Relevant bibliographies by topics / Notched composite

Contents

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

Academic literature on the topic 'Notched composite'

Author: Grafiati
Published: 4 June 2021
Last updated: 13 February 2022

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Journal articles on the topic "Notched composite"

1

Wang, Ze Xing, Jin Hua Jiang, and Nan Liang Chen. "Notch Size and Loading Rate on the Tensile Behavior of Woven Fabric Reinforced Flexible Composite with Symmetrical Double Edge Notch." Applied Mechanics and Materials 341-342 (July 2013): 49–53. http://dx.doi.org/10.4028/www.scientific.net/amm.341-342.49.

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In order to investigate the effects of lager notch ratio (2α/W) and loading rate on the tensile behavior of woven fabric reinforced flexible composites, in this study, fracture mechanism and tensile strength of finite woven fabric-reinforced flexible composite materials with a through-the-thickness symmetrical located double edge notches is experimentally investigated, and the effects of notch size, loading rate on the tensile properties of notched specimen are analyzed. The results show that the woven fabric reinforced flexible composites exhibit notch sensitivity and loading rate dependent.
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De Giorgi, Marta, Riccardo Nobile, and Fania Palano. "kf Evaluation in GFRP Composites by Thermography." Applied Sciences 11, no. 11 (2021): 5200. http://dx.doi.org/10.3390/app11115200.

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Since the presence of a notch in a mechanical component causes a reduction in the fatigue strength, it is important to know the kf value for a given notch geometry and material. This parameter is fundamental in the fatigue design of aeronautical components that are mainly made of composites. kf is available in the literature for numerous types of notch but only for traditional materials such as metals. This paper presents a new practice, based on thermographic data, for the determination of the fatigue notch coefficient kf in composite notched specimens. The innovative aspect of this study is
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Kawai, M., and A. Kasuga. "Anisotropic size effect law for notched strength of unidirectional carbon/epoxy laminates – Part 2: Comparison with experiment." Journal of Composite Materials 51, no. 5 (2016): 603–21. http://dx.doi.org/10.1177/0021998316649779.

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The multiaxial quasi-brittle failure criterion for notched orthotropic composites that was formulated in the first part of this study is evaluated on the basis of the off-axis notched strength of a unidirectional carbon/epoxy composite. Static tension tests are first carried out on center circular hole specimens of different hole diameters and fiber orientations to examine the notch size effect as well as the fiber orientation effect on the off-axis notched strength of the unidirectional composite. Experimental results show that the tensile strength in the fiber direction is more notch-sensiti
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Pham, D. C., X. S. Sun, V. B. C. Tan, B. Chen, and T. E. Tay. "Progressive Failure Analysis of Scaled Double-Notched Carbon/Epoxy Composite Laminates." International Journal of Damage Mechanics 21, no. 8 (2011): 1154–85. http://dx.doi.org/10.1177/1056789511430415.

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This article presents progressive failure analysis of double-notched carbon/epoxy composite laminates with different scales. A numerical analysis strategy based on material property degradation method (MPDM) and cohesive elements (CE) is developed to model progressive failure of scaled double-notched composite laminates, where the material property degradation method is used to model the intralaminar failure and the cohesive elements are employed to account for the delamination at the interfaces. Different failure theories are considered in the material property degradation method–cohesive ele
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Kawai, M. "Anisotropic size effect law for notched strength of unidirectional carbon/epoxy laminates – Part 1: Formulation." Journal of Composite Materials 51, no. 5 (2016): 593–602. http://dx.doi.org/10.1177/0021998316651481.

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A multiaxial quasi-brittle failure criterion for notched orthotropic composites is developed with an emphasis on establishment of an analytical formula to predict their anisotropic notched strength for any notch size under any multiaxial proportional loading. It is formulated by replacing the principal unnotched strengths with the principal notched strengths in the framework of the Tsai–Hill static failure criterion for orthotropic composites. The effects of notch size and specimen width on the principal notched strengths are described by means of the Suo-Ho-Gong model that can consider notch
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Herráez, M., A. Fernández, C. S. Lopes, and C. González. "Strength and toughness of structural fibres for composite material reinforcement." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 374, no. 2071 (2016): 20150274. http://dx.doi.org/10.1098/rsta.2015.0274.

