Relevant bibliographies by topics / Interlaminar damage

Academic literature on the topic 'Interlaminar damage'

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Published: 4 June 2021
Last updated: 19 February 2022

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Journal articles on the topic "Interlaminar damage"

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Miura, Masaya, Yasuhide Shindo, Tomo Takeda, and Fumio Narita. "Damage Development in Hybrid Composite Laminates under Three-Point Bending at Cryogenic Temperatures." Key Engineering Materials 452-453 (November 2010): 565–68. http://dx.doi.org/10.4028/www.scientific.net/kem.452-453.565.

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This paper studies the damage behavior and interlaminar shear properties of hybrid composite laminates subjected to bending at cryogenic temperatures. Cryogenic short beam shear tests were performed on hybrid laminates combining woven glass fiber reinforced polymer (GFRP) composites with polyimide films, and microscopic observations of the specimens were made after the tests. A progressive damage analysis was also conducted to simulate the initiation and growth of damage in the specimens and to determine the interlaminar shear strength based on the maximum shear stress in the failure region. The predicted load-deflection curve and damage pattern show good agreement with the test results, and the numerically determined interlaminar shear strength is higher than the apparent interlaminar shear strength.
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Allix, O., P. Ladevéze, and A. Corigliano. "Damage analysis of interlaminar fracture specimens." Composite Structures 31, no. 1 (January 1995): 61–74. http://dx.doi.org/10.1016/0263-8223(95)00002-x.

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Gillespie, J. W. "Damage Tolerance of Composite Structures: The Role of Interlaminar Fracture Mechanics." Journal of Offshore Mechanics and Arctic Engineering 113, no. 3 (August 1, 1991): 247–52. http://dx.doi.org/10.1115/1.2919927.

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Layered fiber-reinforced composite structures are susceptible to crack initiation and growth in the resin-rich layer between plies. Delamination represents one of the most prevalent life-limiting failure modes in laminated composite structures. Interlaminar fracture mechanics represents one approach to assess the damage tolerance of composite structures. This paper is organized into two major sections. The first sections introduces interlaminar fracture mechanics and test methods that have been developed to characterize the Mode I, II and III interlaminar fracture toughness of composite laminates. In the second section, the role of interlaminar fracture mechanics in assessing damage tolerance of composite structures is defined through the following case studies: residual compression after impact strength, instability related delamination growth in compressively loaded laminates and delamination growth in composite laminates with discontinuous internal plies.
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Abdullah, Muhammad A'imullah, Mohammad Reza Arjmandi, Seyed Saeid Rahimian Koloor, King Jye Wong, and Mohd Nasir Tamin. "Interlaminar Damage Behavior of CFRP Composite Laminates under Cyclic Shear Loading Conditions." Advanced Materials Research 1125 (October 2015): 121–25. http://dx.doi.org/10.4028/www.scientific.net/amr.1125.121.

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This paper provides quantitative description of interlaminar damage process in CFRP composite laminates under cyclic shear loading. Quasi-static end-notched flexural (ENF) test on 16-ply CFRP composite laminate beam, [0]16 and its complementary validated FE model provide the reference “no-interlaminar damage” condition. Two identical ENF samples were fatigue to 50000 cycles, but at different load amplitude of 90 and 180 N, respectively (Load ratio, R = 0.1) to induce selectively property degradation at the interface crack front region. Subsequent quasi-static ENF tests establish the characteristic of the interlaminar damage degradation. The residual peak load for the fatigued ENF samples is measured at 1048 and 914 N for the load amplitude of 90 and 180 N, respectively. Cyclic interlaminar shear damage is represented by a linear degradation of the residual critical energy release rate, GIIC with the accumulated damage. Reasonably close comparisons of the predicted residual load-displacement responses with measured curves serve to verify the suitability of the assumed bilinear traction-separation law for the cyclic cohesive zone model (CCZM) used.
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Lonetti, Paolo, Raffaele Zinno, Fabrizio Greco, and Ever J. Barbero. "Interlaminar Damage Model for Polymer Matrix Composites." Journal of Composite Materials 37, no. 16 (August 2003): 1485–504. http://dx.doi.org/10.1177/0021998303034741.

