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Academic literature on the topic 'Delamination of Composites'

Author: Grafiati

Published: 6 September 2023

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Journal articles on the topic "Delamination of Composites"

1

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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Toscano, Cinzia, Aniello Riccio, FrancescoPaolo Camerlingo, and Carosena Meola. "On the use of lock-in thermography to monitor delamination growth in composite panels under compression." Science and Engineering of Composite Materials 21, no. 4 (September 1, 2014): 485–92. http://dx.doi.org/10.1515/secm-2013-0156.

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AbstractThe success of composites in automotive, aerospace, and naval applications is mainly related to their aptitude to be tailored to obtain a final product that perfectly fulfills the design requirements. However, during both manufacturing processes and maintenance, some flaws, like delaminations (which may escape simple visual inspection), may be induced in composite structures. The presence of delaminations is of major concern for the load-carrying capability of carbon fiber-reinforced polymer panels. Indeed, delaminations can strongly affect the structural strength and may grow under in-service loads, leading sometimes to catastrophic failures. The aim of this work is to explore the use of lock-in thermography for the monitoring of delamination propagation in composite structures when subjected to generic multiaxial loading conditions. A stiffened composite panel with an embedded skin delamination subjected to compressive loading was taken as a benchmark to assess experimentally the effectiveness of lock-in thermography for monitoring the delamination propagation in situ during the compressive mechanical test. The delamination size as a function of the applied load, observed by lock-in thermography during the execution of the compressive test, was used to validate the results of preliminary numerical computations.

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Chattopadhyay, Aditi, Changho Nam, and Youdan Kim. "Damage Detection and Vibration Control of a Delaminated Smart Composite Plate." Advanced Composites Letters 9, no. 1 (January 2000): 096369350000900. http://dx.doi.org/10.1177/096369350000900101.

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In this paper, the effects of delamination on the dynamic characteristics of a composite plate are investigated. The refined higher order theory is used to model the smart composite plate in the presence of delaminations. The theory accurately captures the transverse shear deformation through the thickness, which is important in anisotropic composites, particularly in the presence of discrete actuators and sensors and delaminations. Next, the detection of delamination is investigated using the Root Mean Square (RMS) values of the response of the composite plate subject to disturbances. An active control system is designed to minimise the effect of delamination. The pole placement technique is applied to design the closed loop system by utilising piezoelectric actuators. Numerical results show that the RMS information can be used to estimate the location of the delamination. The controller designed makes the delaminated plate behave like a healthy plate model. The controller also reduces the magnitudes of RMS responses due to disturbance.

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Subba Rao, V. V., Godavarthi Yeswanth Kiran Kumar, and Sansanka Pentapalli. "Reduction of AWJ Induced Delaminations by Impregnated Nanoclay GFRP Composites." Materials Science Forum 969 (August 2019): 284–90. http://dx.doi.org/10.4028/www.scientific.net/msf.969.284.

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Composite materials are extensively used in various applications like space, aircraft, and automobile sector because of superior physical and mechanical properties even though they are costly. In recent technological innovations, using Montmorillonite (Nanoclay) to reinforce polymer-based composites has raised attention to academic and industrial sectors since small addition could enhance Mechanical properties thereby decreasing failures like delaminations. In present research work, the effect of AWJ machining parameters on delaminations of glass fibre reinforced epoxy composite is investigated. The Main objective is determining delamination factor and reduce delaminations which is major failure in laminates. This paper investigates on effects of impregnated Nanoclay epoxy in Bi-directional GFRP where previous research has been made only in changing the parameters for reduction of delaminations. The samples were machined using AWJ, delamination factors are measured using image-J software and SEM analysis for comparing micrographs. Finally with increase in nano clay weight fraction, delaminations are checked.

