Relevant bibliographies by topics / Composite bonded joints

Academic literature on the topic 'Composite bonded joints'

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Published: 4 June 2021
Last updated: 7 September 2023

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Journal articles on the topic "Composite bonded joints"

1

Hart-Smith, L. J. "Bonded-bolted composite joints." Journal of Aircraft 22, no. 11 (November 1985): 993–1000. http://dx.doi.org/10.2514/3.45237.

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2

Ghoneam, S. M., A. A. Hamada, and M. I. El-Elamy. "Experimental and Analytical Investigations of the Dynamic Analysis of Adhesively Bonded Joints for Composite Structures." Solid State Phenomena 147-149 (January 2009): 663–75. http://dx.doi.org/10.4028/www.scientific.net/ssp.147-149.663.

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Adhesively bonded joints are used extensively in various industries. Some imperfections like holes, thermal residual stresses occurring in the bolted, welded, riveted, and soldered joints don't take place in adhesively bonded joints. Hence, the main advantages of bonded joint are lightness, sealing, corrosion resistance, heat and sound isolation, damping, and quickly mounting facility which have been highly proved. This paper introduces an attempt to study the dynamic analysis of adhesively bonded joint for composite structures to investigate mainly the influences of lamina code number, bonded adhesive line configuration and boundary condition on the dynamic behavior of the test specimens containing composite assembly. The numerical based on the use of finite element model (FEM) modified by introducing unified mechanical properties are represented and applied to compute efficiently the Eigen-nature for composite bonded structures. The experimental tests are conducted to investigate such adhesive bonded joints using two different techniques. The first technique includes an ultrasonic technique in which the magnetostractive pulse echo delay-line for material characterization of composite material is used. The second technique is bassed on the use of the frequency response function method (FRF) applying the hammering method. The comparison between the numerical and experimental results proves that the suggested finite element models of the composite structural beams with bonded joints provide an efficient by accurate tool for the dynamic analysis of adhesive bonded joints. The damping capacity is inversely proportional to the stiffness of the bonded joint specimens. The type of the proportionality depends mainly on the bond line configuration type, lamina orientation, and boundary conditions. This in turn enables an accurate evaluation for selecting the proper characteristics of the specimens for controlling the present damping capacity and the proper resistance against deformation during the operating process. The present study provides an efficient non-destructive technique for the prediction of dynamic properties for an adhesive bonded joint for the studied composite structure systems. The coordination of the experimental and numerical techniques makes it possible to find an efficient tool for studying the dynamic performance of adhesively bonded joint for composite structures.
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3

Lokhande, Rupesh, Abhijeet Deshpande, and Ashok Mache. "Taguchi Analysis of Bonded Single-Lap Joint in Hemp Fiber Composite." International Journal of Engineering Technology and Sciences 3, no. 1 (June 30, 2016): 27–33. http://dx.doi.org/10.15282/ijets.5.2016.1.4.1043.

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The adhesively bonded joints in composite structures are widely used in aerospace and automobile fields. Hemp epoxy composites are better alternative due to its lower specific gravity and higher toughness. . The joining process is inevitable in the application of such composites. The mechanical behaviour of such joints depends on the strength of the composite, adhesive strength and adhesion phenomenon between substrate and adhesive. The influence of overlap length, adhesive layer thickness and cure temperature on the performance of adhesive joints investigated experimentally. The influence of these parameters on the static behaviour of the joint was studied using design of experiment approach. L9 orthogonal array was used for experimental design. It was found that cure temperature of adhesive predominantly governs joint behaviour followed by adhesive layer thickness and overlap length. To obtain joint strength in the working limits, an empirical relationship between governing parameters and response was developed. Through the analysis it was observed that optimum strength of bonded joint was obtained with overlap length of 25 mm, adhesive layer thickness of 0.5 mm and cure temperature of 500C.
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Liu, Longquan. "A study of the damage tolerance of composite-metal hybrid joints reinforced by multiple and penetrative thin pins." Composites and Advanced Materials 31 (January 2022): 263498332211055. http://dx.doi.org/10.1177/26349833221105523.

