assumed to be isotropic and deform elasto-plastically and the fibers transversely isotropic and linear elastically. We have analyzed damage initiation, damage progression, and failure of 16-ply unidirectional fiber reinforced laminates impacted at normal incidence by a rigid sphere. The damage is assumed to initiate when at least one of Hashinâ s failure criteria is satisfied with the evolving damage modeled by an exponential relation. Transient three dimensional impact problems have solved using the finite element method (FEM) by implementing the material damage model as a user defined subroutine in the FE software ABAQUS. From strains supplied by ABAQUS the subroutine uses the free shear traction technique and values of material parameters of the constituents to find average stresses in a FE, and checks for Hashinâ s failure criteria. If the damage has initiated, the subroutine evaluates the damage developed, computes resulting stresses, and provides them to ABAQUS. The irreversibility of the damage is satisfied by requiring that the damage evolved does not decrease during unloading. The delamination failure mode is simulated by using the cohesive zone model and the degradation of material properties already available in ABAQUS. The computed time histories of the axial load acting on the impactor are found to agree well with the experimental ones available in the literature. The effect of stacking sequence in the laminate upon the impact load has been ascertained.
Ph. D.
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García, Rodríguez Santiago. "X-ray tomography investigation of the impact damage mechanisms of thin-ply composites and the use of veils to improve their impact tolerance." Doctoral thesis, Universitat de Girona, 2019. http://hdl.handle.net/10803/668028.

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This thesis investigates the impact response of novel laminates made with “thin-plies” as well as proposes a toughening method to improve their impact tolerance. To this purpose, we devised a wide experimental campaign combined with cutting-edge non-destructive inspection techniques such as nanometric-resolution X-ray micro-computed tomography. Overall, we gave a step forward towards the inclusion of thin-ply laminates in new commercial aircraft designs
Aquesta tesi investiga la resposta a impacte de laminats compostos fabricats amb "thin-plies" i proposa una tècnica de reforç externa per millorar la seva tolerància al dany (el mètode consisteix a intercalar vels molt fins amb forma de "teranyina" entre les diferents capes del laminat per absorbir més energia durant l'impacte). Per a això, hem dissenyat una extensa campanya experimental acompanyada amb tècniques punteres d'inspecció no destructiva com la tomografia computada de raigs-X. En definitiva, hem fet un pas endavant cap a la inclusió dels laminats "thin-ply" en el disseny de futurs avions
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Kinvi-Dossou, Gbèssiho Raphaël. "Étude de la résistance à l’impact et de l’endommagement des composites stratifiés à matrice Elium acrylique : caractérisation expérimentale et modélisation numérique multi-échelle." Thesis, Université de Lorraine, 2018. http://www.theses.fr/2018LORR0249/document.