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Wei, Z., L. H. Yam, and L. Cheng. "Delamination Assessment of Multilayer Composite Plates Using Model-based Neural Networks." Journal of Vibration and Control 11, no. 5 (May 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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Sreekanth, T. G., M. Senthilkumar, and S. Manikanta Reddy. "Natural Frequency based delamination estimation in GFRP beams using RSM and ANN." Frattura ed Integrità Strutturale 16, no. 61 (June 19, 2022): 487–95. http://dx.doi.org/10.3221/igf-esis.61.32.

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The importance of delamination detection can be understood from aircraft components like Vertical Stabilizer, which is subjected to heavy vibration during the flight movement and it may lead to delamination and finally even flight crash can happen because of that. Any solid structure's vibration behaviour discloses specific dynamic characteristics and property parameters of that structure. This research investigates the detection of delamination in composites using a method based on vibration signals. The composite material's flexural stiffness and strength are reduced as a result of delaminations, and vibration properties such as natural frequency responses are altered. In inverse problems involving vibration response, the response signals such as natural frequencies are utilized to find the location and magnitude of delaminations. For different delaminated beams with varying position and size, inverse approaches such as Response Surface Methodology (RSM) and Artificial Neural Network (ANN) are utilized to address the inverse problem, which aids in the prediction of delamination size and location.

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Mahieddine, Ali, and Mohammed Ouali. "Analysis of Delaminated Composite Plates." Advanced Materials Research 686 (April 2013): 104–8. http://dx.doi.org/10.4028/www.scientific.net/amr.686.104.

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A mathematical model for plates with partially delaminated layers is presented to investigate their behavior. In this formulation account is taken of lateral strains. The principal advantage of the element is that it allows the modeling of delamination anywhere in the structure. The region without delamination is modeled to carry constant peel and shear stresses; while the region with delamination is modeled by assuming that there is no peel and shear stress transfer between the top and bottom layers. Numerical results of the present model are presented and its performance is evaluated for static problems. Laminated beams and plates are often used as primary load-carrying structures. However, the mechanical properties of composite materials may degrade severely in the presence of damage. One of the common types of damage modes in laminated composites is delamination. The presence of delamination is one of the most prevalent life-limiting failure modes in laminated composite structures. Many researchers had been studying the effect of delamination. Wee and Boay [1] developed an analytical model to predict the critical load of a delaminated composite laminated beam. Lee et al. [2] investigated the buckling behavior of the beam plate with multiple delaminations under compression. Kapania and Wolfe [3] examined the buckling behavior of a beam plate with two delaminations of equal length. Wang et al. [4] improved the analytical solution by including the coupling between the flexural and axial vibrations of the delaminated sub-laminates. Lee et al. [5] studied a composite beam with arbitrary lateral and longitudinal multiple delamination. Finite-element methods have been developed using the layerwise theory by Kim et al. [6]. Tan and Tong [7] developed a dynamic analytical model for the identification of delamination embedded in a laminated composite beam. To investigate the effects of delamination of a plate layers, a finite-element model is developed. Both displacement continuity and force equilibrium conditions are imposed between the regions with and without delamination. The accuracy of the approach is verified by comparing results with previously published data.

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Tay, TE. "Characterization and analysis of delamination fracture in composites: An overview of developments from 1990 to 2001." Applied Mechanics Reviews 56, no. 1 (January 1, 2003): 1–32. http://dx.doi.org/10.1115/1.1504848.

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Delamination is a major failure mode in laminated composites and has received much research attention. A huge amount of literature has been published on this subject, resulting in considerable improvement in our understanding of delamination behavior. A rather comprehensive review paper was published by Garg in 1988. That paper contains 136 references from 1971 to 1988, a period spanning roughly two decades. A more recent survey by Pagano and Schoeppner contains critical reviews of many selected papers, especially the pioneering works on delamination research. An overview of Russian and Soviet literature on this subject is also given by Bolotin. The present paper aims to review major developments in the analysis and characterization of buckling driven delamination from 1990 to the present. Its abridged version was presented in a plenary lecture at the 13th International Conference on Composite Materials, Beijing. Particular emphasis is placed on the application of fracture mechanics methods in the analysis of delamination. The question of the extent of fracture mechanics’ success in characterizing delamination, both in laboratory-based specimens and in more realistic structural composite components, is discussed. Some recent numerical formulations for efficient computational modeling and analysis of delaminations are also reviewed. This review lists 270 major works covering a period of about a decade, indicating that there is still considerable research interest and activity in this field.