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The application of adhesive bonding technology in aircraft structures can reduce the total wight greatly, but the bonded joints are very sensitive to the possible manufacturing defects and damages during service operations, which makes them difficult to meet the damage tolerance requirements of the current transport airplane structures. In this study, the damage tolerance of composite-metal hybrid joints reinforced by multiple and penetrative thin pins was studied. The damage tolerance performance of the composite-metal joint is supposed to be enhanced by multiple through-the-thickness penetrative thin reinforcements in the bonding region, and the thin reinforcements were bonded together with both the composite and metallic joint plates. Both experimental tests and finite element simulations were conducted to investigate the effects of the through-the-thickness reinforcements on the damage tolerance performance of the joints with and without pre-fabricated disbond defects. Through the comparative analyses, it was found that the penetrative thin pins in the bonding region significantly improved the static load carrying capacity, the failure strain, the fracture energy, and the fatigue lives of the composite-metal bonded joints. Moreover, the reinforcements decreased the sensitivity of the bonded joints to the disbond defects in the bonding region. The damage tolerance performance of the composite-metal adhesively bonded joints was significantly increased by the through-the-thickness penetrative reinforcements and the enhancement mechanism was revealed by the combined analysis of test results and simulation results.
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5

ATMAKURI, Ayyappa, Arvydas PALEVICIUS, Madhusudan SIDDABATHULA, and Giedrius JANUŠAS. "Failure Studies on Adhesive Bonded and Bolted Joints of Natural Fiber Composites." Mechanics 27, no. 5 (October 12, 2021): 392–99. http://dx.doi.org/10.5755/j02.mech.28108.

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Composites with natural fibers as reinforcements are playing a vital role in recent developments. The present work deals with the fabrication of okra and empty fruit bunch banana fiber polyester matrix composites with varying reinforcement content (5%, 10%, and 15%). Composites were fabricated by using the hand layup technique. After the fabrication process, composites were then adhesively bonded and also joined with bolts. The main objective of this work is to analyse the failure studies on adhesive bonded and bolted joints of okra and empty fruit bunch banana composite specimens. The specimens were tested under tensile load, flexural creep studies, and SEM analysis. It has been observed that empty fruit bunch banana fiber composites exhibited better joint strength properties under tensile loading when compared to the okra fiber composites. To estimate the flexural creep behaviour, all the samples were tested at a constant load of 2.5kg and 5kg. The deflections obtained during regular time intervals (four months) were noted. The presence of internal defects and void content was observed by using the scanning electron microscope. The results showed that adhesive-bonded composites were exhibited less deflection compared to the bolted joints. The empty fruit banana fiber composites exhibited higher creep than okra fiber composites. Decreased creep with the increased fiber has been observed in both cases. SEM Adhesively bonded joints possessing better sustainability as compared to the bolted joints in both the fiber-reinforced composites.
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Ramezani, Farin, Beatriz D. Simões, Ricardo J. C. Carbas, Eduardo A. S. Marques, and Lucas F. M. da Silva. "Developments in Laminate Modification of Adhesively Bonded Composite Joints." Materials 16, no. 2 (January 6, 2023): 568. http://dx.doi.org/10.3390/ma16020568.

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The use of carbon fibre reinforced polymer (CFRP) materials is increasing in many different industries, such as those operating in the aviation, marine, and automotive sectors. In these applications, composite parts are often joined with other composite or metallic parts, where adhesive bonding plays a key role. Unlike conventional joining methods, adhesive bonding does not add weight or require the drilling of holes, both of which are major sources of stress concentration. The performance of a composite joint is dependent on multiple factors and can be improved by modifying the adhesive layer or the composite layup of the adherend. Moreover, joint geometry, surface preparation, and the manufacturing methods used for production are also important factors. The present work reviews recent developments on the design and manufacture of adhesively bonded joints with composite substrates, with particular interest in adherend modification techniques. The effects of stacking sequence, use of thin-plies, composite metal laminates and its specific surface preparations, and the use of toughened surface layers in the composite adherends are described for adhesively bonded CFRP structures.
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Kim, Won Seock, and Jung Ju Lee. "Interfacial Fracture Analysis of Adhesive-Bonded Joints." Advanced Materials Research 33-37 (March 2008): 327–32. http://dx.doi.org/10.4028/www.scientific.net/amr.33-37.327.