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Face aux défis environnementaux actuels, les industriels ont mis en œuvre de nouveaux matériaux recyclables et permettant une réduction significative de la masse. Le développement de la résine thermoplastique Elium par ARKEMA s’inscrit dans cette problématique. L’utilisation de cette résine pour la fabrication de pièces composites qui peuvent être sujettes à des dommages d’impact, nécessite au préalable des études, dans le but de comprendre leurs mécanismes de ruine sous ce type de sollicitation. Ainsi, la présente thèse propose une contribution à l’analyse multi-échelle de la tenue à l’impact des composites stratifiés à base de la résine Elium. Une étude expérimentale préliminaire a permis de confirmer la meilleure résistance à l’impact des composites à matrice Elium acrylique, comparativement à celles des composites thermodurcissables conventionnels. Ensuite, les performances à l’impact des composites stratifiés ont été améliorées par l’introduction de copolymères à blocs dans la matrice. Ces derniers sont capables de former des micelles de tailles nanométriques et ainsi d’améliorer la ténacité de la matrice acrylique. Les effets de l’énergie d’impact, de la température et de la composition en nanocharges sur la réponse du matériau composite ont été analysés. Afin de proposer un outil d’aide à la prédiction de la réponse à l’impact des matériaux fibres de verre/Acrylique, deux stratégies de modélisation ont été retenues. La première modélisation (macroscopique) considère le pli tissé du stratifié comme un matériau homogène tandis que la seconde (mésoscopique) utilise une description géométrique de l’ondulation et de l’entrecroisement des torons noyés dans la résine Elium. Ces deux modèles considèrent des zones cohésives à l’interface entre les plis adjacents pour simuler le délaminage interlaminaire. Des essais de délaminage (expérimentaux et numériques) ont permis d’alimenter le modèle d’endommagement de l’interface interplis. D’autre part, des essais de caractérisation du comportement mécanique et de l’endommagement du matériau couplés à l’homogénéisation multi-échelle des matériaux par la Mécanique du Génome de Structure ont permis d’identifier les paramètres du modèle macroscopique. A l’échelle mésoscopique, le modèle géométrique a été réalisé grâce au logiciel Texgen. Ce logiciel permet d’obtenir une description approchée mais réaliste de l’ondulation des torons de fibres. La même description a servi à l’homogénéisation numérique multi-échelle des stratifiés étudiés. La simulation numérique de l’impact basse vitesse a été effectuée au moyen du logiciel d’éléments finis ABAQUS/Explicit. Les modèles de comportement du matériau ont été implémentés via la routine utilisateur VUMAT. Les résultats obtenus offrent une bonne corrélation avec les données expérimentales
In the race for light materials able of meeting modern environmental challenges, an acrylic resin (Elium) has been developed. Elium is a thermoplastic resin able to replace thermosetting matrices, which are widespread nowadays in the industrial world. The present study aims to evaluate the impact resistance and to understand the failure mechanisms of composite laminates based on acrylic matrix under impact loading. We provide a contribution to the multiscale analysis of the impact resistance of laminated composite.First, the impact resistance and the damage tolerance of the acrylic resin based composites were compared with those of conventional composites. Then, the impact performance of the laminated composites has been enhanced by adding copolymer blocks to the liquid acrylic resin. These copolymers are able to form micelles of nanometer sizes, which lead to the improvement of both the acrylic matrix fracture toughness and the impact resistance. The effects of the impact energy, temperature, and composition in nano-copolymers have also been investigated.In order to provide a numerical tool for the prediction of the impact response of the glass fiber/Acrylic laminates, two strategies have been analyzed. The first one, performed at the macroscopic scale, considers the woven ply of the laminate as homogeneous material, and the second one (at the mesoscopic scale), deals with a realistic geometrical description of the yarns undulation. Both models use cohesive zones at the interface between the adjacent plies, to simulate the delamination. For this purpose, experimental and numerical delamination tests were performed to feed the inter-ply damage model. Mechanical tests for material characterization were also performed on specimens in order to identify the ply-damage model parameters. The Mechanics of Structure Genome (MSG) and a finite element based micromechanics approaches were then conducted to evaluate the effective thermomechanical properties of the yarns and the plain woven composite laminate. The realistic topological and morphological textures of the composite were accounted through Texgen software. These numerical impact simulations were performed using the finite element software ABAQUS/Explicit. Both models were implemented through a user material subroutine VUMAT. The obtained results appear in a good agreement with the experimental data and confirm the relevance of the proposed approach
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Hsueh, Chun-Teng, and 薛鈞謄. "Study of Impact and Failure Analysis for Laminates Composite with Crack Patch." Thesis, 2011. http://ndltd.ncl.edu.tw/handle/84531865439332875495.

