Relevant bibliographies by topics / Delamination

Academic literature on the topic 'Delamination'

Author: Grafiati
Published: 4 June 2021
Last updated: 7 September 2024

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Journal articles on the topic "Delamination"

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Mei, Hanfei, Asaad Migot, Mohammad Faisal Haider, Roshan Joseph, Md Yeasin Bhuiyan, and Victor Giurgiutiu. "Vibration-Based In-Situ Detection and Quantification of Delamination in Composite Plates." Sensors 19, no. 7 (April 11, 2019): 1734. http://dx.doi.org/10.3390/s19071734.

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This paper presents a new methodology for detecting and quantifying delamination in composite plates based on the high-frequency local vibration under the excitation of piezoelectric wafer active sensors. Finite-element-method-based numerical simulations and experimental measurements were performed to quantify the size, shape, and depth of the delaminations. Two composite plates with purpose-built delaminations of different sizes and depths were analyzed. In the experiments, ultrasonic C-scan was applied to visualize the simulated delaminations. In this methodology, piezoelectric wafer active sensors were used for the high-frequency excitation with a linear sine wave chirp from 1 to 500 kHz and a scanning laser Doppler vibrometer was used to measure the local vibration response of the composite plates. The local defect resonance frequencies of delaminations were determined from scanning laser Doppler vibrometer measurements and the corresponding operational vibration shapes were measured and utilized to quantify the delaminations. Harmonic analysis of local finite element model at the local defect resonance frequencies demonstrated that the strong vibrations only occurred in the delamination region. It is shown that the effect of delamination depth on the detectability of the delamination was more significant than the size of the delamination. The experimental and finite element modeling results demonstrate a good capability for the assessment of delamination with different sizes and depths in composite structures.
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Panda, Rabi S., Prabhu Rajagopal, and Krishnan Balasubramaniam. "Characterization of delamination-type damages in composite laminates using guided wave visualization and air-coupled ultrasound." Structural Health Monitoring 16, no. 2 (September 24, 2016): 142–52. http://dx.doi.org/10.1177/1475921716666411.

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This article reports on the characterization of delamination damages in composite laminates using wave visualization method. A combination of plate-guided ultrasound and air-coupled ultrasonics is used to locate and visualize delaminations. The study focuses on the physics of Lamb wave propagation and interaction with delaminations at various through-thickness locations and positions. Three-dimensional finite element simulations are used to study, in detail, the changes in wave features such as mode velocity, wavelength and wave refraction in the delamination region. These wave features provide information on the location, position and orientation of the delamination. These studies are validated by experimental measurements. The influence of position of source and delamination on wave refraction in the delamination region is examined. This method also correlates the results obtained from experiments and finite element simulations to theoretical dispersion curves in order to distinctly determine the delamination location.
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Ueda, Masahito, and Akira Todoroki. "Asymmetrical Dual Charge EPCM for Delamination Monitoring of CFRP Laminate." Key Engineering Materials 321-323 (October 2006): 1309–15. http://dx.doi.org/10.4028/www.scientific.net/kem.321-323.1309.

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CFRP laminate is sensitive to impacts. Even a low impact creates delamination, bringing deterioration of the structural reliability. Monitoring for delamination is, therefore, indispensable to maintain the reliability of a CFRP structure. In this study, asymmetrical dual charge electric potential change method was introduced to estimate a delamination in the CFRP laminate. Delaminations were estimated using response surfaces as solver of the inverse problem. Learning data of response surfaces were calculated by FEM analyses. Actual delaminations in the CFRP laminate were successfully identified.
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Ellison, Andrew, and Hyonny Kim. "Shadowed delamination area estimation in ultrasonic C-scans of impacted composites validated by X-ray CT." Journal of Composite Materials 54, no. 4 (July 27, 2019): 549–61. http://dx.doi.org/10.1177/0021998319865311.

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Although ultrasonic pulse-echo C-scanning is a mature non-destructive evaluation technique for imaging internal damage in composite structures, a major impediment of obtaining a full characterization of the internal damage state is delamination shadowing effects. Specifically, shadowing refers to regions of interest that are behind other delamination planes or discontinuities with respect to the scanning surface. The delamination planes block ultrasonic wave transmission and the regions of interest are thus hidden (i.e. shadowed) from the scan. A methodology has been developed to expand ultrasonic scan data of impacted composites by utilizing damage morphology information that is well established in the composite impact research community, such as matrix cracks bounding delaminations, to estimate shadowed delamination information and matrix cracking. First, impacted flat composite plates were C-scanned by pulse-echo ultrasonic and the results were segmented by depth of damage to establish interface-by-interface delamination information. These delaminations were then fit by bounding lines representing the fiber/matrix crack directions defined by the orientations of plies adjacent to each interface to estimate the shadowed portion of the delamination results. The area inside this boundary was added to the original ultrasonic delamination area to create an estimation of the full delamination state at each shadowed interface. Additionally, because this extension method is based on the interactions between delaminations and matrix cracking, this extension method provides an approximation of the matrix cracking of adjacent plies. Results were compared with X-ray computed tomography scans to assess the effectiveness of the extension method.
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Zhang, Zhi Fang, Krishna Shankar, Murat Tahtali, and Evgeny V. Morozov. "Graphical Detection Method for Delaminations." Applied Mechanics and Materials 66-68 (July 2011): 1410–15. http://dx.doi.org/10.4028/www.scientific.net/amm.66-68.1410.