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The failure in an adhesive-bonded structure starts at the interface, and the interfacial fracture is of interest whenever adhesion between different materials is concerned. One of primary factors limiting the application of adhesive-bonded joints to structural design is the lack of a good evaluation tool for adhesion strength to predict the load-bearing capacity of boned joints. The adhesion strength of composite/steel bonding has been evaluated using interfacial fracture mechanics characterization. The energy release rate of a composite/steel interfacial crack was compared with the fracture toughness of the interface, which was measured from bi-material end notched flexure (ENF) specimens, to predict the failure loads of bi-material lap joints. Fracture toughness, IIc G , was regarded as a property of the interface rather than a property of the adhesive. The results show that interfacial fracture mechanics characterization of adhesion strength can be a practical engineering tool for predicting the load-bearing capacities of adhesive-bonded joints.
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Qin, Tian Liang, Li Bin Zhao, and Hai Huang. "Damage Investigation and Design of Woven Composite Bonded Joint." Key Engineering Materials 417-418 (October 2009): 861–64. http://dx.doi.org/10.4028/www.scientific.net/kem.417-418.861.

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Non-plane joints, such as T-joints, L-joints and  shaped joint can bring enormous potential benefits from the reduction of the fastener and the part count, which lead to the dramatic decrease of assemble cost and primary structural weight in composite structures. To understand the mechanistic character of the  joint, a 3-D finite element analysis model is established by means of software ABAQUS. The stresses on ply level and the predictions on the damage onset of 3-D woven composite π joint under tensile load are obtained. Numerical results agree well with empirical data. The effects of structural geometry parameters, such as support length, support thickness and radius of the corner, are also discussed. Results illustrated that increasing the thickness of L preform or filler radius can improve the strength of woven composite π joint effectively.
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Asgari Mehrabadi, Farhad. "Experimental and Numerical Failure Analysis of Adhesive Composite Joints." International Journal of Aerospace Engineering 2012 (2012): 1–10. http://dx.doi.org/10.1155/2012/925340.

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In the first section of this work, a suitable data reduction scheme is developed to measure the adhesive joints strain energy release rate under pure mode-I loading, and in the second section, three types of adhesive hybrid lap-joints, that is, Aluminum-GFRP (Glass Fiber Reinforced Plastic), GFRP-GFRP, and Steel-GFRP were employed in the determination of adhesive hybrid joints strengths and failures that occur at these assemblies under tension loading. To achieve the aims, Double Cantilever Beam (DCB) was used to evaluate the fracture state under the mode-I loading (opening mode) and also hybrid lap-joint was employed to investigate the failure load and strength of bonded joints. The finite-element study was carried out to understand the stress intensity factors in DCB test to account fracture toughness using J-integral method as a useful tool for predicting crack failures. In the case of hybrid lap-joint tests, a numerical modeling was also performed to determine the adhesive stress distribution and stress concentrations in the side of lap-joint. Results are discussed in terms of their relationship with adhesively bonded joints and thus can be used to develop appropriate approaches aimed at using adhesive bonding and extending the lives of adhesively bonded repairs for aerospace structures.
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Nagayya, M. K. Venkatesh, N. Nithesh Bhaskar, and B. K. Venkatesha. "Strength analysis of carbon fiber reinforced polymer and titanium alloy for axisymmetric lap joint." Journal of Mines, Metals and Fuels 69, no. 12A (April 28, 2022): 137. http://dx.doi.org/10.18311/jmmf/2021/30142.

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Many industries such as oil, gas, aerospace, and automotive, use axisymmetric adhesively bonded single lap joints. Different materials are frequently mated using axisymmetric lap joints. When composite adherents delaminate, the stress circulation inside the adhesive layer significantly influenced. As a result, the importance of considering adhesive layer stresses in the presence of considerable delamination is investigated in this paper. To understand stress analysis and examine adhesive bond strength at static loading conditions, the model created using finite element analysis with cohesive zone modelling. A complete parametric study carried using simple finite element code in ABAQUS, the axisymmetric single lap joins adhesively bonded joints prepared with different material adherents. Analysis carried on the influence of numerous factors such as the distribution stress inside the adhesive joints. In this connection, mating of carbon reinforced polymer composite to titanium alloy adherends discussed thoroughly. The results show that depending on the position of the delamination, the presence of a throughout-the-thickness delamination affects the structural response of both single lap and axisymmetric adhesively bonded joints by varying overlap length. The presence of a delamination reduced adhesive peel and shear stresses significantly in both joint configurations.
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Dissertations / Theses on the topic "Composite bonded joints"

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Ficarra, Christina Helene. "ANALYSIS OF ADHESIVE BONDED FIBER-REINFORCED COMPOSITE JOINTS." NCSU, 2001. http://www.lib.ncsu.edu/theses/available/etd-20010626-155040.

