Bibliographies thématiques / Delamination mechanism

Littérature scientifique sur le sujet « Delamination mechanism »

Auteur : Grafiati
Publié le 14 mars 2023

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Articles de revues sur le sujet "Delamination mechanism"

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Hosseini-Toudeshky, Hossein, M. Saeed Goodarzi et Bijan Mohammadi. « Multiple Delaminations Growth in Composite Laminates under Compressive Cyclic Loading in Post-Buckling ». Applied Mechanics and Materials 225 (novembre 2012) : 195–200. http://dx.doi.org/10.4028/www.scientific.net/amm.225.195.

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Due to discontinuity of mechanical properties in composite laminates, failure occurs in different damage mechanisms. Delamination growth of adjacent layers is a major failure mechanism in laminates with various layup configurations. Pre existing delamination may initiate in composite laminate before use, due to impact in assembly and fabrication process. Cyclic compressive loading may cause delamination growth due to both post-bucking behavior and fatigue nature of loading. In this paper, a 3D mixed-mode interface element model has been developed to simulate the growth of multiple delaminations under compressive cyclic loading. For this purpose, the presented model should be able to handle the geometry nonlinearity of post-buckling and material nonlinearity of cohesive zone constitutive law under cyclic loading at interfaces. Because of mixed-mode condition of stress field at the delamination-front of post-buckled laminates, a mixed-mode bilinear constitutive law has been used as user material in this model. Paris Law has been used to relate the energy release rate to the fatigue crack growth in cohesive zone. A composite laminate with pre-existing delamination under buckling load, available from the literature has been reproduced with the present approach. Finally, laminates containing multiple delaminations in various interface layers have been analyzed under compressive fatigue loading. It is shown that the pre-existing delamination with more depth from the surface of laminate causes more initial static and fatigue delamination growth rate.
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Dong, Hui Ru, Wanlin Guo et Zheng Yang. « Mechanism of Delamination and Its Effects on Fracture of Surface Crack Bodies in Ductile Pipeline Steel ». Key Engineering Materials 297-300 (novembre 2005) : 1235–40. http://dx.doi.org/10.4028/www.scientific.net/kem.297-300.1235.

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The effects of three-dimensional crack configurations and delaminations on fracture mechanism and fracture toughness Jc of pipeline steel were investigated experimentally by use of tensile specimens having surface cracks of different depth to length ratio. Comparison with test results of through-thickness cracks and mechanism analyses are made as well. When 3D stress constraint is larger than the strength in the thickness direction the delamination forms. As no delamination occurs in the interior of a surface crack, the constraint is higher and the fracture toughness is lower than that of the through-thickness cracks. Therefore, the nominal fracture toughness obtained from through-thickness cracked specimens is not a real material constancy, and not suitable for safety assessment of pipelines.
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Brenneman, Jacob, Derya Z. Tansel, Gary K. Fedder et Rahul Panat. « Interfacial delamination and delamination mechanism maps for 3D printed flexible electrical interconnects ». Extreme Mechanics Letters 43 (février 2021) : 101199. http://dx.doi.org/10.1016/j.eml.2021.101199.

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Wei, Z., L. H. Yam et L. Cheng. « Delamination Assessment of Multilayer Composite Plates Using Model-based Neural Networks ». Journal of Vibration and Control 11, no 5 (mai 2005) : 607–25. http://dx.doi.org/10.1177/1077546305052317.

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A procedure for damage detection in multilayer composites is described using model-based neural networks and vibration response measurement. The appropriate finite element model is established to generate the training data of neural networks. Internal delaminations with different sizes and locations are considered as the particular damage scenarios in multilayer composite plates. The damage-induced energy variation of response signal is investigated, and the mechanism of mode-dependent energy dissipation of composite plates due to delamination is revealed. In order to obtain the structural dynamic response of the samples, impulse forced vibration testing is conducted using a piezoelectric patch actuator and an accelerometer. To enhance the sensitivity of damage features in the vibrating plate, the damage-induced energy variation of the response signal decomposed by wavelet packets is used as the input data of backward propagation neural networks for the prediction of delamination size and location. The test results show that the proposed method is effective for the assessment of delamination status in composites.
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Jeevan Kumar, N. « Analysis of Mode-I crack growth arresting mechanism in curved laminated joint ». International Journal of Computational Materials Science and Engineering 08, no 01 (mars 2019) : 1950001. http://dx.doi.org/10.1142/s2047684119500015.

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The critical damage for carbon fiber structures, which are being employed in aircraft structures, is known as delamination/crack. Fasteners are commonly installed to arrest the delamination by clamping the laminate together. Fasteners are installed in each corner of the delaminated zone to provide significant arrest capability, shifting the failure mode away from delamination under most conditions. The Finite Element Analysis (FEA) model is constructed to study the effectiveness of the fastener as crack arrest mechanism. The FEA results show that the fastener provides significant crack retardation capability in Mode-I condition. An analytical model is developed for the delamination embedded between the skin and stiffener interface of the joint. The fasteners are modeled with spring elements. The analysis is solved with Virtual Crack Closure Technique (VCCT) approach. The primary objective of the current research work is to enhance the safety of bonded joint by providing arrest mechanisms.
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Riccio, Aniello, Angela Russo, Andrea Sellitto, Cinzia Toscano, Davide Alfano et Mauro Zarrelli. « Experimental and Numerical Assessment of Fibre Bridging Toughening Effects on the Compressive Behaviour of Delaminated Composite Plates ». Polymers 12, no 3 (3 mars 2020) : 554. http://dx.doi.org/10.3390/polym12030554.