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Burlayenko, Vyacheslav, and Tomasz Sadowski. "FE modeling of delamination growth in interlaminar fracture specimens." Budownictwo i Architektura 2, no. 1 (June 11, 2008): 095–109. http://dx.doi.org/10.35784/bud-arch.2315.

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Interlaminar fracture specimens like Double Cantilever Beam (DCB), End Notched Flexural (ENF), Single Leg Bending (SLB) etc. are widely used for studying the interlaminar toughness of composite laminates. The aim of this paper is to analysis delamination specimens within the framework of a meso-level damage modeling of composite laminates. In this case interlaminar interface is assumed as a damageable homogeneous layer between adjacent layers of the specimen bulk material. The degradation of the interlaminar connection can be taken into account by means either of an appropriate damage initiation criterion and damage evolution law or using fracture mechanics approach. Onset and growth of the delamination pre-existing crack in the fracture specimens are simulated by using both modeling possibility within commercial finite element code ABAQUSTM. Comparisons between numerical predictions of used different finite element models as well as available experimental data have been performed.
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Castellanos, AG, Md S. Islam, E. Tarango, Y. Lin, and P. Prabhakar. "Interlaminar reinforcement for enhancing low-velocity impact response of woven composites." Textile Research Journal 88, no. 15 (May 12, 2017): 1710–20. http://dx.doi.org/10.1177/0040517517708536.

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This paper proposes a novel technique for improving the low-velocity impact response of woven composites, which involves synthesizing ZnO nanowires on dry woven carbon fabric layers. ZnO nanowire reinforcements were added to the interlaminar regions that are most susceptible to damage within layered composites, which were determined using finite element method analysis. Upon fabricating the laminates with and without ZnO nanowire interlaminar reinforcements, low-velocity impact responses were investigated next and the degree of damage was experimentally determined. The physical tests reveal that the samples with ZnO nanowires experience a lower degree of damage, up to a maximum of 25% for different impact energies, in comparison to the samples without ZnO nanowires. Therefore, the study presented in this paper shows the potential of using ZnO nanowires as interlaminar reinforcements for woven composites to improve their impact damage resistance.
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Cui, W. C., M. R. Wisnom, and M. Jones. "Failure mechanisms in three and four point short beam bending tests of unidirectional glass/epoxy." Journal of Strain Analysis for Engineering Design 27, no. 4 (October 1, 1992): 235–43. http://dx.doi.org/10.1243/03093247v274235.

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Three and four point bending tests are compared both analytically and experimentally. In all the three point bending tests, damage was observed under the loading roller in addition to the interlaminar shear failure, while in the four point bending tests, only interlaminar shear failure was observed. Therefore, this four point bending test is valid for measuring the interlaminar shear strength. From the finite element analysis, it is found that the roller diameter is a critical parameter in determining the stress concentrations in short beam tests. In order to avoid damage under the roller and thus to make the short beam test a valid means for measuring the interlaminar shear strength, the appropriate roller diameters should be chosen. The damage under the loading roller in the three point bending test basically reduces the effective specimen thickness and thus this test underestimates the interlaminar shear strength. The interlaminar shear cracks in the short beam tests were found to be randomly distributed in a region between 30 percent and 70 percent through the thickness from the top surface. This is due to the non-linear shear response which means that the shear stress distribution is more uniform near the middle of the section. Also the maximum value of the shear stress is lower than the maximum value given by beam theory. A non-linear shear correction factor is suggested to account for this effect and for the glass/epoxy composite tested here, the actual interlaminar shear strength is only about 83 percent of the apparent value from classical beam theory. The interlaminar shear crack does not occur at the location of maximum shear stress. This may be because there is insufficient energy to propagate a crack at this location.
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Li, N., P. H. Chen, and Q. Ye. "A damage mechanics model for low-velocity impact damage analysis of composite laminates." Aeronautical Journal 121, no. 1238 (March 6, 2017): 515–32. http://dx.doi.org/10.1017/aer.2017.6.