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In this paper, a simple graphical method for the detection of delaminations in damaged composite laminates is introduced. By using this method, both delamination size and location can be predicted accurately. First, a frequency database for the damaged beams with a range of delamination sizes and locations is generated using a Finite Element (FE) model; then for each mode, a surface plot relating the delamination size, location and frequency shift is generated. The next step is to look up the actual frequency shift (either from numerical simulation or experiment) from surface plots relating to three or more modes to get the intersection curves, which show the possible combination of delamination size and location for each mode. Finally the intersection curves of different modes are plotted together and the intersection point of all the curves indicates the possible delamination size and location, where the frequency shifts for all the modes can be matched. We demonstrate that this method is able to predict both delamination size and location fairly accurately. This method can be expanded to detect the propagation of delaminations by only monitoring the shifts in natural frequencies. It has the potential to detect multiple delaminations through continuous monitoring, provided that they do not occur simultaneously. This method has promising applications in the Structure Health Monitoring (SHM) of composite structures.
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Hwang, Shun Fa, and Horng Ming Chen. "Compression Tests of Unidirectional Composite Laminates with Two Delaminations." Key Engineering Materials 306-308 (March 2006): 381–86. http://dx.doi.org/10.4028/www.scientific.net/kem.306-308.381.

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Compression tests are conducted on composite laminates consisting of 16 unidirectional carbon/epoxy layers with two through-width delaminations. Two types of delamination length and location are considered. One is that a short delamination is located at the middle surface along the thickness direction and a long delamination is positioned between the second layer and the third layer. The other is that a long delamination is located at the middle surface and the position of the short elamination is between the second layer and the third layer. The results indicate that if the long delamination is close to the surface of the laminate, the inner, short delamination has no effect on the critical buckling stresses. However, the presence of inner, short delamination may significantly change the critical delamination growth stresses. If the short delamination is above the long delamination that is located on the middle surface, the presence of the short delamination may significantly reduce the critical buckling stresses. But its effects on the critical delamination growth stresses are minor.
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Bhat, Sunil, and S. Narayanan. "Numerical investigations on delaminated Glare under uni-axial tension." International Journal of Structural Integrity 7, no. 4 (August 8, 2016): 553–70. http://dx.doi.org/10.1108/ijsi-07-2015-0021.

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Purpose – Since failure of laminated composites by delaminations is common, the purpose of this paper is to present a numerical procedure to check the stability of delaminations in fiber metal laminate (Glare), with different possible damage configurations, under uni-axial tension. Deformation behavior of the laminate is also examined. Influence of the type and the extent of damage, represented by varying sizes and number of delaminations, on delamination driving force and laminate deformation is found. Design/methodology/approach – Delaminated Glare is modeled by finite element method. Interface cohesive elements are used to model the delaminations. Finite element results provide the deflection/deformation characteristics of the laminate. Driving forces of delaminations are estimated by J integrals that are numerically obtained over cyclic paths near delamination tips. Laminates with different types of delaminations are also fabricated and externally delaminated for measurement of their interlaminar fracture toughness. The delamination is considered to be stable if its driving force is less than corresponding interlaminar fracture toughness of the laminate. Findings – Delaminations are found to be stable in laminates with lower number of delaminations and unstable in laminates with higher number of delaminations. Increase in size of delaminations increases the deformations but reduces the delamination driving force whereas increase in number of delaminations increases both deformations and driving forces. The trends change in case of laminates with symmetrical damage. Shape of delamination is also found to influence the deformations and driving forces. The finite element model is validated. Research limitations/implications – There is scope for validating the numerical results reported in the paper by theoretical models. Practical implications – Checking the stability of delaminations and their effect on deformation behavior of the laminate helps is assessment of safety and remaining life of the laminate. If failure is predicted, preemptive action is taken by using repair patch ups at identified critical locations in order to avoid failures in service conditions. Originality/value – The paper offers the following benefits: use of cohesive zone method that is readily possible in finite element procedures and is relatively simple, fast and reasonably accurate is demonstrated; suitability of using J integrals over paths crossing non-homogeneous and property mismatched material layers is tested; and influence of the type and the extent of damage in the laminate on its deformation behavior and delamination driving forces is found. This type of work has not been reported so far.
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Kardomateas, G. A. "The Initial Post-buckling and Growth Behavior of Internal Delaminations in Composite Plates." Journal of Applied Mechanics 60, no. 4 (December 1, 1993): 903–10. http://dx.doi.org/10.1115/1.2901000.