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Increasing the Mode I inter-laminar fracture toughness of composite laminates can contribute to slowing down delamination growth phenomena, which can be considered one of the most critical damage mechanisms in composite structures. Actually, the Mode I interlaminar fracture toughness (GIc) in fibre-reinforced composite materials has been found to considerably increase with the crack length when the fibre bridging phenomenon takes place. Hence, in this paper, the fibre bridging phenomenon has been considered as a natural toughening mechanism able to replace embedded metallic or composite reinforcements, currently used to increase tolerance to inter-laminar damage. An experimental/numerical study on the influence of delamination growth on the compressive behaviour of fibre-reinforced composites characterised by high sensitivity to the fibre bridging phenomenon has been performed. Coupons, made of material systems characterised by a variable toughness related to a high sensitivity to the fibre bridging phenomenon and containing artificial through-the-width delaminations, were subjected to a compressive mechanical test and compared to coupons made of standard material system with constant toughness. Out-of-plane displacements and strains were monitored during the compression test by means of strain gauges and digital image correlation to assess the influence of fibre bridging on delamination buckling, delamination growth and on the global buckling of the specimens, including buckling shape changes. Experimental data were combined with a numerical study, performed by means of a virtual crack closure technique based procedure, named SMart Time XB – Fibre Bridging (SMXB-FB), able to mimic the crack bridging effect on the toughness properties of the material system. The combination of numerical results and experimental data has allowed the deformations and the buckling shape changes to be correlated to the onset and evolution of damage and, hence, contributes to improving the knowledge on the interaction of the failure mechanisms in the investigated composite specimens.
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Djamaluddin, Rudy, Hijriah, Rita Irmawati, Faharuddin et Rossy T. Wahyuningsih. « Delamination mechanism of GFRP sheet bonded on the reinforced concrete beams ». MATEC Web of Conferences 258 (2019) : 03009. http://dx.doi.org/10.1051/matecconf/201925803009.

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Fiber reinforced polymer (FRP) has been developed to be applied for a strengthening of the deteriorated structures. In the form of a sheet, the FRP may be applied for the strengthening of the structures by bonding it to the concrete surface. Glass composed FRP (GFRP) sheet is most commonly used due to its relatively lower cost compared to the other FRP materials. GFRP sheet is applied externally by bonding it on the concrete surface. The strengthened structures should be monitored periodically to ensure the health of the strengthened structures. Regarding the development of monitoring system of the strengthened structure, it is important to study the delamination phenomenon of the bonded GFRP. Therefore the delamination mechanism is important to be clarified. Many studies have been done to investigate the bonding characteristics of GFRP sheet under direct tensile loading. However, the studies on the bonding characteristics of GFRP sheet on the strengthened beams due to flexural loadings are still limited. A series of concrete beams strengthened with GFRP sheet on extreme tension surface were prepared. The beam specimens ware loaded under four-point bending test gradually up to the ultimate capacity. Results indicated that prior to final delamination, a local delamination occurred which was indicated by the suddenly decreasing of an applied load. The delamination of the GFRP sheet may be initiated by the flexural cracks occurred on the beams.
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Wang, Ligang, et Dan G. Zollinger. « Mechanistic Design Framework for Spalling Distress ». Transportation Research Record : Journal of the Transportation Research Board 1730, no 1 (janvier 2000) : 18–24. http://dx.doi.org/10.3141/1730-03.

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Spalling is a distress form in concrete pavements that often manifests as the breakdown of the joint of a slab within 15 cm (6 in.) of the joint or crack and can occur at both longitudinal and transverse joints. Efforts have been under way at Texas A&M University to formulate mechanistic spalling models derived from data gathered in recent Texas Department of Transportation studies related to spall development. Extensive field studies have led to the establishment of a spalling mechanism consisting of a step-by-step process that can be characterized with engineering mechanics. These findings indicate that spalling is the result of damage initiated in the form of a shear delamination that is oriented parallel to and at a shallow depth below the surface of the pavement. Conditions necessary for formation of the delaminations include low interfacial strength between the aggregate and mortar and sufficient evaporation of pore water from the hydrating concrete, resulting in differential drying shrinkage near the pavement surface. Delaminations have been noted to initiate early in the life of the pavement and, once formed, extend later into spalls as a result of incompressibles, freeze-thaw cycles, traffic loading, and other such effects. A design framework for delamination formation and subsequent spalling development is presented in a practical format in which to mechanistically design concrete pavement systems relative to spalling distress.
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Liu, Chang, et Yaolin Shi. « Initiation of Triangle Zones by Delamination, Shear, and Compaction at the Front of Fold-and-Thrust Belts ». Journal of Earthquakes 2016 (16 mars 2016) : 1–21. http://dx.doi.org/10.1155/2016/6302546.