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ABSTRACTA method was developed to predict numerically the damage of composite laminates with multiple plies under low-velocity impact loading. The Puck criterion for 3D stress states was adopted to model the intralaminar damage including matrix cracking and fibre breakage, and to obtain the orientation of the fracture plane due to matrix failure. According to interlaminar delamination mechanism, a new delamination criterion was proposed. The influence of transverse and through-thickness normal stress, interlaminar shear stress and damage conditions of adjacent plies on delamination was considered. In order to predict the impact-induced damage of composite laminates with more plies quickly and efficiently, an approach, which can predict the specific damage of several plies in a single solid element, was proposed by interpolation on the strains of element integration points. Moreover, the proposed model can predict specific failure modes. A good agreement between the predicted delamination shapes and sizes and the experimental results shows correctness of the developed numerical method for predicting low-velocity impact damage on composite laminates.
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Constantinescu, Dan Mihai, Marin Sandu, Liviu Marsavina, Radu Negru, Matei Constantin Miron, and Dragos Alexandru Apostol. "Evaluation of Interlaminar Damage and Crack Propagation through Digital Image Correlation Method." Key Engineering Materials 399 (October 2008): 105–12. http://dx.doi.org/10.4028/www.scientific.net/kem.399.105.

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Interface damage characterization and interlaminar failure of sandwich specimens with two initial interlaminar defects (inserts) is done by using the digital image correlation method. Mode I tests reveal interesting particularities on damage localization and unstable crack propagation. After analyzing the experimentally obtained results, we propose as a failure parameter the local strain at the crack tip or, alternatively, the crack tip opening displacement which quantifies the non-linear phenomena.
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Dissertations / Theses on the topic "Interlaminar damage"

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González, Juan Emilio Vicente. "Simulation of interlaminar and intralaminar damage in polymer-based composites for aeronautical applications under impact loading." Doctoral thesis, Universitat de Girona, 2011. http://hdl.handle.net/10803/22834.

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La aplicación de materiales compuestos de matriz polimérica reforzados mediante fibras largas (FRP, Fiber Reinforced Plastic), está en gradual crecimiento debido a las buenas propiedades específicas y a la flexibilidad en el diseño. Uno de los mayores consumidores es la industria aeroespacial, dado que la aplicación de estos materiales tiene claros beneficios económicos y medioambientales. Cuando los materiales compuestos se aplican en componentes estructurales, se inicia un programa de diseño donde se combinan ensayos reales y técnicas de análisis. El desarrollo de herramientas de análisis fiables que permiten comprender el comportamiento mecánico de la estructura, así como reemplazar muchos, pero no todos, los ensayos reales, es de claro interés. Susceptibilidad al daño debido a cargas de impacto fuera del plano es uno de los aspectos de más importancia que se tienen en cuenta durante el proceso de diseño de estructuras de material compuesto. La falta de conocimiento de los efectos del impacto en estas estructuras es un factor que limita el uso de estos materiales. Por lo tanto, el desarrollo de modelos de ensayo virtual mecánico para analizar la resistencia a impacto de una estructura es de gran interés, pero aún más, la predicción de la resistencia residual después del impacto. En este sentido, el presente trabajo abarca un amplio rango de análisis de eventos de impacto a baja velocidad en placas laminadas de material compuesto, monolíticas, planas, rectangulares, y con secuencias de apilamiento convencionales. Teniendo en cuenta que el principal objetivo del presente trabajo es la predicción de la resistencia residual a compresión, diferentes tareas se llevan a cabo para favorecer el adecuado análisis del problema. Los temas que se desarrollan son: la descripción analítica del impacto, el diseño y la realización de un plan de ensayos experimentales, la formulación e implementación de modelos constitutivos para la descripción del comportamiento del material, y el desarrollo de ensayos virtuales basados en modelos de elementos finitos en los que se usan los modelos constitutivos implementados.
The application of polymer-based composites reinforced by long fibers, called advanced Fiber Reinforced Plastic (FRP), is gradually increasing as a result of their good specific mechanical properties and increased flexibility of design. One of the largest consumers is the aerospace industry, since the application of these materials has clear economic and environmental benefits. When composites are to be used in structural components, a design development program is initiated, where a combination of testing and analysis techniques is typically performed. The development of reliable analysis tools that enable to understand the structure mechanical behavior, as well as to replace most, but not all, the real experimental tests, is of clear interest. Susceptibility to damage from concentrated out-of-plane impact forces is one of the major design concerns of structures made of advanced FRPs used in the aerospace industry. Lack of knowledge of the impact effects on these structures is a factor in limiting the use of composite materials. Therefore, the development of virtual mechanical testing models to analyze the impact damage resistance of a structure is of great interest, but even more, the prediction of the post-impact residual strength. In this sense, the present thesis covers a wide range of analysis of the low-velocity and large mass impact events on monolithic, flat, rectangular, polymer-based laminated composite plates with conventional stacking sequences. Keeping in mind that the main goal of this work is the prediction of the residual compressive strength of an impacted specimen coupon, a set of different tasks are performed in order to provide suitable tools to analyze the problem. Accordingly, the topics which are addressed in this thesis are: the analytical description of the impact, the design and the realization of an experimental test plan, the formulation and implementation of constitutive models for the description of the composite material behavior, and the assessment of the performance of virtual tests based on finite element models where the constitutive models are used.
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Orifici, Adrian Cirino, and adrian orifici@student rmit edu au. "Degradation Models for the Collapse Analysis of Composite Aerospace Structures." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080619.090039.