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Sellitto, Andrea, R. Borrelli, Francesco Caputo, Aniello Riccio, and Francesco Scaramuzzino. "Application of the Mesh Superposition Technique to the Study of Delaminations in Composites Thin Plates." Key Engineering Materials 525-526 (November 2012): 533–36. http://dx.doi.org/10.4028/www.scientific.net/kem.525-526.533.

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Laminated composite structures are increasingly finding more applications in various fields thanks to their lower weight if compared with other materials of the same strength. Nevertheless, composites thin plates show a critical behavior in terms of damage propagation mechanisms when subjected to (low velocity) impact. Indeed they tend to produce delaminations which can be hardly detected by optical inspections and can affect the global load carrying capability, leading to a premature structural collapse. The aim of this paper is to assess the capabilities of the Davies-Zhang approach (introduced in 1994 and aimed to the estimation of both the delamination initiation impact load and the size of the impact induced delaminations) by using a multiscale FE model based on the mesh superposition technique. Indeed the impact area has been modeled layer-wise with an element per layer while the rest of the structure has been modeled at laminate level by layered elements by means of a homogenization approach for the determination of the equivalent laminate material properties. The impact induced delamination area has been determined by adopting stress-based criteria. The results (in terms of delamination initiation impact force and delamination size) have been compared to the ones obtained by adopting the Davies-Zhang approach.

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Azuan, S. A. Syed, J. M. Juraidi, and Wan Mansor Wan Muhamad. "Evaluation of Delamination in Drilling Rice Husk Reinforced Polyester Composites." Applied Mechanics and Materials 232 (November 2012): 106–10. http://dx.doi.org/10.4028/www.scientific.net/amm.232.106.

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Delamination is recognized as one of the most critical defects that can result from the machining composites. Delamination has been a major form of failure in drilled composite materials due to the composites lack of strength in the drilling direction, which results in poor surface finish, reduction in bearing strength, reduction in structural integrity and ultimately poor performance of the composite. Currently, most of the major research reported delamination address specific of machining fiber glass, graphite fiber or carbon fiber reinforced polymer composites. It is not yet clear how different drilling parameters affect the machinability of natural fiber reinforced polymer composite materials and quality of drilled holes. This paper report the investigation in drilling holes on natural fibre reinforced polyester composites and evaluate its hole quality by measuring delamination. Three different type of drill: twist 118o drill, brad drill and end mill were used. Drilling process is carried out for three spindle speed (1500 rpm, 2000 rpm and 2500 rpm) and three feed rate (0.1 mm/rev, 0.15 mm/rev and 0.2 mm/rev). Brad drill experienced higher delamination values compared to twist and end mill. Increasing of feed rate and spindle speed also caused a relevant increase in the delamination values. It is found that Rice husk reinforced polyester composites delamination value is lower when compared to the glass fiber reinforced polymer.

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Dissertations / Theses on the topic "Delamination of Composites"

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Alessa, Hassan Ali. "Delamination in Hybrid Carbon/Glass Fiber Composites." University of Dayton / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1399037290.

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Canturri, Gispert Carla. "On delamination directionality and migration in laminated composites." Thesis, Imperial College London, 2014. http://hdl.handle.net/10044/1/18169.