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The interest of this paper is to investigate the initiation of triangle zones at the front of fold-and-thrust belts by analyzing the virtual velocity fields in triangle wedges. It allows achieving five collapse mechanisms by delamination, shear, and compaction of competing for the formation of triangle zones as follows. The first mechanism is the classical Coulomb shear thrust. The second is delamination at the frontal part of the décollement with straight back thrust, while the third is delamination with curvy back thrust. The fourth is the combination of ramp with Coulomb shear and shear-enhanced compact fault, while the fifth is the combination of the exchanging motion on the ramp and thrust. The dominating mechanism in the formation of triangle zones relies on the competition of the least upper bound of each mechanism when subjected to tectonic force. The controlling factors of the competition are discovered as follows: (1) the frictional characters and cohesion of horizontal décollements and thrust, (2) the slope of the topography of accretion wedge, and (3) the thickness and rock density of the front toe of accretion wedge.
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Wakamoto, Keisuke, Takukazu Otsuka, Ken Nakahara et Takahiro Namazu. « Degradation Mechanism of Pressure-Assisted Sintered Silver by Thermal Shock Test ». Energies 14, no 17 (4 septembre 2021) : 5532. http://dx.doi.org/10.3390/en14175532.

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This paper investigates the degradation mechanism of pressure-sintered silver (s-Ag) film for silicon carbide (SiC) chip assembly with a 2-millimeter-thick copper substrate by means of thermal shock test (TST). Two different types of silver paste, nano-sized silver paste (NP) and nano-micron-sized paste (NMP), were used to sinter the silver film at 300 °C under a pressure of 60 MPa. The mean porosity (p) of the NP and MNP s-Ag films was 2.4% and 8%, respectively. The pore shape of the NP s-Ag was almost spherical, whereas the NMP s-Ag had an irregular shape resembling a peanut shell. After performing the TST at temperatures ranging from −40 to 150 °C, the scanning acoustic tomography (SAT) results suggested that delamination occurs from the edge of the assembly, and the delamination of the NMP s-Ag assembly was faster than that of the NM s-Ag assembly. The NMP s-Ag assembly showed a random delamination, indicating that the delamination speed varies from place to place. The difference in fracture mechanism is discussed based on cross-sectional scanning electron microscope (SEM) observation results after TST and plastic strain distribution results estimated by finite element analysis (FEA) considering pore configuration.
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Thèses sur le sujet "Delamination mechanism"

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Blandon, Omar Ali. « Mechanism of Delamination of Electrospun Adhesive Nanofibers ». University of Akron / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=akron1446477512.

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Yamanaka, Tadayoshi. « Delamination modelling and toughening mechanism of a woven fabric composite ». Thesis, McGill University, 2011. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=104701.

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Efficient and accurate numerical simulation methods for the damage tolerance analysis and fatigue life prediction of fibre reinforced polymers are in high demand in industry. Problems arise in the development of such a simulation method due to the limitations from numerical methods, i.e., delamination modelling, and understanding of damage mechanism of woven fabric composites. In order to provide effective and accurate delamination modelling, a new crack modelling method by using the finite element method is proposed in this study. The proposed method does not require additional degrees-of-freedom in order to model newly created crack/delamination surfaces. The accuracy of delamination growth simulation by the proposed method and that of a commercial FEA package are in good agreement. The damage mechanisms of five harness satin weave fabric composite is studied by creating a multiscale finite element model of a double cantilever beam specimen. The weft and warp yarns, where the gaps are filled with matrix, are individually modeled. Cohesive zone model elements are pre-located within the matrix and interfaces of matrix-yarns and weft-yarns and warp yarns. These meso-scale parts are bonded with homogeneous parts that are used to model regions where no damage is expected. This constitutes a multiscale model of a DCB specimen. The simulation results are in good agreement with the lower bound of experimental results. The toughening mechanism contributed from the weave structure was revealed. This study contributes to knowledge by introducing crack modelling methods and by providing more information in order to understand damage mechanisms of 5HS weave fabric composite laminates during delamination growth.
Les méthodes de simulation numériques efficaces et exactes pour l'analyse de l'endommagement et la prédiction de vie en fatigue des matériaux composites sont essentielles pour l'industrie. Les problèmes surviennent dans le développement d'une telle méthode de simulation en raison des restrictions des méthodes numériques, c'est-à-dire, modélisation de la délamination et compréhension des mécanismes de rupture de composites à base de fibres tissées.Pour developer un modèle de délamination efficace et précis, une nouvelle méthode est proposée dans cette étude en utilisant la method des éléments finis. La méthode proposée n'exige pas de degrés-de-liberté supplémentaires pour créer de nouvelles sufaces de fissures/ délaminations. Le résultat de simulation de délamination par la méthode proposée est comparé avec un logiciel d'éléments finis commercial, et les résultats se comparent bien.Les mécanismes d'endommagement d'un composite tissé typique "five-harness satin" sont le sujet d'une étude. Ceci est fait en créant un modèle d'éléments finis "méso-échelle" en utilisant l'exemple d'un spécimen d'essais Mode 1 (spécimen DCB). Le tissu est modélisé avec les trajectoires exactes des fibres dans les deux directions, et les espaces entre les fibres sont remplis de la matrice. Des éléments cohésifs sont insérés entre la matrice et les interfaces des fibres. Les composants méso-échelles sont joints avec des parties homogènes qui sont utilisées pour modéliser des régions où aucun endommagement n'est prévu. La combinaison des ces parties constitue un modèle multiéchelle d'un spécimen DCB. Les résultats de simulation d'un essai sont en accord avec les résultats expérimentaux, du côté conservateur. Le mécanisme renforçant des ultant du type de tissage a été démontré.Cette étude contribue à la science en présentant de nouvelles méthodes pour modéliser les fissures et pour comprendre les mécanismes d'endommagement des composites tissés pendant la croissance des délaminations.
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Tran, Tony D. « An Investigation of Initially Delaminated Composite Sandwich with Delamination Arrest Mechanism under Buckling Loading ». DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/428.