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碩士
大葉大學
工業工程與科技管理學系
99
In this research, finite elements method such as a plane, and a solid are used to build a laminated composite model for analyzing various cracks therein for comparison with the literature to confirm the accuracy of the model. In the experiments are used manufacturing methods such as resin transfer molding (RTM) and the hand lay-up technique that carbon fiber prepreg of materials are used to produce differential types of cracks such of bilateral, central, and centrally perforated in composite laminate composites as well as in a patch test fragment for a tensile test. This study primarily used ANSYS finite element software to analyze the strain and stress intensity factors of composite laminates and the cracks in a patch test fragment to establish an accurate analytical model. Furthermore, ANSYS simulation to analyze the structure of cracks can be recommended. In the optimal design, this research is used the Particle Swarm Optimization (PSO) method that the differential conditions (length -to- width ratio (b/a), layer angles of composite patch, boundary and force conditions) found optimal manufacturing process parameters of composite plate specimen with a crack patch. This research is achieved the goal of maximum stiffness in composite materials under the impact. Finally, this theory analysis values are compared experimental data to prove the correct of the theory analysis and optimal design.
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Books on the topic "Laminate; Impact; Failure"

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(Editor), J. K. Kim, and T. X. Yu (Editor), eds. Impact Response and Dynamic Failure of Composites and Laminate Materials (Key Engineering Materials). Trans Tech Publications, 1998.

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L, Kemmerly Heather, and United States. National Aeronautics and Space Administration., eds. Influence of impactor mass on the damage characteristics and failure strength of laminated composite plates: Presented at the 39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference : Long Beach, California, April 20-23, 1998. [Washington, DC: National Aeronautics and Space Administration, 1998.

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A new merit function for evaluating the flaw tolerance of composite laminates. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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A new merit function for evaluating the flaw tolerance of composite laminates. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 2000.

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A new merit function for evaluating the flaw tolerance of composite laminates. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Book chapters on the topic "Laminate; Impact; Failure"

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Zhou, Wei, Mao Sheng Cao, Hai Bo Jin, Yi Long Lei, and Ji Li Rong. "Compressive Failure of Carbon/Epoxy Laminate Composites under High Impact Loading." In Fracture and Damage Mechanics V, 1237–40. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-413-8.1237.

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Aminanda, Y. "Impact Study on Aircraft Type Laminate Composite Plate; Experimental, Failure Criteria and Element Model Review." In Advanced Structured Materials, 157–88. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-23659-4_11.

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Olsson, Robin, Rickard Juntikka, and Leif E. Asp. "High Velocity Hail Impact on Composite Laminates – Modelling and Testing." In Dynamic Failure of Composite and Sandwich Structures, 393–426. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5329-7_9.

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Kerr-Anderson, Eric, Selvum Pillay, Basir Shafiq, and Uday K. Vaidya. "Compressively Pre-stressed Navy Relevant Laminated and Sandwich Composites Subjected to Ballistic Impact." In Dynamic Failure of Composite and Sandwich Structures, 151–76. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5329-7_4.

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Lopresto, V., and G. Caprino. "Damage Mechanisms and Energy Absorption in Composite Laminates Under Low Velocity Impact Loads." In Dynamic Failure of Composite and Sandwich Structures, 209–89. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5329-7_6.

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Bouvet, Christophe, Natthawat Hongkarnjanakul, Samuel Rivallant, and Jean-Jacques Barrau. "Discrete Impact Modeling of Inter- and Intra-laminar Failure in Composites." In Dynamic Failure of Composite and Sandwich Structures, 339–92. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5329-7_8.

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Stevanović, M. M., T. B. Stecenko, M. C. Kostić, and D. B. Briški-Gudić. "Effect of Impactor Shape on Residual Tensile Strength and Tensile Failure of Carbon/Epoxy Laminates." In Composite Structures 5, 323–31. Dordrecht: Springer Netherlands, 1989. http://dx.doi.org/10.1007/978-94-009-1125-3_16.

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Mahajan, Puneet, K. S. Krishnamurthy, and R. K. Mittal. "Impact response of a laminated cylindrical composite shell panel." In Structural Failure and Plasticity, 139–44. Elsevier, 2000. http://dx.doi.org/10.1016/b978-008043875-7/50157-x.

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Sahoo, Sarmila. "Laminated Composite Hypar Shells as Roofing Units." In Composites and Advanced Materials for Industrial Applications, 249–69. IGI Global, 2018. http://dx.doi.org/10.4018/978-1-5225-5216-1.ch011.