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The work presented in this thesis involved the analysis of adhesive bonded joints for composite bridge decks and was divided into three phases. The first phase involved a parametric study on a single lap joint using ANSYS finite element analysis software. The purpose of the parametric study was to alter the geometry and material properties of the joint and study their effects on the stress distribution in both the adherends and adhesive. The four different cases studied included adding a taper to the adherends, different edge shapes on the adhesive layer, a material stiffness imbalance and a geometric stiffness imbalance. It was found that for the taper case and the edge shape case, the stress field in the joint was affected slightly. The material and geometric stiffness imbalance cases had the most drastic affect on the stress field of both the adhesive and adherend. Phase two of this study involved physical tests on single lap joints pulled in uniaxial tension. Tests were performed on three different types of laminates in order to study the interfacial effects these laminates had on the adhesive bond. It was found that by changing the surface of the composite, the mode of failure changed significantly.Phase three of this research involved a study on surface preparation. Three different surface preparations were conducted on the adherends of a butt-strap joint. The first included an acetone wipe. The second involved sanding the adherends. The third surface preparation involved adding APRIME-2, a secondary bonding agent, to the adherends before adding the strap. By simply sanding the adherends, the load to failure was increased by 350% compared to an acetone wipe. The ATPRIME-2 improved the load to failure by an additional 60% as well as improved the failure mode to a fiber tear. It was concluded that surface preparation has a major impact on the behavior of adhesively bonded joints.

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Shāhid, Muḥammad. "Adhesion characterisation of bonded steel/composite cleavage joints." Thesis, University of Glasgow, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.402470.

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Osiyemi, Stephen Olusegun. "The fatigue performance of adhesively bonded fibre-composite joints." Thesis, Imperial College London, 1992. http://hdl.handle.net/10044/1/7971.

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Brett, Michael Alexander de Oliveira. "Prediction of the performance of adhesively-bonded composite joints." Thesis, Imperial College London, 2012. http://hdl.handle.net/10044/1/9545.

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The use of adhesively-bonded joints instead of the traditional types of joining can give reduced weight and increased stiffness in a structure. However, most industries have concerns about the use of adhesive joints in anything other than secondary structures, due to uncertainties over the long-term service life. This thesis discusses the prediction of the lifetime of adhesively-bonded composite structures. A fracture mechanics approach was used to characterise the fracture behaviour of an epoxy film adhesive, Cytec FM-300M, mainly using composite substrates prepared using wet peel ply, removing the need for any additional surface treatment. Aluminium alloy substrates were also used for some tests. Tapered double cantilever beam and double cantilever beam specimens were used to determine the mode I critical strain energy release rate, GIC, and end loaded split specimens were tested to obtain the mode II critical strain energy release rate, GIIC. Lastly, fixed ratio mixed mode specimens were used to obtain the relationship between GIC and GIIC when a joint undergoes mixed mode failure. For validation purposes, single lap joint and double scarf joint specimens were also tested. These data were then applied in finite element models using Abaqus. Two different modelling techniques were used, the virtual crack closure technique and cohesive zone modelling, CZM. Simulations of the tests performed were executed, in the process obtaining the CZM fitting parameters. Good agreement with the experimental data was verified for each of the models tested. Fatigue tests were also performed in order to obtain the mode I and mode II threshold values of the fracture energy below which crack growth did not occur, by executing double cantilever beam and end loaded split tests, respectively. For validation purposes, single lap joint fatigue tests were also performed to determine the threshold maximum load the joint could withstand without failure. Finally, using the CZM fitting parameters obtained in the quasi-static tests and the experimentally obtained threshold values of the fracture energy, modelling of single lap and double scarf joints was performed in order to predict the maximum load value for which no failure would occur when subject to cyclic loading. These predictions showed excellent agreement with the experimental results, showing that this simpler model can obtain good results.
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Pillai, Govind Ramakrishna Lankarani Hamid M. "Response of adhesively bonded composite joints to low velocity impact." Diss., A link to full text of this thesis in SOAR, 2006. http://soar.wichita.edu/dspace/handle/10057/676.

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Thesis (M.S.)--Wichita State University, College of Engineering, Dept. of Mechanical Engineering.
"December 2006." Title from PDF title page (viewed on Nov. 4, 2007). Thesis adviser: Hamid M. Lankarani. Includes bibliographic references (leaves 64-67).
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Mosher, Bryan C. "Failure Prediction of Adhesively Bonded Hardboard Doorskin Joints." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/42867.