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The initial post-buckling and growth behavior of delaminations in plates is studied by a perturbation procedure. In this work, no restrictive assumptions regarding the delamination thickness and plate length are made, i.e., the usual thin film assumptions are relaxed. The perturbation procedure is based on an asymptotic expansion of the load and deformation quantities in terms of the distortion parameter of the delaminated layer, the latter being considered a compressive elastica. Closed-form solutions for the load and midpoint delamination deflection versus applied compressive displacement during the initial post-buckling phase are derived. Moreover, closed-form expressions for the energy release rate and the mixity ratio (i.e., Mode II versus Mode I) at the delamination tip are produced. A higher Mode I component is found to be present during the initial post-buckling phase for delaminations of increasing ratio of delamination thickness over plate thickness, h/T (i.e., delaminations further away from the surface). Moreover, the-energy release rate corresponding to the same applied strain is larger for a higher h/T ratio. The reduced growth resistance of these configurations is verified by experimental results on unidirectional composite specimens with internal delaminations.
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Xing, Shutao, Marvin W. Halling, and Paul J. Barr. "Delamination Detection of Reinforced Concrete Decks Using Modal Identification." Journal of Sensors 2012 (2012): 1–17. http://dx.doi.org/10.1155/2012/156583.

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This study addressed delamination detection of concrete slabs by analyzing global dynamic responses of structures. Both numerical and experimental studies are presented. In the numerical examples, delaminations with different sizes and locations were introduced into a concrete slab; the effects of presence, sizes, and locations of delaminations on the modal frequencies and mode shapes of the concrete slab under various support conditions were studied. In the experimental study, four concrete deck specimens with different delamination sizes were constructed, and experimental tests were conducted. Traditional peak-picking, frequency domain decomposition, and stochastic subspace identification methods were applied to the modal identification from dynamic response measurements. The modal parameters identified by these three methods correlated well. The changes in modal frequencies, damping ratios, and mode shapes that were extracted from the dynamic measurements were investigated and correlated to the actual delaminations and can indicate presence and severity of delamination. Finite element (FE) models of reinforced concrete decks with different delamination sizes and locations were established. The modal parameters computed from the FE models were compared to those obtained from the laboratory specimens, and the FE models were validated. The delamination detection approach was proved to be effective for concrete decks on beams.
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Ding, Wenxiang, Maxime Bavencoffe, and Marc Lethiecq. "Modeling and Experimental Characterization of Bonding Delaminations in Single-Element Ultrasonic Transducer." Materials 14, no. 9 (April 27, 2021): 2269. http://dx.doi.org/10.3390/ma14092269.

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Ultrasonic transducers performance can be seriously deteriorated by loss of adhesion between some constitutive elements such as the active element, the backing, or the matching layer. In the present work, the influence of bonding delaminations on the performance of a single-element ultrasonic transducer, which is composed of a piezoelectric disk, a backing, and a matching layer, is studied numerically and experimentally. Based on the positions between layers, two cases, i.e., delaminations between ceramic and backing or between ceramic and matching layer, are considered. Each case involves three different types of delaminations, which are marked as delamination type (DT)-I, II, and III. DT-I, a circular shape delamination, starts from the center and expands towards the peripheric zone; DT-II, an annular shape delamination, starts from the peripheric zone and expands towards the center; DT-III is a sector shape delamination with a given angle. The numerical simulations are performed by the finite element method and the influence of delaminations on the electromechanical admittance (EMA) of the transducer is investigated. 3D printed backings and matching layers are mounted on a PZT sample to assemble delaminated single-element transducers. An impedance analyzer is used for experimental measurements. Comparison between numerical and experimental results shows a reasonable agreement making changes in EMA an interesting indicator to inform about the occurrence and severity of delaminations in a single-element ultrasonic transducer.
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Dissertations / Theses on the topic "Delamination"

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Whitcomb, J. D. "Instability-related delamination growth of embedded and edge delaminations." Diss., Virginia Polytechnic Institute and State University, 1988. http://hdl.handle.net/10919/77755.