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This chapter presents a broad perspective of the recent research done on laminated composite hypar shells used as roofing units. Different types of analysis including bending, vibration, buckling, impact, and failure are included. The chapter is collated and categorized based on various aspect of research. The first aspect concentrates on typical analyses including problems in which various boundary conditions and laminations are considered. Then it focuses on the structural complexities which include stiffened shells, shells with cutouts, etc. The basic results of theoretical and experimental investigations of stress-strain state, vibration, buckling, and failure are summarized in this chapter incorporating the review of materials published in scientific and technical journals and proceedings in recent times.
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Pelfrene, J., S. Van Dam, W. Van Paepegem, and J. Degrieck. "Numerical simulation of elastic, fracture and post-failure response of monolithic and laminated glass under impact loading." In COST Action TU0905 Mid-term Conference on Structural Glass, 413–20. CRC Press, 2013. http://dx.doi.org/10.1201/b14563-56.

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Conference papers on the topic "Laminate; Impact; Failure"

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Park, Chun, Adam Propst, Kara Peters, and Mohammed A. Zikry. "Sensor Networks for In-Situ Failure Identification in Woven Composites." In ASME 2009 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2009. http://dx.doi.org/10.1115/smasis2009-1283.

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This paper presents experimental measurements of the response of woven composite laminates to multiple low-velocity impacts. Damage initiation and progression occur at multiple physical and temporal scales in heterogeneous materials, including fiber breakage, matrix cracking, delamination and matrix relaxation. The sensor networks/interrogators were therefore chosen specifically to provide insight into the order and progression of different failure modes. Measurements of the contact force between the impactor and composite are measured throughout impact. Additionally, the dissipated energy per impact event is also calculated from the impactor velocity. Surface mounted and embedded fiber Bragg grating sensors are used for the measurement of the laminate response. Peak wavelength measurements are performed during impact at 1 kHz, while full-spectral scanning is performed at 5 Hz during relaxation period of the laminate immediately after impact and quasi-statically to measure post-impact residual strain states within the laminate. The results highlight the depth of information embedded within the FBG full-spectral data sensors, as well as the added insight to be gained from combined global-local measurements.
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Bernhardt, S., M. Ramulu, and A. S. Kobayashi. "Low-Velocity Impact Response Characterization of a Hybrid Titanium Composite Laminate." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-82836.

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The low-velocity impact response of a hybrid titanium composite laminate (HTCL), known as TiGr, was compared to that of graphite/epoxy composite. The TiGr material comprised of two outer plies of titanium foil surrounding a composite core. The composite core was PIXA-M (a high temperature thermoplastic) reinforced by IM-6 graphite fibers and consolidated by an induction heating process. The impact response of TiGr was characterized by two modes of failure which differed by failure or non-failure in tension of the bottom titanium ply. The ductility of titanium caused buckling by yielding whereas the brittle adjacent composite ply lead to fracture. The maximum failure force of the material correlated well with the previously reported static flexural data, and the material outperformed the commonly used graphite/epoxy.
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Garrett, Ryan, Kara Peters, and Mohammed A. Zikry. "Sensor Networks for In-Situ Failure Identification in Woven Composites Throughout Impact." In ASME 2007 International Mechanical Engineering Congress and Exposition. ASMEDC, 2007. http://dx.doi.org/10.1115/imece2007-42737.

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In this study, the development of embedded fiber Bragg grating (FBG) sensor networks within composite materials is investigated. Various densities of optical fibers were embedded within two-dimensional woven composite laminates, and low-velocity impact damage responses were evaluated to determine the effects on the mechanical behavior of the laminates. The woven composites were subjected to multiple strikes at 2 m/s until perforation occurred, and the impactor position and acceleration were monitored throughout each event. From these measurements, we obtained dissipated energies and contact forces for specimens with and without embedded optical fibers. Cross sectional optical micrographs of the specimens were also used to determine the local effects of the embedded fibers on neighboring fibers and the surrounding matrix material, both before and after impact events. Multiple FBG sensors were serially multiplexed together to create a single fiber sensing network capable of monitoring damage for each impact event. Residual strain information was gathered through strain distributions along the FBG sensors to map out the near-field and far-field regions with respect to the impact location. The resulting data will be used to better monitor and predict damage in the composite system when combined with global response data from the laminate itself.
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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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Pearson, James, Mohanraj Prabhugoud, Mohammed Zikry, and Kara Peters. "In-Situ Failure Identification in Woven Composites Throughout Impact." In ASME 2006 International Mechanical Engineering Congress and Exposition. ASMEDC, 2006. http://dx.doi.org/10.1115/imece2006-15784.