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The characterization of the strength and fracture toughness of three common structural fibres, E-glass, AS4 carbon and Kevlar KM2, is presented in this work. The notched specimens were prepared by means of selective carving of individual fibres by means of the focused ion beam. A straight-fronted edge notch was introduced in a plane perpendicular to the fibre axis, with the relative notch depth being a 0 / D ≈0.1 and the notch radius at the tip approximately 50 nm. The selection of the appropriate beam current during milling operations was performed to avoid to as much as possible any microstr
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Kamiya, Shoji, and Hideki Sekine. "Damage Mechanism and Apparent Fracture Strength of Notched Fiber-Reinforced Composite Laminates." Key Engineering Materials 430 (March 2010): 53–67. http://dx.doi.org/10.4028/www.scientific.net/kem.430.53.

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Apparent fracture strength of notched fiber-reinforced composite laminates depends on the notch tip radius even if it is evaluated in terms of the local parameters such as the stresses at a notch tip or the stress intensity factors. Although numbers of phenomenological explanations have been made, this phenomenon has not yet been physically clear enough. In order to elucidate its key mechanism, our interest is here focused on the interlaminar crack extension from a notch tip in cross-ply laminates subjected to mode-I loading. We find a stochastically expected upper bound of interlaminar crack
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Patel, Mitesh, Stephen Daynes, and Chun H. Wang. "The Influence of Orthotropy and Taper Angle on the Compressive Strength of Composite Laminates with Scarfed Holes." Advanced Materials Research 891-892 (March 2014): 178–84. http://dx.doi.org/10.4028/www.scientific.net/amr.891-892.178.

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The residual strengths of laminated composites containing notches or holes depend on the characteristic dimension of the notches as well as the laminate properties. This paper presents an experimental and computational investigation of the effect of orthotropy as well as scarf notch angles on the compressive strength of composite laminates made of seven different stacking sequences with the number of plies ranging between 20 and 24. Specimens containing scarfed holes of different scarf angles (6° and 10°) and straight holes of two different diameters (3.175mm and 6.35mm) were tested for compar
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Duva, J. M., E. J. Lang, F. Mirzadeh, and C. T. Herakovich. "Probabilistic Perspective on the Failure of Composite Laminae." Applied Mechanics Reviews 43, no. 5S (1990): S288—S293. http://dx.doi.org/10.1115/1.3120830.

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A probabilistic approach is presented for predicting the applied stress at failure for notched and unnotched unidirectional brittle matrix fibrous composites. It is assumed that failure is caused by the transverse normal stress alone. The mean value of the applied stress at failure can be calculated for any test coupon once the distribution of the transverse normal stress is known. Results are presented for axial and transverse tensile loading of notched coupons and transverse tensile loading of unnotched coupons. The widely observed linear ln–ln relationship between applied stress at failure
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Liang, Li, Pu Rong Jia, and Gui Qiong Jiao. "Progressive Failure Study of Discrete-Source Damage in Stiffened Composite Panels." Advanced Materials Research 314-316 (August 2011): 963–67. http://dx.doi.org/10.4028/www.scientific.net/amr.314-316.963.

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In this paper experimental and FEA methods were used to study the damage propagation and failure properties of stiffened composite panels with discrete-source damage. The influence of discrete-source damage on residual strength of the composite panel was also investigated. The research results indicated that notched composite panel was suitable to simulate the damage property of stiffened composite panel with discrete-source damage. It has showed that there is high strain concentration at the notch end. And break-through of the stringer can make the load path changed. Based on different failur
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Dissertations / Theses on the topic "Notched composite"

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Kothidar, Arjun. "Use of finite element method to evaluate the strength response of notched composite laminates under tension." Pullman, Wash. : Washington State University, 2008. http://www.dissertations.wsu.edu/Thesis/Fall2008/A_Kothidar_120508.pdf.