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Iervolino, Onorio. "Enhanced impact resistance and pseudo plastic behaviour in composite structures through 3D twisted helical arrangement of fibres and design of a novel chipless sensor for damage detection." Thesis, University of Bath, 2017. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.723326.

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The future of the aerospace industry in large part relies on two factors: (i) development of advanced damage tolerant materials and (ii) development of advanced smart sensors with the ability to detect and evaluate defects at very early stages of component service life. Laminated composite materials, such as carbon fibre reinforced plastics (CFRP), have emerged as the materials of choice for increasing the performance and reducing the cost and weight of aircrafts, which leads to less fuel consumption and therefore lower CO2 emissions. However, it is well known that these materials exhibit fragile behaviour, poor resistance to impact damage caused by foreign objects and require a relatively slow and labour intensive manufacturing process. These factors prevent the rapid expansion of composite materials in several industrial sectors at the current time. Inspired by the use of rope throughout history and driven by the necessity of creating a lean manufacturing process for composites and enhancing their impact properties, the first part of this work has shown that enhanced damage tolerance and pseudo-ductile behaviour can be achieved with standard CFRP by creatively arranging the fibres into a 3D twisted helical configuration. Through an extensive experimental campaign a new method to arrange fibre reinforcement was presented and its effect investigated. The second part of this PhD work focused on developing a new smart sensor. A spiral passive electromagnetic sensor (SPES) for damage detection on CFRP and glass fibre reinforced plastics (GFRP) is presented in this work. A range of defect types in glass and carbon composite has been considered, such as delamination, perforated holes and cracks. Furthermore, throughout this work, the SPES has been exploited as a multi-sensing device allowing the ability to detect temperature and humidity variation, presence of ice and act as an anti/de-icing device.
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Ben, Kahla Hiba. "Models for bending stiffness in laminates with intralaminar and interlaminar damage." Thesis, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-44595.

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Books on the topic "Interlaminar damage"

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Illg, Walter. Effect of partial interlaminar bonding on impact resistance and loaded-hole behavior of graphite/epoxy quasi-isotropic laminates. Hampton, Va: Langley Research Center, 1986.

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Grami, Vahid, Salim M. Hayek, and Samer N. Narouze. Lumbar Transforaminal and Nerve Root Injections: Fluoroscopy. Oxford University Press, 2016. http://dx.doi.org/10.1093/med/9780199908004.003.0016.