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Delamination is recognised as the most critical damage process in laminated composites under compressive or bending loading conditions and managing this failure mode has been key to using composites in primary structures. However, predictive modelling of delamination growth has been limited, since even a simple, single plane defect can result in multiplane delamination growth which is often associated to other secondary processes such as intralaminar or translaminar damage. The objective of this thesis has been to experimentally investigate the fundamental phenomena associated with delamination growth which were isolated from the observations made in embedded defects: delamination preferentially grows along the direction of the fibres at a ply interface (directionality) and, if forced to grow obliquely to the fibres, a change of delamination plane typically ensues (migration). Directionality was demonstrated with a bespoke test to grow delamination in a preferential direction. The geometrical effect of the fibres on the direction of delamination growth was also studied using a macroscopic model of the delaminating interface. A numerical strategy was introduced to model directionality. Cohesive elements and the virtual crack closure technique were modified to include the effect of fibre orientation at the interface at which delamination propagated. Migration was isolated with a series of delamination tests in cross-ply laminates under variable mode mixities. Finally, the insight gained in delamination growth mechanisms was demonstrated on a set of sandwich configurations with embedded defects to understand growth in complex composite geometries. Fractographic studies were used to glean a detailed understanding of the migration process. This work has successfully characterised the detailed processes by which delaminations grow and provided knowledge to develop damage tolerant designs.

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Lee, Jaehong. "Vibration, buckling and postbuckling of laminated composites with delaminations." Diss., This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-06062008-170322/.

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Malik, Basharat U. "Fatigue delamination growth under cyclic compression in unidirectional composites." Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/12094.

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Xu, Ying. "Detection of delamination in composites with fiber optic sensor /." View abstract or full-text, 2004. http://library.ust.hk/cgi/db/thesis.pl?CIVL%202004%20XU.

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Thesis (Ph. D.)--Hong Kong University of Science and Technology, 2004.
Includes bibliographical references (leaves 194-209). Also available in electronic version. Access restricted to campus users.

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Daniewicz, David Joseph 1965. "Edge delamination in advanced laminated composites, theory and verification." Thesis, The University of Arizona, 1990. http://hdl.handle.net/10150/277294.

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A damage evolution theory capable of predicting the effects of edge delamination phenomena on composite laminate response is developed. The theory is a mechanics-based formulation which quantifies the damage development of a laminate under general loading, and incorporates it directly to the constitutive behavior of the laminate. The theoretical development introduces a laminate-specific constant φ; the methodology of φ selection is presented for [±15/±50]s, [±45/0/90]s, and [0₂/90₂]s T300 graphite/epoxy laminates. Edge effects are demonstrated by comparing the damage state of the above laminates with and without edge delamination damage. The capability of the theory in predicting the volume scaling effect is shown through consideration of the failure strengths of the [±25/90n]s laminate series.

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Javidrad, Farhad. "The development of a finite element for delamination growth in composites." Thesis, Imperial College London, 1995. http://hdl.handle.net/10044/1/7731.

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Gambone, Livio R. "The effect of R-ratio on the mode II fatigue delamination growth of unidirectional carbon/epoxy composites." Thesis, University of British Columbia, 1991. http://hdl.handle.net/2429/29968.

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An investigation of the effect of R-ratio on the mode II fatigue delamination of AS4/3501-6 carbon/epoxy composites has been undertaken. Experiments have been performed on end notched cantilever beam specimens over a wide range of R-ratios (-l ≤R ≤0.50). The measured delamination growth rate data have been correlated with the mode II values of strain energy release rate range ∆G[formula omitted]), maximum strain energy release rate (G[formula omitted]) and stress intensity factor range (∆K[formula omitted]). The growth rate is dependent on the R-ratio over the range tested. For a constant level of ∆G[formula omitted], the crack growth rate decreases with increasing R-ratio. A similar trend is observed when the data is plotted as a function of G[formula omitted]. The effect of plotting the growth rate as a function of ∆K[formula omitted] is to produce an R-ratio dependence opposite to that obtained by either the ∆G[formula omitted] or G[formula omitted] approach. For a constant level of ∆K[formula omitted], the crack growth rate increases with increasing R-ratio. Master equations which completely characterize the fatigue behaviour as a function of ∆G[formula omitted] and ∆K[formula omitted] have been derived, based on the observation that the growth rate law exponent, n and constant, A are unique functions of R-ratio. Values for n are surprisingly large and increase with increasing R-ratio whereas values for A decrease with increasing R-ratio. The effect of time-at-load has been considered in an attempt to explain the existence of the R-ratio dependence of the growth rate. The correct trend can be established for the exponent, n but not for the constant, A. Friction between the crack faces, particularly at higher R-ratios, is proposed as a possible explanation for the observed anomaly. Further evidence of a frictional mechanism operating at higher R-ratios has been discovered through a postmortem fracture surface examination. Additional fractographic observations are presented over the entire range of R-ratios tested. In regions subjected to negative R-ratio cycling, there is no evidence of the characteristic mode II hackle features. Instead, loose rounded particles of matrix material are found. An extensive amount of hackling is observed in regions subjected to low positive R-ratio cycles. The extent of hackle damage visibly decreases in areas where higher levels of R-ratio are imposed. A correlation between the general fracture surface morphology and the fatigue data provides support for the hypothesis that energy for delamination is always available in sufficient quantity, and that growth is dependent on the stresses ahead of the crack tip being sufficiently high.
Applied Science, Faculty of
Materials Engineering, Department of
Graduate