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Wood and wood based composites such as hardboard have become very common materials for use in non-structural applications, which include pre-finished paneling, siding, exterior trim, furniture, and door skins. This thesis describes the results of a study of the failure of hardboard door skins. Forces applied during manufacture load the door skins in bending, and in some cases cause a split at the edge of the hardboard. A finite element model as well as a closed form solution based on mechanics of materials were developed to analyze the stresses and deformations of the door skin/stile assembly so that stresses could be predicted for various stile widths and loading conditions. The wood members that make up the frame along the perimeter of the doors, or stiles, were modeled as orthotropic and their properties were selected from available literature. The hardboard was modeled as transversely isotropic, and its properties were determined experimentally. The closed form solution developed can be used to determine the critical geometry for different combinations of hardboard thickness and adhesive joint stiffness. It predicts that as the stile width decreases, the point of maximum deflection, and greatest stresses, moves toward the outside edge of the panel. The ability to predict the critical stile width, or the stile width below which the maximum deflection and stress occurs at the outside edge of the panel, allows one to design the joint to be able to withstand specific loadings and prevent unwanted delamination of the hardboard during manufacture.
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Pohlit, David Joseph. "Dynamic Mixed-Mode Fracture of Bonded Composite Joints for Automotive Crashworthiness." Thesis, Virginia Tech, 2007. http://hdl.handle.net/10919/33837.

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An experimental evaluation of the mixed-mode fracture behavior of bonded composite joints is presented. Commonly used experimental techniques for characterizing the mode I, mixed-mode I/II, mode II, and mode III fracture behavior have been employed for the purpose of developing a fracture envelope to be utilized in the automotive design process. These techniques make use of such test geometries as the double cantilever beam (DCB), asymmetric double cantilever beam (ADCB), single-leg bend (SLB), end-loaded split (ELS), and split cantilever beam (SCB) specimens. Symmetric versions of the DCB, SLB, and ELS specimens produced mode mixities of 0°, 41°, and 90° respectively, while the testing of ADCB specimens allowed for mode mixities of 18°, 31°. Pronounced stick-slip behavior was observed for all specimen test geometries under both quasi-static and dynamic loading conditions. Due to the nature of the adhesive studied, a limited number of data points were obtained under mode I loading conditions. A significant increase in the number of measurable crack initiation events was observed for mixed-mode I/II loading conditions, where stick slip behavior was less pronounced. Additionally, a comparison of the measured fracture energies obtained under mixed-mode I/II loading conditions reveals that the addition of a small mode II component results in a decrease in the mode I fracture energy by roughly 50%, as the crack was driven to the interface between the adhesive layer and composite adherends. Furthermore, the propensity of debonds to propagate into the woven composite laminate adherends under mode II loading conditions limited the number of crack initiation points that could be obtained to one or two usable data points per specimen. A limited number of experimental tests using the SCB specimen for mode III fracture characterization, combined with a numerical analysis via finite element analysis, revealed a significant mode II contribution toward the specimen edges. Similarly, FE analyses on full bond width and half bond width SCB specimens was conducted, and results indicate that by inducing a bond width reduction of 50%, the mode II contribution is greatly decreased across the entire width of the specified crack front. To provide a means for comparison to results obtained using the standard DCB specimen, an alternative driven wedge test specimen geometry was analyzed, as this geometry provided a significant increase in the number of measurable data points under mode I loading conditions. A three-dimensional finite element analysis was conducted to establish ratios of simple beam theory results to those obtained via FEA, GSBT/GFEA, were of particular interest, as these ratios were used to establish correction factors corresponding to specific crack lengths to be used in correcting results obtained from an experimental study utilizing a driven wedge technique. Corrected results show good agreement with results obtained from traditional mode I double cantilever beam tests. Finally, bulk adhesive experiments were conducted on compact tension specimens to establish a correlation between adhesively bonded composite joint and bulk adhesive fracture behavior under mode I loading conditions. Measured fracture energy values were shown to gradually drop across a range of applied loading rates, similar to the rate-dependent behavior observed with both the DCB and driven wedge specimens. Application of the time-temperature superposition principle was explored to determine whether or not such techniques were suitable for predicting the fracture behavior of the adhesive studied herein. Good correlation was established between the fracture energy values measured and the value of tan d obtained from dynamic mechanical analysis tests conducted at corresponding reduced test rates.
Master of Science
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8

Wang, Xiao. "Stress-Function Variational Methods for Stress Analysis of Composite Laminates and Adhesively Bonded Composite Joints." Thesis, North Dakota State University, 2015. https://hdl.handle.net/10365/27639.