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Compressive loads can cause local buckling in composite laminates that have a near-surface delamination. This buckling causes load redistribution and secondary loads, which in turn cause interlaminer stresses and delamination growth. The goal of this research effort was to enhance the understanding of this instability-related delamination growth in laminates containing either an embedded or an edge delamination. There were three primary tasks: 1) development of a geometrically nonlinear finite element analysis named NONLIN3D; 2) performance of a parametric analytical study to determine the effects of strain, delamination shape, and delamination size on the distribution of the strain energy release rate components along the delamination front; and 3) performance of a combined experimental and analytical study of instability-related delamination growth (IRDG). Two material systems (AS4/PEEK and IM7/8551-7) and two stacking sequences (0/90/90/0)₆ and (90/0/0/90)₆ were examined. The laminates were fabricated with Kapton inserts between the fourth and fifth plies from the top surface to give an initial delamination. The analysis predicted a large variation of GI and GII along the delamination front. The GIII component was always small. The location of maximum GI and GII depended on the delamination shape and applied strain. In general, the strain-energy release rates were small except in a small region. Hence, delamination growth was expected to occur over only a small portion of the delamination front. Experiments corroborated this prediction. The laminate stacking sequence had a large effect on the shape of the deformed region, the direction of delamination growth, and the strain at which delamination growth occurred. These effects were predicted by the analysis. The GI component appeared to govern initial delamination growth in the IM7/8551-7 laminates. Matrix ply cracking generally accompanied delamination growth. In some cases fiber micro-buckling also occurred shortly after delamination growth occurred.
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Ding, Wei. "Delamination analysis of composite laminates." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape8/PQDD_0001/NQ41141.pdf.

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Wright, Jennifer Edith. "Compound bifurcations in delamination buckling." Thesis, University of Bath, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.432375.

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Batel, Mehdi. "Acoustic determination of adhesive bond delamination." Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/18201.

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Pernice, Maria Francesca. "On delamination migration in composite laminates." Thesis, University of Bristol, 2016. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.702469.

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Carbon fibre/epoxy composite laminates are well known to be susceptible to delamination. Delamination usually grows at interfaces between plies with dissimilar fibre orientation and may migrate from one interface to another, as in low-velocity impact damage or skin-stringer debonding. Much of the modelling work in the literature focuses on delamination contained within a single ply interface, using data from characterization tests in which delamination grows at interfaces between plies of the same fibre orientation, mainly because of a lack of understanding of the fundamental causes of delamination migration. However, to obtain representative results, delamination migration should be accounted for by finite element methods aimed at accurately simulating delamination growth. The objective of this work was to investigate and understand delamination migration at interfaces between plies with dissimilar fibre orientation in composite laminates. Initially, delamination migration was observed experimentally in a Double Cantilever Beam (DCB) specimen containing ±θ ply interfaces. Finite element analyses of the DCB specimen were then performed, to simulate delamination migration using a cohesive zone model-based approach. Comparison of experimental and numerical results highlighted the need for a more detailed experimental understanding of the fundamental driving forces for delamination migration, before methods to simulate delamination migration could be developed and validated. To this end, further experimental tests were conducted, using the Delamination Migration test method, recently developed at NASA Langley Research Center, which allows the isolation of a single migration event that can then be studied in detail. A novel delamination migration specimen was employed, to investigate delamination migration at a generic 0/θ° interface. Tests were performed in the laboratories of the Durability, Damage Tolerance and Reliability Branch at NASA Langley Research Center. Damage was characterised in detail using C-scan and X-ray Computed Tomography techniques. During the test, delamination initially propagated along a 0°/θ ply interface, by growing closer to one of the bounding plies, turning into it and subsequently arresting. Eventually, delamination migrated to a different 0/θ° ply interface. Linear elastic finite element analyses and the Virtual Crack Closure Technique were employed to interpret experimental results. Results suggested that delamination migration is governed by the shear stress sign and the strain energy release rate along the delamination front, which both vary across the specimen width at a 0/θ° ply interface. Results of this study represent a step forward in the understanding of the key mechanism of delamination propagation and migration at ply interfaces with dissimilar fibre orientation, and help in the understanding of complex damage patterns such as low-velocity impact. Understanding delamination migration can inform design of damage tolerant composite structures and provide guidelines and benchmark data to develop and validate modelling methods aimed at simulating and predicting delamination migration.
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Chong, Iok Tong. "Steam driven delamination in electronics packages /." View Abstract or Full-Text, 2002. http://library.ust.hk/cgi/db/thesis.pl?MECH%202002%20CHONG.

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Dinc, Dincer. "Delamination Of Layered Materials Under Impact Loading." Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/1060623/index.pdf.

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In this study, a cold worked tool steel and a low carbon steel ( St 37 ), which were joined by brazing, were subjected to impact and shear loading. The end product is used as paper cutting blades in the industry. Effects of different brazing filler metals on the delamination of the blades under impact loading and on the impact toughness of the blades were studied. The target is to achieve higher impact toughness values without delamination. Impact toughness of the steels, joined by Cu, CuNi and BNi brazing filler metals and separation of brazed surfaces under shear loading were studied. The microstructures that were formed as a result of each application were studied by scanning electron microscopy and x-ray diffraction. The results indicate that brittle intermetallic compounds are formed in BNi brazing filler metal application. It is observed that CuNi alloy with 24% wt Ni form stronger bonds with the base metals than pure Cu and 10% wt Ni CuNi alloy.
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Olsson, Robin. "Impact response and delamination of composite plates /." Stockholm, 1998. http://www.lib.kth.se/abs98/olss0528.pdf.