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9

Gozluklu, Burak. "Delamination Analysis By Using Cohesive Interface Elements In Laminated Composites." Master's thesis, METU, 2009. http://etd.lib.metu.edu.tr/upload/12611005/index.pdf.

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Finite element analysis using Cohesive Zone Method (CZM) is a commonly used method to investigate delamination in laminated composites. In this study, two plane strain, zero-thickness six-node quadratic (6-NQ) and four-node linear (4-NL) interface elements are developed to implement CZM. Two main approaches for CZM formulation are categorized as Unified Mode Approach (UMA) and Separated Mode Approach (SMA), and implemented into 6-NQ interface elements to model a double cantilever beam (DCB) test of a unidirectional laminated composite. The results of the approaches are nearly identical. However, it is theoretically shown that SMA spawns non-symmetric tangent stiffness matrices, which may lower convergence and/or overall performance, for mixed-mode loading cases. Next, a UMA constitutive relationship is rederived. The artificial modifications for improving convergence rates such as lowering penalty stiffness, weakening interfacial strength and using 6-NQ instead of 4-NL interface elements are investigated by using the derived UMA and the DCB test model. The modifications in interfacial strength and penalty stiffness indicate that the convergence may be improved by lowering either parameter. However, over-softening is found to occur if lowering is performed excessively. The morphological differences between the meshes of the models using 6-NQ and 4-NL interface elements are shown. As a consequence, it is highlighted that the impact to convergence performance and overall performance might be in opposite. Additionally, benefits of selecting CZM over other methods are discussed, in particular by theoretical comparisons with the popular Virtual Crack Closure Technique. Finally, the numerical solution scheme and the Arc-Length Method are discussed.

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Datta, Sidhyartha. "Investigation of the micromechanics of delamination in fibre reinforced composites." Thesis, Imperial College London, 2005. http://hdl.handle.net/10044/1/7867.

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Books on the topic "Delamination of Composites"

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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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3

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

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4

Chern, E. James. Assessment of probability of detection of delaminations in fiber-reinforced composites. Greenbelt, Md: National Aeronautics and Space Administration, Goddard Space Flight Center, 1991.

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5

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

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6

Armanios, Erian A. Analysis of delamination related fracture processes in composites. [Washington, DC: National Aeronautics and Space Administration, 1992.

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7

Storakers, Bertil. Nonlinear plate theory applied to delamination in composites. Stockholm, Sweden: The Royal Institute of Technology, Department of Strength of Materials and Solid Mechanics, 1987.

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Center, Langley Research, ed. Delamination modeling of composites for improved crash analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

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Center, Langley Research, ed. Delamination modeling of composites for improved crash analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

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10

1928-, Sun C. T., and United States. National Aeronautics and Space Administration., eds. Dynamic delamination crack propagation in a graphite/epoxy laminate. [Washington, DC]: National Aeronautics and Space Administration, 1991.