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Adhesively bonded composite joints (ABCJs) have been broadly used to connect multimaterials and show their structural and economic advantages compared to traditional bonding methods. However, robust methods are still desired for efficient and accurate lay-wise stress analysis of ABCJs involving multiple boundaries and layers. The purpose of this work was to extend the stress-function variational method for free-edge stress analysis of composite laminates with a finite length. At each interface of the laminate, two unknown Lehknitskii?s stress potential functions were introduced to interpolate the stresses across the layer. A set of 4th-order governing ODEs of the functions was obtained via evoking the complementary virtual work, solved by eigenvalue-function method under proper traction conditions. Corresponding MATLAB? program was developed and validated by the FEM (ANSYS?). This method can also examine the stress-suppression effect after composite laminates interleafing. Consequently, the above method was furthered for determining the laywise stress distribution in ABCJs.
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Tiu, W. P. "Fatigue strength prediction of adhesively bonded unidirectional carbon fibre reinforced composite joints." Thesis, City University London, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.378857.

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Jolly, Prateek. "Lamb wave based active damage identification in adhesively bonded composite lap joints." Thesis, Mississippi State University, 2016. http://pqdtopen.proquest.com/#viewpdf?dispub=10100288.

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Bonding composite structures using adhesives offers several advantages over mechanical fastening such as better flow stress, weight saving, improved fatigue resistance and the ability to join dissimilar structures. The hesitation to adopt adhesively bonded composite joints stems from the lack of knowledge regarding damage initiation and propagation mechanisms within the joint. A means of overcoming this hesitation is to continuously monitor damage in the joint. This study proposes a methodology to conduct structural health monitoring (SHM) of an adhesively bonded composite lap joint using acoustic, guided Lamb waves by detecting, locating and predicting the size of damage. Finite element modeling of a joint in both 2D and 3D is used to test the feasibility of the proposed damage triangulation technique. Experimental validation of the methodology is conducted by detecting the presence, location and size of inflicted damage with the use of tuned guided Lamb waves.

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Books on the topic "Composite bonded joints"

1

Cheng, Jinquan. Smart adhesively bonded composite joints: Analysis and design. Hauppauge, NY, USA: Nova Science, 2009.

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2

Chamis, C. C. Simplified procedures for designing adhesively bonded composite joints. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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S, Mall, and Langley Research Center, eds. Mixed-mode cyclic debonding of adhesively bonded composite joints. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

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S, Mall, and Langley Research Center, eds. Mixed-mode cyclic debonding of adhesively bonded composite joints. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

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S, Mall, and Langley Research Center, eds. Mixed-mode cyclic debonding of adhesively bonded composite joints. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

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K, Kochhar N., and Langley Research Center, eds. Criterion for mixed mode fracture in composite bonded joints. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

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S, Mall, and Langley Research Center, eds. Mixed-mode cyclic debonding of adhesively bonded composite joints. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

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Ali, Rezaizadeh Mohammad, Ramamurthy G, and Langley Research Center, eds. Interaction of mixed mode loading on cyclic debonding in adhesively bonded composite joints. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

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R, Tullos Thomas, ed. Handbook of adhesive bonded structural repair. Park Ridge, N.J., U.S.A: Noyes Publications, 1992.

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S, Johnson W., Everett R. A, and Langley Research Center, eds. Effect of adherend thickness and mixed mode loading on debond growth in adhesively bonded composite joints. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

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Book chapters on the topic "Composite bonded joints"

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Marr, G. R., R. P. Barrowcliffe, and A. R. Curtis. "The Non-destructive Evaluation of Composite Bonded Joints." In Composite Structures 3, 502–10. Dordrecht: Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-4952-2_35.

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Kim, Hyonny. "Analytical Modeling for Composite Structures." In Strength Prediction of Adhesively-Bonded Joints, 47–70. Boca Raton, FL : Taylor & Francis Group, CRC Press, [2016] | “A science publishers book.”: CRC Press, 2017. http://dx.doi.org/10.1201/9781315370835-3.

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Hart-Smith, L. J. "Adhesively Bonded Joints for Fibrous Composite Structures." In Recent Advances in Structural Joints and Repairs for Composite Materials, 173–210. Dordrecht: Springer Netherlands, 2003. http://dx.doi.org/10.1007/978-94-017-0329-1_6.