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This thesis involves the development of a fiberglass-foam composite sandwich structure with the introduction of delamination arrestment keys; therefore, a study of an initially delaminated composite sandwich structure was the experimental analysis on multiple configurations in how the arrestment keys are placed. The first part of this thesis research was to the experimental design and manufacturing of the composite sandwich plates. These plates were later cut down to the specific test dimensions and manufacturing processes for the composite sandwich plates and test specimens were created. The composite sandwich plates were manufactured using a vacuum resin infusion process. The dimensions of the composite layup are 14 inches in length with a width of 10.75 inches. The width size has margin to account for machining. The actual dimensions of the test specimen after it is prepared are 14 inches by 0.75 inches. The test anvil length is 11 inches and is used to perform tests to determine mechanical characteristics of the structures under buckling loading. These plates provide approximately 9 to 13 specimens per each case. All the test specimens have 4 plies of 18 oz fiberglass woven roving fabric from Jamestown Distributors, a LAST-A-FOAM FR-6710 foam core, and 5 to 1 ratio of West Systems 105/206 epoxy. Also, a non-porous material was integrated into the structure to create an initial delamination in some of the case studies. The integration of the delamination arrestment keys involve milling the foam core to provide the necessary grooves for key placements before the structure is vacuumed and epoxy is flowed. The arrestment keys are made of unidirectional fiberglass strand and the West Systems 105/206 epoxy using a wet layup process. In addition, fiberglass woven roving specimens were created to see the material characteristics under compression and tensile loading. The same is created to determine the material properties of the foam core, wood boundary core, and arrestment keys under compression loading. The second part to this thesis investigation is the experimental testing of the test specimens with all different variables considered. Those variables includes determining the final solid cure duration of the fiberglass skin, the geometric lengths between pure compression and pure buckling, behaviors of different initial delamination size, effects of continuous and discontinuous arrestment keys parallel and perpendicular to the in-plane loading, and material properties. The final solid cure duration differ from what the manufacturer gave on their epoxy. This experiment testing followed ASTM D-3039 standard to see the differences in elastic modulus over duration of 15 days. The resulting data shows that the test specimen fully cures after 13 to 14 days. The test specimens in search of the geometric buckling length for this investigation did not follow ASTM C-364 standard in full, but follows a variation of the ASTM C-364 standard in order to support buckling loading condition and the limited accessibility of the test equipments. Instead, the modifications are found with a different test jig design and test specimen configuration. The test jig was created to provide a pinned condition with a 0.25 inch diameter. The test specimen is laid up with a foam and wood cores. Two wood cores are laid at each edge of the foam core to increase loading capacity and holes are drilled through the wood cores to create a pinned-pinned case for the optimum buckling condition. The results detailing the geometric buckling show that after 9 inches anvil length there is no compression; only buckling occurs with a cross-sectional dimension of 0.75 inch by 0.575 inch. The 11 inch foam length was chosen for convenience of machining. This modified setup was also used for testing the different configuration with the embedded arrestment keys. The multiple different configurations completed for these test specimens under unstable loading, the experiment results show that a continuous arrestment key embedded significantly improve the loading capacity over a perfectly sound non-delaminated specimen and maintain the majority of loading capacity even with an introduced delamination. The embedded continuous key also provided a higher horizontal displacement capability before fracture in comparison to the initially delaminated test specimens. As for the test specimens used to determine the material characteristics, ASTM D-3410 and modified ASTM C-364 standards were followed. The test specimens had a fiber volume fraction of approximately 0.60, which details the brittle failure under tensile and compression loading. The results also show that the fibrous fiberglass test specimens have a higher ultimate strength in compression or buckling then in tension. All of the experimental testing was completed in the Aerospace Engineering Structural/Composite Lab at California Polytechnic State University at San Luis Obispo, California. Therefore, an introduction of a continuous arrestment key parallel to the in-plane loading and embedded into the composite sandwich structure provided a significant increase in loading and buckling capabilities in comparison to the control test specimens with and without an initial delamination and no embedded key. The continuous key placed parallel to the load vector increased the structural strength with an increase of 126% from a 1-inch delaminated structures and only an 11% drop from non-delaminated structures. That is, 1-inch and 2-inch delaminated structures showed a 61% drop and 81% drop from non-delaminated structures. Some configurations have reduced or arrested of the delaminated region.
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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.
Ph. D.
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Xia, Qingxi 1973. « Mechanics of inelastic deformation and delamination in paperboard ». Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/8334.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2002.
Includes bibliographical references (p. 233-236).
Paperboard is one of the most widely used materials. The inelastic deformation of paperboard plays a crucial role during many manufacturing processes (e.g., the converting process whereby paperboard is converted into a product such as a milk carton by punching and subsequent folding) and during in-service applications. There is a scarcity of constitutive models describing inelastic behavior of paperboard under complex loading, despite the paper industry's great need of analytical tools to aid the design and manufacturing of better paperboard products. In this thesis, two constitutive models are developed to model the highly anisotropic, elastic-plastic behavior of paperboard/paper: (1) A three-dimensional elastic-plastic interface constitutive model is developed to model the out-of-plane delamination behavior of paperboard. The onset of interface separation is controlled by a limit surface in the normal-shear traction space. The limit surface is taken to shrink with a monotonically-increasing scalar internal variable reflecting damage associated with the history of inelastic relative interface displacement. (2) A three-dimensional, anisotropic continuum constitutive model is developed to model the in-plane elastic-plastic deformation of paper and paperboard. The proposed initial yield surface is directly constructed from the yield strengths measured in various loading directions and the corresponding ratios of plastic strain components. An associated flow rule is used to model the plastic flow of the material. Anisotropic strain-hardening of yield strengths is introduced to model the evolution of the yield surface with inelastic strain.
(cont.) The two constitutive models are implemented into finite element software to enable the simulation of paperboard mechanical behavior under complex, finite deformation. The models are shown to be capable of accurately capturing both the out-of-plane delamination (via the interface model) and the anisotropic in-plane elastic-plastic (via the continuum in-plane model) behavior of paperboard under complex loading. The two models are combined to simulate the mechanics of a converting process (creasing and subsequent folding) of paperboard. The simulations agree well with corresponding experimental observations. In particular, the underlying mechanisms of damage and delamination development during creasing and subsequent folding are predicted well; the macroscopic response of the bending moment vs. bending angle also agrees with experimental data. This research provides physically based three-dimensional material models of the anisotropic, elastic-plastic deformation of paperboard that enable the computational design of paperboard process and product design.
by Qingxi Steve Xia.
Ph.D.
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Johansson-Näslund, Markus. « Numerical analysis of paperboard delamination using cohesive elements ». Thesis, KTH, Hållfasthetslära, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-277779.