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The transforaminal approach, compared with the interlaminar approach, allows injectate delivery directly at the target nerve root, placing greater amounts of medication at the location of the suspected pathology. The utility of selective nerve root injections includes blocking with local anesthetics specific nerve roots suspected of transmitting radicular symptoms. These diagnostic radicular blocks are often used for presurgical planning. The fluoroscopic-guided lumbar transforaminal epidural steroid injection approaches mentioned in this chapter have been described to safely and effectively deposit medication in the epidural space, adjacent to affected nerve roots transmitting pain signals. It is imperative that proper patient selection, physician training, thorough knowledge of anatomy, vigilance, and effective use of fluoroscopy and radiocontrast dye help to avoid catastrophic tissue damage and embolization.
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Book chapters on the topic "Interlaminar damage"

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Massabò, Roberta. "Effective Modeling of Interlaminar Damage in Multilayered Composite Structures Using Zigzag Kinematic Approximations." In Handbook of Damage Mechanics, 1–34. New York, NY: Springer New York, 2020. http://dx.doi.org/10.1007/978-1-4614-8968-9_91-1.

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Prinz, R. "Damage Rates for Interlaminar Failure of Fatigued CFRP Laminates." In Developments in the Science and Technology of Composite Materials, 189–94. Dordrecht: Springer Netherlands, 1990. http://dx.doi.org/10.1007/978-94-009-0787-4_23.

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Li, Lei, and Zhu Feng Yue. "Analysis of Interlaminar Stresses and Failure around Hole Edge for Composite Laminates under In-Plane Loading." In Fracture and Damage Mechanics V, 1027–30. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-413-8.1027.

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Varandas, L. F., G. Catalanotti, A. Arteiro, António R. Melro, and B. G. Falzon. "Micromechanical modelling of interlaminar damage propagation and migration." In Multi-Scale Continuum Mechanics Modelling of Fibre-Reinforced Polymer Composites, 307–47. Elsevier, 2021. http://dx.doi.org/10.1016/b978-0-12-818984-9.00011-1.

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Bilal Afzal, Muhammad. "Modeling of Damage Evolution of Fiber-Reinforced Composite Structure." In Safety and Risk Assessment of Civil Aircraft during Operation. IntechOpen, 2020. http://dx.doi.org/10.5772/intechopen.93323.

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This chapter is the result of a study of many special disciplines, such as damage of matrix, cracking, interface, debonding, and fiber failure. A damage mechanics model is presented to characterize brittle failure in elastic fiber-reinforced composite materials. During the life of the aircraft, cracks and damage can occur in aviation structures that should be analyzed to determine the decrease in stiffness and resistance due to the presence of the cracks. Theoretical and numerical problems related to intralaminar and interlaminar failure modeling are very well discussed. The formulations of the constitutive models presented in this chapter support the Continuum Damage Mechanics (CDM) approach and enable the control of energy dissipation in relation to each failure mode, regardless of the refinement of the network and the orientation of the fracture plane. In context to CDM, internal thermodynamic irreversible damage variables are defined to quantify the damage concentration in relation to each possible failure mode and to predict the gradual reduction in stiffness for each bond layer. Numerical examples are provided to possibly explain the capabilities of the model.
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Ogihara, S., N. Takeda, K. Matsuo, and A. Kobayashi. "Effects of Thermal Cycling on Damage Progress in Interlaminar-Toughened CFRP Cross-Ply Laminates." In Proceedings of the Eighth Japan-U.S. Conference on Composite Materials, 591–99. CRC Press, 2019. http://dx.doi.org/10.1201/9780367812720-60.

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Chou, I., and K. Namba. "Correlation of Damage Resistance under Low Velocity Impact and Mode II Interlaminar Fracture Toughness in CFRP Laminates." In Proceedings of the Eighth Japan-U.S. Conference on Composite Materials, 459–66. CRC Press, 2019. http://dx.doi.org/10.1201/9780367812720-47.