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Thesis (M.S. in mechanical engineering)--Washington State University, December 2008.<br>Title from PDF title page (viewed on July 6, 2009). "Department of Mechanical and Materials Engineering." Includes bibliographical references (p. 115-118).
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Toribio, Michael Garcia-Lopez 1975. "Compressive response of notched composite-honeycomb sandwich panels." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/50540.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.<br>Includes bibliographical references (leaves 237-250).<br>Experimental and numerical work was conducted to understand better the compressive response of notched composite sandwich panels. The quasi-static uniaxial compressive response of notched (circular through hole) E-glass/epoxy- NomexTM sandwich panels were studied experimentally. Two different woven fabric architectures were examined. The key failure mechanism was observed to be linear damage zones (LDZs) emanating from the notch tip (in
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Chern, Shue-Ming. "Analysis of notched composite plates under in-plane loading /." Thesis, Connect to this title online; UW restricted, 1999. http://hdl.handle.net/1773/7125.

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Munden, Daniel Christopher. "Development of a Progressive Failure Model for Notched Woven Composite Laminates." Thesis, Virginia Tech, 2018. http://hdl.handle.net/10919/85058.

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As part of the Composite Technology for Exploration (CTE) project at NASA, woven fabric composites are being investigated for their use in Space Launch System (SLS) hardware. Composites are more difficult to analyze than isotropic materials and require more complex methods for predicting failure. NASA is seeking a method for predicting the damage initiation and propagation of woven fabric composites in order to utilize these materials effectively in SLS hardware. This work focuses on notched woven fabric composites under tensile loading. An analytical model consisting of a macro-level failure
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Budiman, Haryanto Tiara. "An assessment of subscale notched specimens for composites shear property measurement." Thesis, This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-09052009-040300/.

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Aidi, Bilel. "Experimental and Numerical Analysis of Damage in Notched Composites." Diss., Virginia Tech, 2016. http://hdl.handle.net/10919/82559.

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This dissertation contains the results from an experimental study, numerical, and analytical study conducted on quasi-isotropic carbon fiber laminates containing a center hole (notch) subjected to constant amplitude tension-tension fatigue loading in order to investigate the effect of fatigue damage development on the residual properties. Quasi-static tests were initially performed on notched composites using digital image correlation (DIC) to determine the strain profiles at selected transverse sections of the outer ply of the laminates and the static strength of the laminates. Subsequently,
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Gojuri, Arun. "Stability of End Notched Flexure Specimen." Thesis, Högskolan i Skövde, Institutionen för teknik och samhälle, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:his:diva-4487.

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This paper deals with two-dimensional Finite Element Analysis of the End Notched Flexure (ENF) specimen. The specimen is known to be unstable if the crack length is shorter than some critical crack length acr. A geometric linear two-dimensional Finite Element (FE) analysis of the ENF specimen is performed to evaluate acr for isotropic and orthotropic elastic materials, respectively. Moreover, the Mode II Energy Release Rate (ERR) JII and the compliance of the specimen are calculated. The influence of anisotropy is studied. Comparisons are made with the results from beam theory. This work is an
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Jen, Ming-Hwa Robert. "The residual strength determination due to fatigue loading by fracture mechanics in notched composite materials." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/54303.

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The objective of this investigation is to predict the residual strength of notched composite Iaminates with various layups, subjected to low frequency fatigue loading with constant amplitude at room temperature, by using a material modeling approach, fracture and fatigue mechanics and the finite element method (FEM). For simplicity, after thousands of cycles, the geometry of a circular hole of the deformed laminate was categorized as (1) uniformly expanded hole into elliptic shape, (2) crack propagation around the hole transversely. Both types were studied for 12 cases of layups with various
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Beuth, Jack L. "An analytical and experimental study of crack extension in center- notched composites." Thesis, Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/101161.

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The normal stress ratio theory for crack extension in anisotropic materials is studied analytically and experimentally in order to evaluate its validity. The theory is applied within a macroscopic-level analysis of a single center notch of arbitrary orientation in a unidirectional composite material. The bulk of the analytical work of this study applies an elasticity solution for an infinite plate with a center line crack to obtain critical stress and crack growth direction predictions. An elasticity solution for an infinite plate with a center elliptical flaw is also used to obtain qualitativ
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Graham, Una. "Experimental and theoretical analyses on un-notched and pin-loaded metal matrix composite laminated plates." Thesis, University of Bristol, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.314423.