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A new test method for measuring the shear strength associated with mode III delamination of paperboard is studied with the purpose of reducing the size of the test configuration. The method, which uses a split cantilever beam (SCB) specimen, measures the shear strength indirectly through the fracture resistance. The methodology is based on the double cantilever beam (DCB) specimen, used for measuring the normal delamination strength of paperboard. The study is based on finite element analyses, where cohesive elements are implemented for predicting the fracture response. An experimental evaluation of the test method was carried out in a pre-study conducted between Karlstad, Skövde and Lund University together with Tetra Pak. The experiments considered both the SCB-specimen and the standardised DCB-specimen, and for determination of the fracture behaviour the cohesive law presented by Tryding & Ristinmaa (2017) were considered. The result obtained from the experiments is used as a basis for evaluating the analyses. To model the fracture development, the relation presented by Tryding & Ristinmaa (2017) is implemented in the commercial finite element software Abaqus through a user-specified element. From the analyses of the DCB-specimen it is shown that through implementation of a specified cohesive law, it is possible to simulate mode I fracture development of paperboard in an accurate manner. The results for the DCB analyses correlate well with the experimental results. The result for the SCBspecimen shows a deviating behaviour from the experimental result by underestimating the shear strength. It is noted that the specimen is subjected to notable deformations in both the first shear direction and the normal direction, preventing pure shear loading from being obtained. Based on the analyses, it is indicated that the current test configuration does not obtain pure shear separation in mode III, and thereby underestimates the actual shear strength of the paperboard. It is also shown that reducing the specimen length with 400 mm has no significant impact on the properties related to the cohesive law. By altering the initial crack length, it is possible to further reduce the length of the specimen. However, to prevent development of unstable fracture, the length of the paperboard should exceed 300 mm. Alternating the crack length and the width of the paperboard also seems to contribute to lower displacements in the normal direction and provides a better fit with the experiments. Tryding, J. & Ristinmaa, M. (2017). Normalization of cohesive laws for quasi-brittle materials. Engineering Fracture Mechanics, 178, 333-345. doi:10.1016/j.engfracmech.2017.03.020
En ny testmetod för att mäta skjuvstyrkan för modus III delaminering av kartong studeras i syftet att reducera testutrustningens storlek. Testmetoden, som använder sig av en delad konsolbalk (SCB), mäter skjuvstyrkan indirekt genom brottresistansen. Metodiken är baserad på det standardiserad konsolbalks testet DCB, var två balkar är sammankopplade och som används för att mäta delaminering styrkan i kartongens normala riktning. Studien baseras på analyser med finita element, var kohesiva element implementeras för att prediktera brottbeteendet. En experimentell utvärdering av testmetoden genomfördes i en förstudie mellan Karlstads, Skövdes och Lunds universitet tillsammans med Tetra Pak. Experimenten gjordes både för DCB- och SCB-testet, och för att utvärdera brottbeteendet användes de kohesiva lagarna som presenterats av Tryding & Ristinmaa (2017). De experimentella resultaten används som bas vid utvärdering av analyserna. För att modellera spricktillväxten implementeras de kohesiva lagarna i det kommersiella FEM programmet Abaqus genom ett användar specificerat element (UEL). Från analyserna av DCB-testet visas det att det är möjligt att simulera modus I sprickbildning i kartong genom implementering av en specifik kohesive lag. Simuleringarna av DCB-testet stämmer väl överens med de experimentella resultaten. Resultaten från SCB-analyserna visar däremot på ett avvikande beteende från experimenten genom att underskatta skjuvstyrkan. Det noteras i analyserna av SCB-testet att märkbara deformationer i både den första skjuvriktningen och normal riktningen uppkommer, vilket förhindrar att ren skjuvbelastning i modus III erhålls. Baserat på analysernas resultat indikeras det att den nuvarande konfiguration för SCB-testet inte ger ren skjuvbelastning i modus III och underskattar därför kartongens faktiska skjuvstyrka. Det visas också att en 400 mm reducering av SCB-geometrins längd inte har någon märkbar påverkan på de kohesiva egenskaperna. Genom att ändra den initiala spricklängden är det möjligt att ytterligare reducera SCBgeometrins längd. För att försäkra sig om att sprickas tillväxt förblir stabil bör däremot längden på kartongen överstiga 300 mm. Att minska den initiala spricklängden och bredden på kartongen verkar generellt bidra till lägre deformationer i normal riktningen och ett resultat som ligger närmare de experimentella. Tryding, J. & Ristinmaa, M. (2017). Normalization of cohesive laws for quasi-brittle materials. Engineering Fracture Mechanics, 178, 333-345. doi:10.1016/j.engfracmech.2017.03.020
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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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Wang, Bin. « Local delamination failure of thin material layers ». Thesis, Loughborough University, 2017. https://dspace.lboro.ac.uk/2134/25128.