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In this study, measurements form low-impact velocity experiments including embedded and surface mounted optical fiber Bragg grating (FBG) sensors were used to obtain detailed information pertaining to damage progression in two-dimensional laminate woven composites. The woven composites were subjected to multiple strikes at 2m/s until perforation occurred, and the impactor position and acceleration were monitored throughout each event. From these measurements, we obtained dissipated energies and contact forces. The FBG sensors were embedded and surface mounted at different critical locations near penetration-induced damaged regions. These FBG sensors were used to obtain initial residual strains and axial and transverse strains that correspond to matrix cracking and delamination. The transmission and reflection spectra were continuously monitored throughout the loading cycles. They were used, in combination with the peak contact forces, to delineate repeatable sensor responses corresponding to material failure. From the FBG spectra, fiber and matrix damage were separated by an analysis based on signal intensity and the behavior of individual Bragg peaks as a function of evolving and repeated impact loads. This provided independent feedback on the integrity of the Bragg gratings which can serve to eliminate errors in the strain data such as due to sensor debonding or fracture. The critical indicators present in the sensor spectra for the mapping of these sensor failure modes are derived.
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"Analysis of CFRP Laminates Properties under Different Layup Structure using Finite Element Analysis." In Structural Health Monitoring. Materials Research Forum LLC, 2021. http://dx.doi.org/10.21741/9781644901311-30.

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Abstract. In order to study the effect of the layup structure on the static strength and low-velocity impact strength of carbon fiber/epoxy composite (CFRP) laminates, theoretical simulation analysis under different laying angles have been carried out. In this study, Finite Element Analysis (FEA) models for different CFRP laminate specimens are created using ANSYS Workbench by changing the relative volume fraction of 0°, 45° and 90° plies in each specimen and their relative location. The FEA results revealed that the increase of relative volume of 90° ply will improve the impact the impact resistance performance, while the increase of relative volume of 45° ply will take the opposite effect. Moreover, when the relative volume fraction of 0°, 45° and 90° plies are the same, the strength performance of the laminate cannot be improved by changing the thickness of the outermost layer. The study illustrated the significant effects of different stacking sequences and laying angles on the tensile and flexural failure mechanisms in composite laminates, leading to some suggestions to improve the design of composite laminates.
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Prakash, Raghu V., and Monalisha Maharana. "Thermo-Mechanical Response of Hybrid Polymer Composites During Tensile Loading." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-71335.