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Books on the topic "Notched composite"

1

Poon, C. Tensile fracture of notched composite laminates. National Research Council Canada, 1991.

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Naik, Rajiv A. Observations of fatigue crack initiation and damage growth in notched titanium matrix composites. National Aeronautics and Space Administration, Langley Research Center, 1990.

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Johnson, W. S. Elastic-plastic stress concentrations around crack-like notches in continuous fiber reinforced metal matrix composites. National Aeronautics and Space Administration, Langley Research Center, 1987.

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Johnson, W. S. Elastic-plastic stress concentrations around crack-like notches in continuous fiber reinforced metal matrix composites. National Aeronautics and Space Administration, Langley Research Center, 1987.

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Craugh, Linda E. Progressive failure modeling in notched cross-ply fibrous composites. Naval Postgraduate School, 1999.

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Webb, Geoffrey Matthew. The effects of sub-critical damage on the notched strength of carbon fibre composites. National Library of Canada = Bibliothèque nationale du Canada, 1993.

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Bakis, Charles E. Fatigue response of notched laminates subjected to tension-compression cyclic loads. Virginia Polytechnic Institute and State University, 1986.

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Johnson, W. S. Fatigue damage growth mechanisms in continuous fiber reinforced titanium matrix composites. National Aeronautics and Space Administration, Langley Research Center, 1990.

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Johnson, W. S. Fatigue damage growth mechanisms in continuous fiber reinforced titanium matrix composites. National Aeronautics and Space Administration, Langley Research Center, 1990.

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J. C. F. N. van Rijn. Preliminary model for the blunt notch behaviour of fibre metal laminates. National Aerospace Laboratory, 1994.

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Book chapters on the topic "Notched composite"

1

Kellas, S., J. Morton, and S. M. Bishop. "Damage Development in Notched Carbon Fibre Composites Subjected to Fatigue Loading." In Composite Structures 3. Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-4952-2_4.

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Cirese, P., C. Folchitto, M. Marchetti, and M. Porzi. "Damage Propagation in Notched CFRP Laminates." In Durability of Polymer Based Composite Systems for Structural Applications. Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3856-7_21.

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Morris, Don H. "Modeling the Failure Strength of Notched Graphite/Polyimide Plates Subjected to Extreme Temperatures." In Composite Structures 3. Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-4952-2_25.

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Valentin, D., G. Cailletaud, and M. Renault. "Application of Continuum Damage Mechanics to Post Failure Analysis of Notched Cross Plied Laminates." In Composite Structures 5. Springer Netherlands, 1989. http://dx.doi.org/10.1007/978-94-009-1125-3_51.

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Ashrafi, Mahdi, and Mark E. Tuttle. "High Strain Gradient Measurements in Notched Laminated Composite Panels by Digital Image Correlation." In Composite, Hybrid, and Multifunctional Materials, Volume 4. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-06992-0_10.

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Kageyama, K., M. Kikuchi, and K. Nonaka. "Fatigue Damage Analysis of Notched Carbon/Epoxy Composite by Spate and Finite Element Method." In Developments in the Science and Technology of Composite Materials. Springer Netherlands, 1990. http://dx.doi.org/10.1007/978-94-009-0787-4_25.

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Ghosh, Asish, Michael G. Jenkins, Mattison K. Ferber, Jouko Peussa, and Jonathan A. Salem. "Elevated-Temperature Fracture Resistances of Monolithic and Composite Ceramics Using Chevron-Notched Bend Tests." In Fracture Mechanics of Ceramics. Springer US, 1992. http://dx.doi.org/10.1007/978-1-4615-3348-1_6.

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Buffière, Jean-Yves, Eric Maire, Robert Künzi, Gilles Peix, and Peter Cloetens. "Damage Evolution inside a Notched Sample of Metal Matrix Composite Studied by Synchrotron X-Ray Micro-Tomography." In Microstructural Investigation and Analysis. Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527606165.ch23.