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Thin material layers have found various applications with various roles of functions, such as in fibre reinforced laminated composite materials, in integrated electronic circuits, in thermal barrier coating material system, and etc. Interface delamination is a major failure mode due to either residual stress or applied load, or both. Over the past several decades, extensive research works have been done on this subject; however, there are still uncertainties and unsolved problems. This thesis presents the new developed analytical studies on local delamination failure of thin material layers. Firstly, the analytical theories are developed for post-local buckling-driven delamination in bilayer composite beams. The total energy release rate (ERR) is obtained more accurately by including the axial strain energy contribution from the intact part of the beam and by developing a more accurate expression for the post-buckling mode shape. The total ERR is partitioned by using partition theories based on the Euler beam, Timoshenko beam and 2D-elasticity theories. By comparing with independent test results, it has been found that for macroscopic thin material layers the analytical partitions based on the Euler beam theory predicts the propagation behaviour very well and much better than the others. Secondly, a hypothesis is made that delamination can be driven by pockets of energy concentration (PECs) in the form of pockets of tensile stress and shear stress on and around the interface between a microscopic thin film and a thick substrate. Both straight-edged and circular-edged spallation are considered. The three mechanical models are established using mixed-mode partition theories based on classical plate theory, first-order shear-deformable plate theory and full 2D elasticity theory. Experimental results show that all three of the models predict the initiation of unstable growth and the size of spallation very well; however, only the 2D elasticity-based model predicts final kinking off well. Based on PECs theory, the room temperature spallation of α-alumina oxidation film is explained very well. This solved the problem which can not be explained by conventional buckling theory. Finally, the analytical models are also developed to predict the adhesion energy between multilayer graphene membranes and thick substrates. Experimental results show that the model based on 2D elasticity partition theory gives excellent predictions. It has been found that the sliding effect in multilayered graphene membranes leads to a decrease in adhesion toughness measurements when using the circular blister test.
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Dimant, Ron A. « Damage mechanics of composite laminates ». Thesis, University of Cambridge, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.338020.

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Huang, Haiying. « Single and multiple delamination behavior in composite plates ». Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12541.

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Livres sur le sujet "Delamination mechanism"

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

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

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Center, Langley Research, dir. Mechanics of instability-related delamination growth. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1988.

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Center, Langley Research, dir. Mechanics of instability-related delamination growth. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1988.

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Murthy, Pappu L. N. Finite element substructuring methods for composite mechanics. [Washington, DC] : National Aeronautics and Space Administration, 1988.

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United States. National Aeronautics and Space Administration., dir. Analysis of delamination related fracture processes in composites. [Washington, DC : National Aeronautics and Space Administration, 1992.

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United States. National Aeronautics and Space Administration., dir. Analysis of delamination related fracture processes in composites : Preliminary final report. [Washington, DC : National Aeronautics and Space Administration, 1988.

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United States. National Aeronautics and Space Administration, dir. Analysis of delamination related fracture processes in composites : Preliminary final report. [Washington, DC : National Aeronautics and Space Administration, 1988.

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Chapitres de livres sur le sujet "Delamination mechanism"

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Bi, Xue, Peng Zou et Xiangming Chen. « Study on Bearing Mechanism of Composite Stiffened Panel with Delamination Under Shear Load ». Dans Mechanical Engineering and Materials, 155–72. Cham : Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-68303-0_13.

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Liechti, Kenneth M. « Delamination Mechanics ». Dans 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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Dong, Hui Ru, Wanlin Guo et Zheng Yang. « Mechanism of Delamination and Its Effects on Fracture of Surface Crack Bodies in Ductile Pipeline Steel ». Dans Key Engineering Materials, 1235–40. Stafa : Trans Tech Publications Ltd., 2005. http://dx.doi.org/10.4028/0-87849-978-4.1235.