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The fiber reinforced polymers are candidate materials for critical applications in view of the high strength, stiffness characteristics; however, they are highly anisotropic and have complex failure mechanisms. Thermo-mechanical response characterization is one of the means of identifying damage progression in these materials. In this study, tensile tests were conducted on the hybrid composite laminates and Infrared thermographs were used to capture the thermal response of the specimen for the entire range of loading till failure. The tests were conducted on natural fiber composite specimens and hybrid (natural + synthetic fiber) composite specimens. The natural fibers used were in the form of uni-directionally stitched mats of Sunhemp, Kenaf and Flax fiber. The synthetic fibers used were bi-directionally woven Carbon fiber mat and Glass fiber mat. All the laminates were prepared using the hand lay-up technique. Four different configurations of the laminates were prepared. The natural fiber composite laminate comprised of Sunhemp fiber mat in a polyester resin system. The Sunhemp fiber mat was also used with woven Glass fiber mat on one side to prepare an unsymmetrical hybrid laminate. The Kenaf fiber mat was placed between layers of woven Glass fiber mats whereas the flax fiber mat was placed between the woven carbon fiber mats; Epoxy LY 556 and hardener Araldite® was used as the matrix. The finished laminate thickness was 2.1 mm and dog-bone tensile specimens were extracted using a CNC router. Some of the specimens were impacted at low velocities from two different heights to study the change in thermo-mechanical response, post-impact, during tensile test. Temperature response as a function of applied stress, failure strain and work done suggests that there is a correlation between the fracture events that take place during tensile test with the temperature response. In cases where there was a ply-drop failure, the rate of temperature change could identify the failure events, even though the resultant peak temperature was less. When the specimen failed by a single mode of failure (delamination/fiber failure), the temperature rise was found to be proportional to the input work done during tensile testing.
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Cheng, Wing, and Shigeru Itoh. "Modeling of Delamination in Composites." In ASME 2005 Pressure Vessels and Piping Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/pvp2005-71224.

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Stacking sequence, number of plies, and geometry of the composite structure have significant impact on the strength and reliability of the structure. The most detrimental failure mode in composite structures is delamination. Modeling of delamination failure is, therefore, a very important technique for predicting the reliability of composite structures. A modified crack closure technique was used in determining the driving force for crack propagation and branching of laminated composites at the interfaces. Mixed mode fracture parameters, GI for the opening mode, GII for the shear mode, were calculated using the technique for two typical composite structures; namely a composite laminate subjected to tensile loading, and a curved composite laminate subjected to bending. Results of these analyses give a better understanding on the crack growth behavior of these structures, and therefore, provide insight in the composite construction for improved design of the structures.
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Kimbro, Evan, and Ajit D. Kelkar. "Development of Energy Absorbing Laminated Fiberglass Composites Using Electrospun Glass Nanofibers." In ASME 2011 International Mechanical Engineering Congress and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/imece2011-64746.

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Failure due to delamination of composite laminates via low velocity impact damages is critical because of the subsurface nature of delamination. Traditional methods such as stitching and Z-pinning, while improving interlaminar properties in woven composites, lead to a reduction of the in-plane properties. Electrospun non-woven sheets of nanofibrous mat applied at interfacial regions offer an option to traditional treatments. The objective of the present study is to observe the energy absorption during the event of an impact upon a composite laminate. The use of Tetra Ethyl Orthosilicate (TEOS) chemically engineered glass nanofibers manufactured using electrospinning technique in woven glass fiber resin pre-impregnated composite laminates were investigated for their potential to improve the interlaminar properties. Electrospun glass nanofibers pre-impregnated woven mats were manufactured using a vacuum bag and cured in a computer controlled convection oven. The interlaminar properties of the nano engineered hybrid composites were obtained using low velocity impact tests and are compared with those without the presence of electrospun nanofiber layers, to study their influence. Impacted specimens were examined using C-scan analysis to detect impact damage dimensions. It was observed when electrospinning nanofibers were added to lamina interfaces, the electrospun fiber embedded coupons had larger impact damage area compared to the coupons without electrospun fiber layers.
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Lua, Jim, and William Gregory. "Development of a Dynamic Failure Prediction Tool for Marine Composite Structures." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-82784.

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Composite ship structures are subjected to both the low and high velocity impact during their service life. The dynamic impact can generate fiber, matrix and/or delamination damage inside a woven fabric composite laminate, which may significantly reduce its stiffness and strength. Both the structural mechanics and fracture mechanics based models cannot fully capture the impact damage evolution due to coexistence of continuum and discrete damage. The stress and strain at the element level cannot be directly used to predict the constituent damage and the resulting mechanism driven stiffness degradation. In this paper, a hybrid discrete and continuum damage model is developed and numerically implemented within the LS-DYNA environment via a user-defined material model. The continuum damage progression and its associated stiffness degradation are predicted based on the constituent stress/strain and their associated failure criteria while the delamination damage is numerically captured via a cohesive interface model.
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