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Book chapters on the topic "Delamination of Composites"

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Lucia, A. C., G. P. Solomos, P. Zanetta, L. Merletti, and R. Pezzoni. "Delamination Detection Via Holographic Interferometry Techniques." In Mechanical Identification of Composites, 206–12. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3658-7_23.

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Akbarov, Surkay. "Stability Loss in the Structure of Unidirected Fibrous Elastic and Viscoelastic Composites." In Stability Loss and Buckling Delamination, 337–400. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-30290-9_6.

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Brunel, J. E., D. Lang, and D. Trallero. "A Criterion of Mixed Mode Delamination Propagation in Composite Material." In Mechanical Identification of Composites, 350–61. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3658-7_40.

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Akbarov, Surkay. "Surface and Internal Stability Loss in the Structure of Elastic and Viscoelastic Layered Composites." In Stability Loss and Buckling Delamination, 269–335. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-30290-9_5.

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Bose, Tanmoy, Subhankar Roy, and Kishore Debnath. "Detection of Delamination in Fiber Metal Laminates Based on Local Defect Resonance." In Reinforced Polymer Composites, 147–64. Weinheim, Germany: Wiley-VCH Verlag GmbH & Co. KGaA, 2019. http://dx.doi.org/10.1002/9783527820979.ch8.

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Haque, Nawshad. "Delamination in Timber Induced by Drying." In Delamination in Wood, Wood Products and Wood-Based Composites, 197–212. Dordrecht: Springer Netherlands, 2010. http://dx.doi.org/10.1007/978-90-481-9550-3_10.

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Bucur, Voichita. "Delamination Detection – A Vibration-Based Approach." In Delamination in Wood, Wood Products and Wood-Based Composites, 33–50. Dordrecht: Springer Netherlands, 2010. http://dx.doi.org/10.1007/978-90-481-9550-3_3.

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Soutis, C., and S. H. Díaz Valdés. "Delamination Detection in Laminated Composites Using Lamb Waves." In Recent Advances in Composite Materials, 109–26. Dordrecht: Springer Netherlands, 2003. http://dx.doi.org/10.1007/978-94-017-2852-2_10.

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Hirwani, Chetan K., Rishabh Pal, Mrinal Chaudhury, Subrata Kumar Panda, and Nitin Sharma. "Dynamic Behavior of Laminated Composites with Internal Delamination." In Advanced Composite Materials and Structures, 277–94. Boca Raton: CRC Press, 2022. http://dx.doi.org/10.1201/9781003158813-16.

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Li, Tianzhi, Francesco Cadini, Manuel Chiachío, Juan Chiachío, and Claudio Sbarufatti. "Particle Filter-Based Delamination Shape Prediction in Composites." In Lecture Notes in Civil Engineering, 227–36. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-07258-1_24.

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Conference papers on the topic "Delamination of Composites"

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Cheng, Wing, and Shigeru Itoh. "Modeling of Delamination in Composites." In ASME 2005 Pressure Vessels and Piping Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/pvp2005-71224.

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Stacking sequence, number of plies, and geometry of the composite structure have significant impact on the strength and reliability of the structure. The most detrimental failure mode in composite structures is delamination. Modeling of delamination failure is, therefore, a very important technique for predicting the reliability of composite structures. A modified crack closure technique was used in determining the driving force for crack propagation and branching of laminated composites at the interfaces. Mixed mode fracture parameters, GI for the opening mode, GII for the shear mode, were calculated using the technique for two typical composite structures; namely a composite laminate subjected to tensile loading, and a curved composite laminate subjected to bending. Results of these analyses give a better understanding on the crack growth behavior of these structures, and therefore, provide insight in the composite construction for improved design of the structures.

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LIU, J. L., and V. B. C. TAN. "Delamination in Bio-inspired Laminates." In American Society for Composites 2017. Lancaster, PA: DEStech Publications, Inc., 2017. http://dx.doi.org/10.12783/asc2017/15243.