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Jen, Ming-Hwa R. "Fatigue Crack Propagation in Centrally Notched Composites." In Low Cycle Fatigue and Elasto-Plastic Behaviour of Materials. Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-009-3459-7_112.

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Brandt, A. M., and P. Stroeven. "Fracture Energy in Notched Steel Fibre Reinforced Concrete Beams." In Brittle Matrix Composites 3. Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3646-4_8.

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Conference papers on the topic "Notched composite"

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Morscher, Gregory N., John Z. Gyekenyesi, and Andrew L. Gyekenyesi. "Mechanical Behavior of Notched SiC/SiC Composites." In ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/2001-gt-0461.

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Gas turbine components such as combustor liners or turbine vanes are subject to regions of high stress-concentration, e.g. attachment to the frame or at cooling holes. Ceramic matrix composites (CMCs) are potential materials for high temperature applications in gas turbines. They offer some capability to relieve stress at regions of high stress-concentration via matrix damage accumulation. In this study notch sensitivity was examined for woven SiC fiber reinforced, melt-infiltrated SiC matrix composites with a BN interphase, utilizing either Hi-Nicalon™ fibers or the stiffer Sylramic® fibers.
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Vignoli, Lucas L., and Jaime T. P. de Castro. "NOTCHED STRENGTH OF SYMMETRIC ANGLE-PLY LAMINATES." In Brazilian Conference on Composite Materials. Pontifícia Universidade Católica do Rio de Janeiro, 2018. http://dx.doi.org/10.21452/bccm4.2018.03.03.

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QIAO, YAO, ANTINIO ALESSANDRO DELEO, KUOTIAN LIAO, and MARCO SALVIATO. "Multi-axial Fatigue Behavior of Notched Composite Structures." In American Society for Composites 2018. DEStech Publications, Inc., 2018. http://dx.doi.org/10.12783/asc33/25993.

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Vaidya, Rajesh, and C. Sun. "Fracture criterion for notched thin composite laminates." In 37th Structure, Structural Dynamics and Materials Conference. American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-1354.

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Ganesan, R., and A. K. Arumugam. "Effect of Notch Location on the Stress Concentration and Reliability of Notched Composite Laminates Based on a Probabilistic Approach." In ASME 2007 International Mechanical Engineering Congress and Exposition. ASMEDC, 2007. http://dx.doi.org/10.1115/imece2007-41178.

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Composite materials and laminates are being widely used in aerospace and automotive industries due to their less weight to stiffness ratio. Especially the use of composite laminates, made up of Carbon or Graphite Fiber Reinforced Plastics (CFRP/GFRP), in military and commercial aircraft structures has progressed steadily over the past few decades. Drilling holes and making cutouts in these laminates are unavoidable for practical reasons. These holes (or) cutouts introduces stress concentration near the hole (or) cutout edge and reduces the load-bearing capacity of the structure. Cutouts are ma
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Tate, Jitendra S., Ajit D. Kelkar, and Ronnie Bolick. "Performance Evaluation of Notched Biaxial Braided Composites." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-59883.

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Braided composites have good properties in mutually orthogonal directions, more balanced properties than traditional tape laminates, and have potentially better fatigue and impact resistance due to the interlacing. Another benefit is reduced manufacturing cost by reducing part count. Because of these potential benefits braided composites are being considered for various applications ranging from primary/secondary structures for aerospace structures [1]. These material systems are gaining popularity, in particular for the small business jets, where FAA requires take off weights of 12,500 lb. or
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Kelkar, Ajit, and Samuel Tameru. "Fatigue Behaviour of Notched Fiber Glass Braided Composite." In 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2426.

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Xiao, Jian, Xiujun E. Fang, Jim Lua, Rui Li, and Dianyun Zhang. "A Multiscale Fatigue Damage Prediction for Notched Composite Components." In 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-0655.

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Hu, Yile, and Erdogan Madenci. "Peridynamic Modeling of Fatigue Damage in Notched Composite Laminates." In 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-1140.

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Ahn, Junghyun, and Anthony Waas. "The elevated temperature compressive response of notched composite laminates." In 40th Structures, Structural Dynamics, and Materials Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-1249.

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