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Dávila, Carlos G. "Delamination initiation in postbuckled dropped-ply laminates /." This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-07282008-134842/.

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Brewer, John C. (John Charles) 1961. "Failure of graphite/epoxy induced by delamination." Thesis, Massachusetts Institute of Technology, 1988. http://hdl.handle.net/1721.1/35945.

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Books on the topic "Delamination"

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Center, Langley Research, ed. Instability-related delamination growth of embedded and edge delaminations. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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Center, Langley Research, ed. Instability-related delamination growth of embedded and edge delaminations. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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Center, Langley Research, ed. Instability-related delamination growth of embedded and edge delaminations. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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Whitcomb, John David. Instability-related delamination growth of embedded and edge delaminations. Blacksburg, Va: Virginia Polytechnic Institute and State University, 1988.

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Adams, Donald Frederick. Delamination micromechanics analysis. Laramie, Wyo: University of Wyoming, 1985.

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Center, Langley Research, ed. Fractography of composite delamination. Salt Lake City, Utah: University of Utah, 1990.

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1954-, Newaz Golam M., ed. Delamination in advanced composites. Lancaster, Pa., U.S.A: Technomic Pub. Co., 1991.

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M, Newaz Golam, ed. Delamination in advanced composites. Lancaster, Pa: Technomic Pub. Co, 1991.

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Institute of Materials, Minerals, and Mining, ed. Delamination behaviour of composites. Cambridge, England: Woodhead, 2008.

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University of Utah. Dept. of Materials Science and Engineering. and Langley Research Center, eds. Fractography of composite delamination: Final report. Salt Lake City, Utah: University of Utah, Materials Science and Engingeering Dept., 1989.

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Book chapters on the topic "Delamination"

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Gooch, Jan W. "Delamination." In Encyclopedic Dictionary of Polymers, 200. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-6247-8_3400.

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Kerkstra, Randy, and Steve Brammer. "Delamination." In Injection Molding Advanced Troubleshooting Guide, 233–38. München: Carl Hanser Verlag GmbH & Co. KG, 2018. http://dx.doi.org/10.3139/9781569906460.025.

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Kerkstra, Randy, and Steve Brammer. "Delamination." In Injection Molding Advanced Troubleshooting Guide, 241–46. 2nd ed. München: Carl Hanser Verlag GmbH & Co. KG, 2021. http://dx.doi.org/10.3139/9781569908358.025.

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Kerkstra, Randy, and Steve Brammer. "Delamination." In Injection Molding Advanced Troubleshooting Guide, 241–46. München, Germany: Carl Hanser Verlag GmbH & Co. KG, 2021. http://dx.doi.org/10.1007/978-1-56990-835-8_25.

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Jacob, J. W., G. Mertens, and J. Declerk. "Mirror Delamination." In The IEA/SSPS Solar Thermal Power Plants — Facts and Figures— Final Report of the International Test and Evaluation Team (ITET), 112–13. Berlin, Heidelberg: Springer Berlin Heidelberg, 1986. http://dx.doi.org/10.1007/978-3-642-82684-9_49.

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Baylakoglu, I., and E. Hedin. "PCB Delamination." In The ELFNET Book on Failure Mechanisms, Testing Methods, and Quality Issues of Lead-Free Solder Interconnects, 275–82. London: Springer London, 2011. http://dx.doi.org/10.1007/978-0-85729-236-0_12.

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Liechti, Kenneth M. "Delamination Mechanics." In Springer Handbook of Experimental Solid Mechanics, 961–84. Boston, MA: Springer US, 2008. http://dx.doi.org/10.1007/978-0-387-30877-7_34.

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Kachanov, L. M. "Delamination Buckling." In Mechanics of Elastic Stability, 19–56. Dordrecht: Springer Netherlands, 1988. http://dx.doi.org/10.1007/978-94-009-2819-0_2.

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Kachanov, L. M. "Delamination Growth." In Mechanics of Elastic Stability, 57–87. Dordrecht: Springer Netherlands, 1988. http://dx.doi.org/10.1007/978-94-009-2819-0_3.

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Point, Nelly, and Elio Sacco. "A Delamination Model." In Novel Approaches in Civil Engineering, 175. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-540-45287-4_12.

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Conference papers on the topic "Delamination"

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Li, S. X., K. Lee, J. Hulog, R. Gannamani, and S. Yin. "Signature Analysis of Package Delamination Using Scanning Acoustic Microscope." In ISTFA 1996. ASM International, 1996. http://dx.doi.org/10.31399/asm.cp.istfa1996p0287.

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Abstract Package delaminations are often associated with electrical and package reliability problems in IC devices. Delaminations caused by electrical-over-stress (EOS) and moisture expansion during reflow soldering have shown different delamination patterns. A Scanning Acoustic Microscope (SAM) can be used to detect package delaminations. Understanding these delamination signatures can help us quickly identify the failure cause at an early stage of the failure analysis.
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Chen, Deliang, Changping Chen, Yiming Fu, and Liming Dai. "Growth of Delamination for Laminates Circular Plates Subjected to Transverse Loads." In ASME 2009 International Mechanical Engineering Congress and Exposition. ASMEDC, 2009. http://dx.doi.org/10.1115/imece2009-10687.