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Reedy, E. David, and Frank J. Mello. "Modeling Delamination Growth in Composites." In ASME 1996 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/imece1996-0492.

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Abstract A method for modeling the initiation and growth of discrete delaminations in shell-like composite structures is presented. The laminate is divided into two or more sublaminates, with each sublaminate modeled with four-noded quadrilateral shell elements. A special, eight-noded hex constraint element connects opposing sublaminate shell elements. It supplies the nodal forces and moments needed to make the two opposing shell elements act as a single shell element until a prescribed failure criterion is satisfied. Once the failure criterion is attained, the connection is broken, creating or growing a discrete delamination. This approach has been implemented in a three-dimensional finite element code. This code uses explicit time integration, and can analyze shell-like structures subjected to large deformations and complex contact conditions. The shell elements can use existing composite material models that include in-plane laminate failure modes. This analysis capability was developed to perform crashworthiness studies of composite structures, and is useful whenever there is a need to estimate peak loads, energy absorption, or the final shape of a highly deformed composite structure. This paper describes the eight-noded hex constraint element used to model the initiation and growth of a delamination, and discusses associated implementation issues. Particular attention is focused on the delamination growth criterion, and it is verified that calculated results do not depend on element size. In addition, results for double cantilever beam and end notched flexure specimens are presented and compared to measured data to assess the ability of the present approach to model a growing delamination.

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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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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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Ke, L., and F. van den Meer. "Multiscale Modeling of Composite Laminates Delamination via Computational Homogenization." In VIII Conference on Mechanical Response of Composites. CIMNE, 2021. http://dx.doi.org/10.23967/composites.2021.040.

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Anam, K., M. Todt, and H. Pettermann. "Computationally Efficient Modeling of Delamination Behavior in Laminated Composites." In VIII Conference on Mechanical Response of Composites. CIMNE, 2021. http://dx.doi.org/10.23967/composites.2021.057.

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ZHOU, WU, and DAHSIN LIU. "Peridynamic Modeling of Impact-induced Delamination in Laminated Composites." In American Society for Composites 2017. Lancaster, PA: DEStech Publications, Inc., 2017. http://dx.doi.org/10.12783/asc2017/15283.

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JAYARAM, ROHITH, SEUNGHYUN KO, JINKYU YANG, and MARCO SALVIATO. "Delamination Resistance and Size Effect in Discontinuous Fiber Composites." In American Society for Composites 2018. Lancaster, PA: DEStech Publications, Inc., 2018. http://dx.doi.org/10.12783/asc33/26000.

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PEREZ, DANIEL, and RYAN KARKKAINEN. "Damage and Delamination Modeling of Multifunctional Composite Structural Batteries." In American Society for Composites 2018. Lancaster, PA: DEStech Publications, Inc., 2018. http://dx.doi.org/10.12783/asc33/26173.

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Reports on the topic "Delamination of Composites"

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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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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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Cavallaro, Paul V., Andrew W. Hulton, Melvin W. Jee, and Mahmoud Salama. Effects of Crimped Fiber Paths on Mixed Mode Delamination Behaviors in Woven Fabric Composites. Fort Belvoir, VA: Defense Technical Information Center, September 2016. http://dx.doi.org/10.21236/ad1017636.

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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.), May 2019. http://dx.doi.org/10.21079/11681/32680.

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Gama, Bazle A., Jia-Run Xiao, Md J. Haque, Chian-Fong Yen, and John W. Gillespie Jr. Experimental and Numerical Investigations on Damage and Delamination in Thick Plain Weave S-2 Glass Composites Under Quasi-Static Punch Shear Loading. Fort Belvoir, VA: Defense Technical Information Center, February 2004. http://dx.doi.org/10.21236/ada421310.

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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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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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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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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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Reedy, E. D. Jr, F. J. Mello, and T. R. Guess. Modeling the initiation and growth of delaminations in composite structures. Office of Scientific and Technical Information (OSTI), January 1996. http://dx.doi.org/10.2172/201804.

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