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Conference papers on the topic "Interlaminar damage"

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Ngabonziza, Yves, Claudia Boldrini, Benjamin Liaw, Jackie Li, and Feridun Delale. "Damage Self-Diagnosis in Carbon Fiber-Reinforced Composites Under Fatigue Loading." In ASME 2010 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2010. http://dx.doi.org/10.1115/smasis2010-3870.

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An experimental study was conducted to sense interlaminar delamination in carbon-fiber composites utilizing inherent material piezoresistivity. Damage detection was carried out using discrete electrodes mounted on a Double Cantilever Beam (DCB) specimen. The DCB composite specimens were tested for fatigue interlaminar fracture. The traditional two-point probe and four-point probe technique were employed to measure the through-thickness electrical resistance change. Optical marker method was also used to detect interlaminar crack growth. The results show that the two-point probe measurements did not capture effectively the delamination propagation while the four-point probe measurement showed a promising sensing capability in terms of delamination propagation.
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Özkaya, Özge, and Altan Kayran. "Nonlinear Static Aeroelastic Behavior of Composite Missile Fin with Interlaminar and Intralaminar Damage." In 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-1449.

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Shindo, Yasuhide, Fumio Narita, Susumu Takahashi, and Takashi Sato. "Mixed-Mode Interlaminar Fracture and Damage of Woven GFRP Laminates at Cryogenic Temperatures." In 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-2408.

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Tong, Jingwei, Min Shen, Shibin Wang, Hong-Qi Li, Francesco Ginesu, and Filippo Bertolino. "Micromechanical experiments of interlaminar deformation and damage in quasi-isotropic thermoplastic composite laminates." In Third International Conference on Experimental Mechanics, edited by Xiaoping Wu, Yuwen Qin, Jing Fang, and Jingtang Ke. SPIE, 2002. http://dx.doi.org/10.1117/12.468828.

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Marashizadeh, Parisa, Mohammad Abshirini, Mrinal Saha, and Yingtao Liu. "Numerical Interlaminar Shear Damage Analysis of Fiber Reinforced Composites Improved by ZnO Nanowires." In ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-23422.

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Abstract In this study, the damage analysis of hybrid carbon fiber reinforced polymer (CFRP) composited with vertically aligned zinc oxide (ZnO) nanowires is investigated numerically. The effect of growing nanowires on improving the interlaminar shear strength (ILSS) of the hybrid structures is explored. The multi-scale model developed to make a bridge between the materials with different length scales available in the hybrid structures, including micro-scale, meso-scale, and macros-scale. The vertically aligned ZnO nanowires on the lamina and embedded in the epoxy matrix creates an enhancement layer. The effective material properties of this layer are evaluated at micro-scale by homogenization analysis. The cohesive zone method is employed in the meso-scale to explore the interfacial behavior and delamination (interlaminar damage) between the homogenized stacking layer and the CFRP lamina. Besides, the strain-based failure criterion is implemented at the macro-scale to investigate the progressive damage of fiber and matrix in CFRP plies. This analysis is programmed in user-defined subroutine linked to ABAQUS finite element software. The three-dimensional hybrid composite short beam in the three-point bending load is simulated in ABAQUS Explicit packager, and the ILSS is obtained. The damage behavior of hybrid composite is compared to the bare CFRP beam. The results indicate that aligning nanowires on the plies improves the performance of CFRP composites.
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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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CUI, XIAODONG, ANAND KARUPPIAH, DINH CHI PHAM, JIM LUA, CALEB SAATHOFF, and WARUNA SENEVIRATNE. "Progressive Damage and Failure Prediction of Interlaminar Tensile Specimen with Initial Fabrication Induced Defects." In American Society for Composites 2018. Lancaster, PA: DEStech Publications, Inc., 2018. http://dx.doi.org/10.12783/asc33/26089.