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Kachanov, L. M. « Delamination Buckling ». Dans 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 ». Dans 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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Baylakoglu, I., et E. Hedin. « PCB Delamination ». Dans 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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Megonigal, Luke, Foad Nazari, Amirhassan Abbasi, T. Haj Mohamad et C. Nataraj. « Delamination Fault Compensation in Composite Structures ». Dans Mechanisms and Machine Science, 141–50. Cham : Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-60694-7_8.

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Point, Nelly, et Elio Sacco. « A Delamination Model. Mathematical Properties ». Dans Solid Mechanics and Its Applications, 151–62. Dordrecht : Springer Netherlands, 1999. http://dx.doi.org/10.1007/978-94-011-4738-5_18.

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Allix, O., L. Gornet, P. Ladevèze et D. LéVêque. « Delamination Prediction by Continuum Damage Mechanics ». Dans Solid Mechanics and Its Applications, 163–71. Dordrecht : Springer Netherlands, 1999. http://dx.doi.org/10.1007/978-94-011-4738-5_19.

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Na, S. R., A. Hassan, K. M. Liechti et M. J. Krische. « Delamination Between Functionalized Silicon Surfaces ». Dans Experimental and Applied Mechanics, Volume 6, 89. New York, NY : Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4614-0222-0_12.

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Actes de conférences sur le sujet "Delamination mechanism"

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Zhu, Z., B. S. Xu, Y. Liu, Y. X. Chen, S. Ma et Z. X. Li. « The Delamination Wear Mechanism of Thermally Sprayed Coating ». Dans ITSC2005, sous la direction de E. Lugscheider. Verlag für Schweißen und verwandte Verfahren DVS-Verlag GmbH, 2005. http://dx.doi.org/10.31399/asm.cp.itsc2005p1462.

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Abstract The delamination wear mechanism of the thermally sprayed coatings was studied by analyzing coatings structural feature and stress distribution on the warm surface, and the influencing factors on the delamination wear were discussed. And the delamination wear mode of coating was developed. The results show that, the thermally sprayed coatings have typical aspect of lamellar structure. There are oxide layers between splats, and there also exist porosity and micro-crack in the coatings. The coating surface was subjected to alternately tensile stress and compression stress caused by normal load and friction force during sliding. In a certain depth below the surface, there exists maximum shear stress. Therefore fatigue damage will take place at subsurface of the coating under alternate stress. The adhesion strength between splats of coating prepared by HVAS is by far lower than casting material because of lamellar structure. And the adhesion strength between splats is further weakened due to the defects (such as porosity and micro-crack) appearing mostly on the boundaries between thin oxide sheets and splats. When the fatigue damage accumulates to a certain value, micro-cracks initiate at the defects between splats. Then these micro-cracks grow, connect, and propagate along the defects between splats. Finally, these cracks shear to the coating surface leading to spallation of the splats, and thus wear debris is generated. By repeating the above process delamination of the coatings will occur. Reducing friction coefficient, increasing coatings hardness and adhesion strength between inter-splats are the basic methods to improve the wear resistance of thermally sprayed coatings. Abstract only; no full-text paper available.
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Kumar, Rajesh S., et Matthew M. Mordasky. « Foreign Object Impact Damage in Ceramic Matrix Composites : Experiments and Computational Predictions ». Dans ASME Turbo Expo 2019 : Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-90368.

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Abstract Foreign object impact of Ceramic Matrix Composite (CMC) materials and components in a gas turbine engine environment could be detrimental to engine performance and hence must be accounted for in the design of such components. This paper is concerned with experiments and computational modeling of foreign object impact phenomenon in Silicon Carbide-based CMC. Controlled impact experiments were conducted on the CMC material using a gas-gun apparatus with spherical hardened steel projectile. The internal damage state within the CMC specimens was assessed using X-ray computed tomography scan technique. The computational modeling involved explicit dynamic finite element simulation of the impact process wherein either delamination mechanism is modeled or both ply damage and delamination mechanisms are modeled in a coupled manner. The delamination mechanism is modeled explicitly using cohesive-zone fracture mechanics approach, whereas, the ply damage mechanisms are modeled implicitly using simplified continuum damage mechanics approach. The simulation results were found to be in reasonable qualitative and quantitative agreement with the experimental results. Furthermore, it is shown that modeling both the ply damage and delamination mechanisms are essential to predict the correct delamination pattern even for intermediate velocity impacts that leads to predominantly delamination damage. The predictive nature of the modeling approach is demonstrated and approaches to enhance the models are also discussed.
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MASSEY, JUSTIN, BARRETT ROMASKO et HYONNY KIM. « NOVEL ENCLOSED DELAMINATION INJECTION REPAIR PROCESS FOR STRENGTH RESTORATION ». Dans 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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Kim, Ju Young, Hyoung-Ryeun Kim, Dong Woo Hahn et Sung Min Hwang. « Study on Development Behavior and Mechanism of Delamination by NCF Material under uHAST Test Condition ». Dans ISTFA 2017. ASM International, 2017. http://dx.doi.org/10.31399/asm.cp.istfa2017p0040.