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Dhilipkumar, Thulasidhas, and Murugan Rajesh. "Adhesively Bonded Composite Joints in Aerospace Application." In Repair of Advanced Composites for Aerospace Applications, 71–85. Boca Raton: CRC Press, 2022. http://dx.doi.org/10.1201/9781003200994-7.

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Tong, L., J. K. Spelt, and G. Fernlund. "Strength Determination of Adhesive Bonded Joints." In Recent Advances in Structural Joints and Repairs for Composite Materials, 27–66. Dordrecht: Springer Netherlands, 2003. http://dx.doi.org/10.1007/978-94-017-0329-1_2.

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Vinson, Jack R. "Laminated Shells and Adhesive Bonded Joints." In The Behavior of Shells Composed of Isotropic and Composite Materials, 178–82. Dordrecht: Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-015-8141-7_9.

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Mao, Jianghui, Sayed A. Nassar, and Xianjie Yang. "A Model for Fracture Characterization of Adhesively-Bonded Joints." In Composite Materials and Joining Technologies for Composites, Volume 7, 81–91. New York, NY: Springer New York, 2013. http://dx.doi.org/10.1007/978-1-4614-4553-1_9.

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Curtis, A. R., and P. D. Ainsworth. "The Mechanical Testing and Computer Modelling of Composite Bonded Joints." In Composite Structures 3, 562–74. Dordrecht: Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-4952-2_39.

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Gupta, Mohit, Matteo Mazzotti, Daniel Cantrell, Michael McCracken, Jarod Weber, Chuck Zhang, and Massimo Ruzzene. "Guided Wave-Based Assessment of Bonded Composite Joints." In Lecture Notes in Civil Engineering, 242–51. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-07322-9_25.

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Tserpes, Konstantinos, Elli Moutsompegka, Mareike Schlag, Kai Brune, Christian Tornow, Ana Reguero Simón, and Romain Ecault. "Characterization of Pre-bond Contamination and Aging Effects for CFRP Bonded Joints Using Reference Laboratory Methods, Mechanical Tests, and Numerical Simulation." In Adhesive Bonding of Aircraft Composite Structures, 51–117. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-319-92810-4_2.

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AbstractIn this chapter, the pre-bond contamination and ageing effects on carbon fiber reinforced plastic (CFRP) adherends and CFRP bonded joints are characterized by means of reference laboratory non-destructive testing (NDT) methods, mechanical tests, and numerical simulation. Contaminations from two fields of application are considered, namely in aircraft manufacturing (i.e. production) and for in-service bonded repair. The production-related scenarios comprise release agent, moisture, and fingerprint, while the repair-related scenarios comprise fingerprint, thermal degradation, de-icing fluid, and a faulty curing of the adhesive. For each scenario, three different levels of contamination were pre-set and applied, namely low, medium and high level. Furthermore, two types of samples were tested, namely coupons and pilot samples (a stiffened panel and scarf repairs). The CFRP adherends were contaminated prior to bonding and the obtained surfaces were characterized using X-ray photoelectron spectroscopy. After bonding, the joints were tested by ultrasonic testing. To characterize the effects of each contamination on the strength of the bonded joints, mode-I and mode-II fracture toughness tests, and novel centrifuge tests were conducted on the coupons, while tensile tests were performed on the scarfed samples. Additionally, numerical simulation was performed on CFRP stiffened panels under compression using the LS-DYNA finite element (FE) platform.
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Conference papers on the topic "Composite bonded joints"

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Gollins, Kenneth, Jack Chiu, Céline Baudrand, and Feridun Delale. "Characterization of Adhesively Bonded Composite Joints Under High Strain Rate Loading." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-71711.

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With the advantage of having a high strength to weight ratio, composite materials are frequently being implemented as alternatives to steel and aluminum in military vehicles. To perform satisfactorily, joined composite laminates on a vehicle must be able to absorb a significant amount of energy under high strain rate loading events such as ballistic impact. In this paper the dynamic behavior and failure modes of adhesively bonded S2-glass/epoxy laminate joints are investigated. For this experiment, two structural adhesives are selected for comparison: a brittle methacrylate and a more compliant epoxy. The tests are conducted on an in-house assembled gas-gun to achieve the high strain rates necessary to break the adhesive bonds in two configurations, Mode I and II. Results obtained from the ballistic impact tests are compared to quasi-static test results to emphasize the rate-sensitivity of the bonded joints. Irrespective of the material configuration, the failure load of the adhesively bonded joint is seen to increase with the loading rate. Overall, epoxy appears to be 35–50% stronger than methacrylate by most measures. Under bending loading (mode I), most cases exhibit some amount of damage within the composite surrounding the bonded area, demonstrating a fiber-tear failure rather than a cohesive failure. The failure strength of the composite joint is thus not always proportional to the adhesion strength of the adhesive due to the weakness of delamination of the composite material, especially when loaded through the thickness of the composite. As compared with metal adherends, the composites are shown to absorb three times more energy per unit area.
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Anwar, Iqbal, and Golam Newaz. "Computational Approach for Adhesively Bonded Composite Joints." In ASME 2000 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/imece2000-2476.