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By using movable boundary variational principle, a set of nonlinear governing equations for the delaminated circular plate including the transverse shear deformation and contact effect between the delaminations subjected to transverse load are derived and the corresponding boundary and matching conditions are given. At the same time, according to the Griffith criterion, the formulas of total energy release rate and its individual mode components along the delamination front are obtained and the delamination growth is studied. In the numerical calculation, the delamination growth of axisymmetrical laminated circular plates with various delamination radiuses, delamination depths, and the different material properties are discussed.
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Dauda, Benjamin, S. Olutunde Oyadiji, and Prasad Potluri. "Dynamic Properties of Delaminated Braided Textile Composite Beams." In ASME 2008 9th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2008. http://dx.doi.org/10.1115/esda2008-59462.

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In this paper, vibration analysis of through-width single- and multi-delaminated cantilevered composite beams is carried out using Finite Element Analysis (FEA) approach. Different configurations of multiple delaminations are considered. The FEA results for single delaminations are validated via experimental testing. It is found that changes in the natural frequencies of delaminated cantilevered beams are related to the number, type and distributions of delaminations within a beam. Also, the natural frequency shifts due to single or multiple delaminations are influenced by the thickness-wise locations of the delaminations. As the delamination is moved from the outermost inter-laminar layer towards the mid-plane of the beam, the natural frequency decreases and reaches a minimum value when the delamination is located at the midplane. Single delaminations have a more significant effect on natural frequencies than multiple delaminations of the same overall dimension as the single delamination. Furthermore, it is found that there is a greater reduction in natural frequency when multiple delaminations are close together than when they are spread out. However, where the locations of multiple delaminations coincide with nodal or antinodal vibration points, the effect is significantly altered.
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4

Mendioroz, A., D. Sagarduy-Marcos, J. Pérez-Arbulu, J. Rodríguez-Aseguinolaza, R. Celorrio, J. C. Batsale, and A. Salazar. "Sizing the geometrical parameters of semi-infinite delaminations using optically excited lock-in infrared thermography." In 4th Asian Quantitative InfraRed Thermography Conference. QIRT Council, 2023. http://dx.doi.org/10.21611/qirt.2023.06.

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The aim of this work is to characterize the geometrical parameters of a 2D delamination: length, depth and thickness. First, we calculate analytically and numerically the surface temperature oscillation of a sample, containing a semi-infinite delamination, as the material is homogeneously illuminated by a modulated light beam. Then, we perform an inverse parametric estimation of synthetic temperature amplitude and phase data to size the geometrical parameters of the delamination. Finally, we present lock-in infrared thermography experiments performed on AISI-304 stainless steel samples containing calibrated delaminations. We fit the numerical model to the experiments to retrieve the delamination parameters successfully.
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5

Pelegri, Assimina A., and Charles Valentine. "Experimental Investigation of Compressive Overloads on Delamination Growth Behavior in Fatigued Composites." In ASME 1999 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/imece1999-0504.

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Abstract The behavior of laminated graphite/epoxy composites under variable amplitude compressive loading is studied. Laminate composites in aerospace applications undergo both compressive and tensile fatigue stresses as well as spectrum loading. These materials are particularly susceptible to compressive loads and overloads, which cause the growth of any small pre-existing delaminations. Such delamination growth, and the resulting sublaminate buckling, are major causes of fatigue failure. This experimental program investigates the effects of overloads on laminate composite specimens in which small delaminations are introduced during fabrication. The delamination growth is monitored in real time during fatigue tests. Different variable amplitude load spectra are applied, and the delamination position through the depth of the specimens is varied. Up to now, research has focused on constant amplitude fatigue testing or simple two block testing. Some variable amplitude studies have been done but attention has mostly been given to the reduction in residual strength or stiffness of the specimen. Much of the prior work is done in tension instead of compression. This investigation will provide data specifically on the growth behavior of pre-existing delaminations in composites under compressive overloads.
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Leigh, Tim, and Azam Tafreshi. "Delamination Buckling of Composite Cylindrical Panels Under Axial Compressive Load." In ASME 7th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2004. http://dx.doi.org/10.1115/esda2004-58578.