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Velazquez, Eduardo, and John Kosmatka. "Acoustic Emission-Based Health Monitoring of Interlaminar Matrix-Driven Damage in Advanced Composite Structures." In 51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
18th AIAA/ASME/AHS Adaptive Structures Conference
12th. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-3029.

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Ruggles-Wrenn, M. B., and S. R. Hilburn. "Creep in Interlaminar Shear of an Oxide/Oxide Ceramic Matrix Composite at Elevated Temperature." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-44034.

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Creep behavior in interlaminar shear of an oxide-oxide ceramic composite was evaluated at 1100°C in laboratory air and in steam environment. The composite (N720/AS) consists of a porous aluminosilicate matrix reinforced with laminated, woven mullite/alumina (Nextel™720) fibers, has no interface between the fiber and matrix, and relies on the porous matrix for flaw tolerance. The interlaminar shear properties were measured. The interlaminar shear strength (ILSS) was determined as 7.6 MPa. The creep behavior was examined for interlaminar shear stresses in the 2–6 MPa range. Primary and secondary creep regimes were observed in all tests conducted in air and in steam. Tertiary creep was noted in tests performed at 6 MPa. Creep run-out defined as 100 h at creep stress was not achieved in any of the tests. Larger creep strains and higher creep strain rates were produced in steam. However, the presence of steam had a beneficial effect on creep lifetimes. Composite microstructure, as well as damage and failure mechanisms were investigated.
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10

Abdi, Frank, Saber DorMohammadi, Jalees Ahmad, Cody Godines, Gregory N. Morscher, Sung Choi, Rabih Mansour, and Steve Gonczy. "Optimizing Ceramic Matrix Composite Interlaminar Fracture Toughness (Mode I) Wedge Test." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-58076.

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Abstract:
ASTM test standards for CMC’s Crack Growth Resistance (CGR) may exhibit a zig-zag (wavy) crack path pattern, and fiber bridging. The experimental parameters that may contribute to the difficulty can be summarized as: specimen width and thickness, interface coating thickness, mixed mode failure evolution, and interlaminar defects. Modes I crack growth resistances, GI were analytically determined at ambient temperature using wedge test, a modified double cantilever beam (DCB). Several Finite Element (FE) based Multi-scale modeling potential techniques were investigated: a) Multi-scale progressive failure analysis (MS-PFA); b) Virtual Crack Closure Technique (VCCT). Advantages and disadvantages of each were identified. The final modeling algorithm recommended was an integrated damage and fracture evolution methodology using combined MS-PFA and VCCT. The material tested in this study was a slurry-cast melt-infiltrated SiC/SiC composite with Tyranno ZMI fibers (Ube Industries, Kyoto, Japan) and a BN interphase. The fiber architecture consisted of eight plies of balanced 2-D woven five-harness satin. The total fiber volume fraction was about 30% with half of the fibers in the 0° direction and half in the 90° direction. All specimens had a nominal thickness of 4 mm. An alumina wedge with 18° head angle (2α) was used. In this method, a splitting force is created by inserting a vertically-moving wedge in a notch causing the arms to separate and forcing an interlaminar crack at the sharpest end of the notch The MS-PFA numerical model predicted the damage and fracture evolution and utilized the GENOA UMAT (User Material Subroutine) for Damage and FEM (Finite Element Model) stress intensity and LEFM (Linear elastic Fracture Model), Cohesive Model for Fracture. The analysis results (Fracture energy vs. crack length, Fracture energy vs. load, Fracture energy vs. crack opening displacement) matched the Mode I coupon tests and revealed the following key findings. Mode I-Wedge specimen exhibits: 1) failure mode is due to interlaminar tension (ILT) only in the interface section and a zig-zag pattern observed; 2) VCCT crack growth resistance is well matched to the test data; and 3) failure mode is a mixed mode behavior of Interlaminar tension (ILT) to interlaminar shear (ILS). The final Wedge test specimen configuration optimization includes the sensitivity of design parameters to CGR: a) wedge contact coefficient of friction; b) lever arms thickness, and c) inclined head angle, distance between the initial crack and wedge tip.
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