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Abstract A computational intensive study was performed to assess an efficient way to model adhesively bonded glass fiber reinforced composite joints in automotive applications. Three different finite element modeling techniques had been implemented. First, adhesive was represented by 1D-spring elements. Spring stiffness was calculated from adhesive property. This model is inadequate to assess stresses developed in the adhesive layer directly. So adhesive was modeled with 2D elements for better assessment of state of stress in the adhesive and the substrate. Both the model provide limit load, but crack initiation and failure of the bond can not be captured. The third approach adopted was the nodal failure model. In the nodal failure model, to understand the failure of adhesively bonded joints, bond strength had been specified to the interface nodes of the composite substrate. Combined failure criteria had been used. Cracks propagated and interface debonded when interface stress exceeded the failure limit. Finite element model results compared well with the experimental data. This modeling approach was later adopted for dynamic modeling of adhesively bonded joints, which shows promise.
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Action, Jason, and Stephen P. Engelstad. "Crack Arrestment of Bonded Composite Joints." In 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-1876.

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Tsai, Hsi, James Alper, and David Barrett. "Failure analysis of composite bonded joints." In 41st Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-1428.

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Otheguy, M., A. G. Gibson, and A. M. Robinson. "Towards Recyclable Composite Craft: Fusion Bonded Thermoplastic Composite T-Joints." In Marine & Offshore Composites. RINA, 2010. http://dx.doi.org/10.3940/rina.moc10cd.2010.04.

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Dvorak, George J., Jian Zhang, and Olcay Canyurt. "Adhesive Joints for Composite Sandwich Structures." In ASME 2000 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/imece2000-2034.

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Abstract A new approach is explored for joining of thick, woven E-glass/vinyl ester composite laminated plates to steel or composite plates, with applications in naval ship structures. Adhesive is applied along through-the-thickness contoured interfaces, employing tongue-and-groove geometry. Both experimental and finite element modeling results are presented. They show that adhesively bonded tongue-and-groove joints between steel and composite plates loaded in monotonically increasing longitudinal tension, are stronger than conventional strap joints even in relatively thin plates. In particular, a single 0.25 in. wide and 8 or 12 in. long steel tongue, bonded by the Dexter- Hysol 9339 adhesive to a groove in a 0.5 in. thick laminated plate, can support a 20,000 lbs tension force. This force is expected to increase in proportion to plate thickness. Simple design rules indicate that high joint efficiency can be achieved for any thickness of the joined plates.
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Flansburg, Barrett, Stephen Engelstad, and Jim Lua. "Robust Design of Composite Bonded Pi Joints." In 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2447.

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Oterkus, Erkan, Atila Barut, Erdogan Madenci, and Damodar Ambur. "Analysis of Bolted-Bonded Composite Lap Joints." In 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-2187.

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Yarrington, Phil, James Zhang, Craig Collier, and Brett Bednarcyk. "Failure Analysis of Adhesively Bonded Composite Joints." In 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-2376.

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Cox, S., S. Danley, J. Wright, A. Nettles, W. Guin, and K. Segal. "Composite Repair Process for Adhesively Bonded Joints." In CAMX 2019. NA SAMPE, 2019. http://dx.doi.org/10.33599/nasampe/c.19.0696.

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Reports on the topic "Composite bonded joints"

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Tsai, Hsi C., James Alper, and David Barrett. Failure Analysis of Composite Bonded Joints. Fort Belvoir, VA: Defense Technical Information Center, March 1999. http://dx.doi.org/10.21236/ada375743.

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Madenci, Erdogan. An Inverse Approach for Capturing the Interaction of Macro- and Micro-Scales in Characterizing Bonded Composite Joints. Fort Belvoir, VA: Defense Technical Information Center, May 2000. http://dx.doi.org/10.21236/ada387637.

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