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Composite cylindrical shells and panels are widely used in aerospace structures. Delaminations within the composite structure reduce the compressive strength of laminates, and often result because of damage incurred during manufacturing and in-service use. This paper investigates the buckling behaviour of laminated cylindrical panels loaded in axial compression using the finite element method. The use of three-dimensional finite elements for predicting the delamination buckling of these structures is computationally expensive. Here the analysis has been carried out using a layerwise shell finite element based on the first-order, shear deformation theory. Contact elements were placed between the delaminated regions to avoid physical interpenetration of the elements. It is shown that through-the-thickness delamination can be modelled and analysed effectively without requiring a great deal of computing time and memory. Delamination shapes considered in this study were square and rectangular — extended longitudinally over the entire length or extended along the entire circumference of the panel. Some of the results were compared with the corresponding analytical results which were in good agreement. The most influential parameters for a given laminated panel were the size of the delamination and its through-the-thickness position. The effect of the curvature on the global buckling strength of a delaminated panel was also studied. Depending on the size and through the thickness position of delaminations, three different modes of buckling behaviour occur. The local mode occurs when the delamination is near the free surface of the laminate and the area of the delamination is large. The global mode occurs when the delamination is deeper within the laminate and has a small area. The mixed mode is a combination of global and local modes.
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MASSEY, JUSTIN, BARRETT ROMASKO, and HYONNY KIM. "NOVEL ENCLOSED DELAMINATION INJECTION REPAIR PROCESS FOR STRENGTH RESTORATION." In Proceedings for the American Society for Composites-Thirty Seventh Technical Conference. Destech Publications, Inc., 2022. http://dx.doi.org/10.12783/asc37/36491.

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Delaminations are a common damage mechanism that occurs on composite structures due to in-service impacts. Enclosed damages less than 50 mm in diameter are of particular interest for repair. Current practices for repair of delaminations include: cut out of the damage and applying a patch or doubler to the cutout site, or injection using a repair resin. The use of a bonded doubler repair is more invasive and requires a cutout that acts as a stress concentration in the area of the repair. Injection repairs have traditionally been a faster, less expensive way to repair composite delaminations. However, the aerospace industry has not accepted injection repair as a strength restorative process. Questions about quantifying delamination internal contamination and ensuring percentage of repair resin fill within a delamination have been primary reasons why injection repairs have not been credited with strength restoration. Development of a new quantitative internal surface cleaning, preparation and repair process for delaminated composite materials is required to provide justification for strength restoration using injection repair. Fabricating representative local delaminations was performed with a modified end-notch flexure (ENF) test. A unidirectional 24-ply panel was fabricated to simulate damage to laminates. Intentional contamination was introduced into the induced delamination of each panel type. Contamination removal and surface preparation using solvent and atmospheric plasma cleaning were completed on the modified ENF coupon and verified utilizing in-line monitoring with Quantitative Gas Analysis (QGA) and post processing inspection with Fourier Transform Infrared Spectroscopy (FTIR). A modified low-viscosity injection resin was developed and utilized to repair the post-tested ENF coupons. The modified epoxy exhibited comparable shear strength characteristics to un-modified neat resin while achieving a >97% reduction in viscosity. Each ENF panel type was assessed for Mode II fracture toughness (GIIc) of the parent material and repair of fractured coupons. Fractured coupons simulating an enclosed delamination were repaired: without contamination, with contamination, and after the novel contamination removal processes were completed. Mode II interlaminar fracture toughness was restored or increased when compared to control test groups for all coupons that were repaired or cleaned and repaired.
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Davies, Peter, and Leif A. Carlsson. "Influence of Delamination on Strength of Externally Pressurized Glass/Epoxy Cylinders." In ASME 1999 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/imece1999-0908.

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Abstract The delamination resistance of filament wound glass/epoxy cylinders has been characterized for a range of winding angles and fracture mode ratios using beam fracture specimens. The results reveal that the fracture resistance increases with increasing winding angle and mode II (shear) fraction (GII/G). It was also found that interlaced fiber bundles in the filament wound cylinder wall acted as effective crack arresters in mode I loading. To examine the sensitivity of delamination damage on the implosion behavior of cylinders, external pressure tests were performed on filament-wound glass/epoxy composite cylinders with artificial defects and impact damage. The results revealed that the cylinder strength was insensitive to the presence of single delaminations but impact damage caused reductions in failure pressure. The insensitivity of the failure pressure to a single delamination is attributed to the absence of buckling of the delaminated sublaminates before the cylinder wall collapsed. The impacted cylinders contained multiple delaminations, which caused local reduction in the compressive load capability and reduction in failure pressure.
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Dauda, Benjamin, S. Olutunde Oyadiji, and Prassad Potluri. "Finite Element Determination of Beam Surface Stresses Due to Multiple Delamination." In ASME 2009 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2009. http://dx.doi.org/10.1115/detc2009-87442.