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Abstract NCF (Non Conductivity Film) is a material used for under-fill purpose in the TSV (Through Silicon Via) process, and is a key material for ensuring TSV 3D Package (PKG) reliability. Among the types of defects generated by the NCF, the most typical type is delamination. Particularly in NCF delamination frequently occurs during reliability test, we analyzed chemical state change of NCF according to reliability test step/condition by utilizing FTIR and TMA. Through these studies, we clarify the cause of Delamination.
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Shen, Yanfeng, et Mingjing Cen. « Delamination Detection in Composite Plates Using Linear and Nonlinear Ultrasonic Guided Waves ». Dans ASME 2019 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/imece2019-10928.

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Abstract This paper presents a delamination detection strategy for composite plates using linear and nonlinear ultrasonic guided waves via the wave field imaging and signal processing based on Scanning Laser Doppler Vibrometry (SLDV). The anisotropic elastodynamics in composite plates is first studied. Two numerical methods are deployed to analyze the wave mechanics within the composite plates. The Semi-analytical Finite Element (SAFE) method is utilized to obtain the dispersion curves and mode shapes for a carbon fiber composite plate by bonding two quasi-isotropic carbon fiber composite panels together. The Local Interaction Simulation Approach has been employed to investigate the wave propagation and interaction with the delamination. Contact Acoustic Nonlinearity (CAN) between the delamination interfaces during wave damage interaction is presented as a potential mechanism for delamination detection. After developing an in-depth understanding of the wave propagation and wave damage interaction mechanism, active sensing experiments are conducted using the Piezoelectric Wafer Active Sensors (PWAS) and the Scanning Laser Doppler Vibrometry (SLDV). Two delamination imaging methodologies are presented. The first one utilizes the total wave energy to detect the delamination, taking advantage of the trapped modes within the delaminated area. The second one adopts the nonlinear second harmonic imaging algorithm, highlighting the nonlinear interaction traces at the delamination region. The damage detection images are finally compared and fused to provide detailed diagnostic information of the delamination. The damage imaging technique presented in this paper possesses great potential in material evaluation and characterization applications. This paper finishes with summary, concluding remarks, and suggestions for future work.
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Prack, Edward R., et Xuejun Fan. « Root Cause Mechanism for Delamination/Cracking in Stacked Die Chip Scale Packages ». Dans 2006 International Symposium on Semiconductor Manufacturing (ISSM). IEEE, 2006. http://dx.doi.org/10.1109/issm.2006.4493066.

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Knaster, Mark B., et Jeffrey M. Parks. « Mechanism of Corrosion and Delamination of Painted Phosphated Steel During Accelerated Corrosion Testing ». Dans SAE International Congress and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States : SAE International, 1986. http://dx.doi.org/10.4271/860110.

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Kondo, S., T. Nasuno, S. Ogawa, S. Tokitou, B. U. Yoon, A. Namiki, Y. Sone et al. « The Delamination Mechanism of Porous Low-k Film during the Cu-CMP Process ». Dans 2003 International Conference on Solid State Devices and Materials. The Japan Society of Applied Physics, 2003. http://dx.doi.org/10.7567/ssdm.2003.c-5-3.

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Matsumoto, Keiji, Keishi Okamoto et Hiroyuki Mori. « The Mechanism of the Low-K Stress Reduction in Chip Assembly by Shorter Solder Bump Height ». Dans ASME 2017 International Technical Conference and Exhibition on Packaging and Integration of Electronic and Photonic Microsystems collocated with the ASME 2017 Conference on Information Storage and Processing Systems. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/ipack2017-74097.

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To solve the low-k delamination in chip assembly for high-end servers, our hypothesis is proposed that the low-k stress is determined by the bending moment and the stress relaxation of a joint. In our hypothesis, the low-k stress decreases as the joint height (SnAg bump height) becomes shorter, such as below 80μm, in 150μm-pitch joints. Our hypothesis is supported by simulation, in which the low-k stress is investigated as a function of the joint height, the joint material and also the joint width (the joint pitch). Finally, experiments are performed to evaluate the low-k delamination as a function of the joint height and our hypothesis is also supported by experiments.
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De la Rama, Lito P., Dante G. Nuarin et Marilin H. Nery. « Die Edge Thin Film Delamination on the Bottom Die of a Stacked Chip Scale Package (SCSP) ». Dans ISTFA 2005. ASM International, 2005. http://dx.doi.org/10.31399/asm.cp.istfa2005p0037.

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Abstract The increasing demand for high end electronic devices incorporating multiple functions in a small form factor leads to the widespread use of Stacked Chip Scale Packaging (SCSP) in the semiconductor industry. Multiple die stacking in various combinations have been achieved. However, new failure mechanisms are being observed due to new package stress characteristics. This paper will present a unique failure mechanism observed on the bottom die of a multiple die stack package. A detailed discussion of the failure mechanism showing the interaction between the presence of a high die attach adhesive fillet and the die singulation damage initiating a thin film delamination from the die edge towards the active circuit area causing electrical failures will be presented.
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Rapports d'organisations sur le sujet "Delamination mechanism"

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Hodo, Wayne. Investigation of the mechanisms for the delamination resistance found in bio-engineered composites found in nature : bi-layered exoskeleton fish scales. Engineer Research and Development Center (U.S.), mai 2019. http://dx.doi.org/10.21079/11681/32680.

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