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The finite element method is used to analyse the through-the-width stress distribution characteristics of single and multiple delaminated cantilevered composite beams. Single delaminations of fixed length, which are located at different through-the-thickness locations, and multiple delaminations of sequential and diagonal configurations are investigated. The total length of multiple delaminations in a beam was made equal to the fixed length of a single delamination. The results show that the configurations and spatial distributions of multiple delaminations have significant effects on the magnitude of the maximum stresses induced in the beams. Beams in which most of the delaminations are concentrated around the mid-plane of the beam show higher stresses than beams in which most of the delaminations are concentrated close to the surface of the laminate. However, delaminations close to the surfaces of the beams exhibit higher stresses at the tips of the delaminations.
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Todoroki, Akira, Miho Tanaka, and Yoshinobu Shimamura. "Improved Electric Resistance Change Method for Delamination Monitoring of Graphite/Epoxy Composite Laminates." In ASME 2002 International Mechanical Engineering Congress and Exposition. ASMEDC, 2002. http://dx.doi.org/10.1115/imece2002-33491.

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Laminated composite plates have low delamination resistance. Since delamination crack creation is a difficult problem for visual inspection, delamination causes low reliability for primary structure of laminated composites. To improve this low reliability, identifications of delamination cracks in-service are required. The present study employs an electric-resistance change method in an attempt to identify internal delaminations experimentally. In our previous paper, a two-prove method was adopted for the electric resistance change measurements because of the simplicity. Instead, the present paper adopts multiple-prove method for the measurements of electric resistance changes. Electric current is charged from the different electrodes to measure the voltage changes. The measurements of electric voltage change at multiple points are robust against electric resistance change at the electrodes, and the method is similar to the four-probe method for high precision measurements of electric resistance change. In the present study, high precise measurement system of electric voltage change is developed, and the electric voltage measurement method is adopted for identifications of embedded delamination location and size. As a result, the improved electric resistance change method is shown to be effective for the identifications of embedded delamination cracks of graphite/epoxy laminated composites.
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Reports on the topic "Delamination"

1

Bradley, Walter L. Delamination Fracture in Graphite/Epoxy Materials. Fort Belvoir, VA: Defense Technical Information Center, June 1986. http://dx.doi.org/10.21236/ada173255.

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2

Kay, G. Simulations of carbon fiber composite delamination tests. Office of Scientific and Technical Information (OSTI), October 2007. http://dx.doi.org/10.2172/923091.

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Saigal, S., S. Muralidhar, A. Jagota, and S. J. Bennison. Cohesive Formulations for Delamination in Polymer Layered Composites. Fort Belvoir, VA: Defense Technical Information Center, May 2000. http://dx.doi.org/10.21236/ada378866.

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4

Mandell, John F., and William J. Tsai. Effects of Porosity on Delamination of Resin-Matrix Composites. Fort Belvoir, VA: Defense Technical Information Center, April 1990. http://dx.doi.org/10.21236/ada258817.

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Chen, Hsin-Piao, and Aditi Chattopadhyay. Characterization and Detection of Delamination in Smart Composite Structures. Fort Belvoir, VA: Defense Technical Information Center, December 2006. http://dx.doi.org/10.21236/ada470797.

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6

Sandhu, R. S., W. E. Wolfe, R. L. Sierakowski, C. C. Chang, and H. R. Chu. Finite Element Analysis of Free-Edge Delamination in Laminated Composite Specimens. Fort Belvoir, VA: Defense Technical Information Center, June 1991. http://dx.doi.org/10.21236/ada251659.

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Cox, Brian, Christian Lundsgaard-Larsen, and Roberta Massabo. Test and Material Specifications for Dynamic Delamination Studies of Z-Pinned Laminates. Fort Belvoir, VA: Defense Technical Information Center, August 2007. http://dx.doi.org/10.21236/ada482267.

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Larsen, Ross E., Xin He, and Robert Tirawat. The Effect of Aging on the Delamination Fracture Energy of Glass Solar Reflectors. Office of Scientific and Technical Information (OSTI), September 2018. http://dx.doi.org/10.2172/1472245.

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Bocchieri, Robert T., Douglas S. Dierdorf, Kristofor S. Cozart, Steven P. Wells, Steven W. Kirkpatrick, Robert A. MacNeill, and John R. Hawk. Experimental Investigation of Widespread Delamination Damage to Composite Materials Caused by Radiant Heating. Fort Belvoir, VA: Defense Technical Information Center, June 2013. http://dx.doi.org/10.21236/ad1009242.

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10

Sheets, Colton, and Brent Vyvial. PR-201-164502-R01 Study to Evaluate Delamination and Disbonding of Composite Repairs. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), July 2018. http://dx.doi.org/10.55274/r0011500.

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Composite reinforcement systems have seen extensive use in the pipeline industry over the last two decades as solutions to address a range of pipeline integrity threats. Despite their widespread use, few options exist for reliable inspection of installed composite reinforcement systems. Additionally, there is a lack of well-defined criteria for acceptable flaw types and sizes when found during inspection of the composite repairs. The purpose of this study was to provide information regarding the current state of available composite inspection techniques as well as the impact of delamination and disbondment defects on the performance of composite repairs. The results of the work will provide operators with guidance on using inspection technologies to assess the integrity of installed composite repair systems. This report has a related webinar.
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