Relevant bibliographies by topics / Composite bonded joints

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

Academic literature on the topic 'Composite bonded joints'

Author: Grafiati
Published: 4 June 2021
Last updated: 9 June 2025

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Journal articles on the topic "Composite bonded joints"

1

Motlhakudi, I., and A. Jonker. "Fatigue Characterisation of Adhesives Used in Fibre-Reinforced Composites." R&D Journal 39 (2023): 53–79. http://dx.doi.org/10.17159/2309-8988/2023/v39a6.

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A review of past investigations into the fatigue behaviour of structural adhesives and bonded joints in fibre-reinforced polymer composites is given. An overview of the structural adhesives used in general bonded joint applications is first provided, followed by an experimental fatigue testing of these bonded components. The aspects that influence fatigue strength and fatigue life for adhesively bonded joints in fibre-reinforced polymer composites are then discussed in terms of the adhesive composition, geometry configuration, surface condition and preparation, and loading conditions. The aspects that relate to fatigue crack initiation and crack propagation in these bonded composite components are discussed in terms of damage modelling, monitoring, and detecting of crack initiation, crack growth rates and crack propagation modelling. The impact of environmental factors such as temperature and humidity on the fatigue performance of these bonded composite joints is also discussed. The paper then concludes by providing guidelines for characterising the fatigue behaviour of adhesively bonded joints and adhesives used in fibre-reinforced polymer composite applications
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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

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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4

Kulkarni, Santosh, Devendra Singh, Laeth Hussain, V. Balaji, Ajay Sharma, Khurmatbek Jumaniyozov, and Kamila Kenjaeva. "Finite element analysis of bonded, riveted and hybrid joints in glass fibre epoxy composite laminates for aircraft structure." E3S Web of Conferences 563 (2024): 02006. http://dx.doi.org/10.1051/e3sconf/202456302006.

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Because of their superior fatigue resistance and high strength-to-weight ratio, composite materials are essential to the construction of modern airplanes. The joints that interconnect the various parts of these structures play a critical role in their integrity and functionality. In aerospace applications, bonded, riveted, and hybrid joints are among the many types of joints that are frequently used. A thorough finite element analysis (FEA) of hybrid, bonded, and riveted joints in glass fiber epoxy composite laminates for airplane structures is presented in this work. The literature review addresses earlier studies on bonded, riveted, and hybrid joints and emphasizes the importance of joints in composite constructions. There are gaps in our knowledge of these joints' performance under various stress scenarios, despite the fact that previous research offer insightful information about the mechanical behavior and failure processes of these joints. The mechanical behavior of composite materials and the fundamentals of FEA are explained by the theoretical basis. Additionally covered are basic principles that control the behavior of bonded, riveted, and hybrid joints; they set the foundation for further investigation. The manufacturing procedure, experimental setup, and specimen preparation for testing bonded, riveted, and hybrid joints are all described in the methodology. With parameters changed to examine their influence on joint performance, finite element models are created to mimic how joints behave under different loading scenarios. Experiments on mechanical testing of joints yield useful information about failure mechanisms, stiffness, and strength. To verify the accuracy of the numerical models, these outcomes are contrasted with FEA predictions. An analysis of the variables affecting the functionality of various joint types reveals the benefits and drawbacks of each. The stress distribution, deformation, and load-carrying capability of bonded, riveted, and hybrid joints are presented by the results of finite element analysis. The results show how various joint configurations impact structural behavior, offering important information for structural integrity and design optimization. Results from FEA and experimental investigations are interpreted in the discussion, with special attention to the implications for structural applications in airplanes. The comparative study of joint types provides direction for choosing the best joint designs to satisfy particular design specifications. To sum up, this research advances our knowledge of hybrid, bonded, and riveted connections in glass fiber epoxy composite laminates used in aircraft construction. The results provide important information for creating joints that satisfy demanding aerospace performance standards, thereby improving the dependability and safety of aircraft structures.
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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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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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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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P, Prasad, Sreenivasa Murthy B. P, and Thimmegowda M. B. "Bonded Composite Laminates (E-Glass to Graphite) Failure Analysis Subjected to Axial Tension." International Journal for Research in Applied Science and Engineering Technology 12, no. 12 (December 31, 2024): 1146–55. https://doi.org/10.22214/ijraset.2024.65986.

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Abstract: Researchers studied influence of various parameters on the failure behaviour on metal and composite joints. The one of the challenge in analysis of bonded joints of dissimilar materials of the stress and strain fields at the adhesive layer and adherents. The adhesive bonded joints are most used in present technology in aerospace engineering, mechanical engineering, automotive sectors and civil engineering. This work is based on numerical tools of engineering structures adhesion problems. The proposed numerical tools are implemented Finite Element Method (FEM). A numerical methods based on finite element models can be very useful in describing the failure response of each load step. A FE investigation are carried out for composite to composite bonded joints between E-glass/epoxy to Graphite/epoxy laminates of unidirectional, 0/90/90/0 and 0/30/-30/90 layers orientations are chosen with 2 mm thickness of four layers with 75 mm overlap length. Finite element progressive ply by ply failure analysis of dissimilar composite bonded joint is the target of this study
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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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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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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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<p>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.<P>
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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.<br>"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.<br>Master of Science
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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.<br>Master of Science
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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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Radice, Joshua J. "The analysis and design of adhesively bonded composite structures." Access to citation, abstract and download form provided by ProQuest Information and Learning Company; downloadable PDF file 1.10Mb , 279 p, 2005. http://gateway.proquest.com/openurl?url_ver=Z39.88-2004&res_dat=xri:pqdiss&rft_val_fmt=info:ofi/fmt:kev:mtx:dissertation&rft_dat=xri:pqdiss:3181889.

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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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Books on the topic "Composite bonded joints"

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

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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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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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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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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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Hoeven, W. van der. Static and fatigue strength of an adhesive bonded CFRP butt-strap joint, the effects of stacking sequence and temperature. Amsterdam: National Aerospace Laboratory, 1988.

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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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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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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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Conference papers on the topic "Composite bonded joints"

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Cui, Xiaodong, Waruna Seneviratne, Nam Phan, Xiang Ren, and Jim Lua. "A Hybrid Damage Modeling and Experimental Study of Composite Tee-joints under Pull-off Loading." In Vertical Flight Society 73rd Annual Forum & Technology Display, 1–8. The Vertical Flight Society, 2017. http://dx.doi.org/10.4050/f-0073-2017-12177.

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It is a great challenge to perform an accurate and efficient fatigue life prediction of a bonded composite structure with the presence of geometry and material heterogeneity induced stress concentration. The present fatigue damage characterization of composite structures is still dominated by the use of a phenomenological stress-life (S-N) approach due to the availability of extensive S-N data and lower cost in generation of S-N data from fatigue tests at different applied stress ratios. Because of the inaccurate life prediction using the S-N approach for the structure with stress concentrators, a more rational fracture mechanics approach based on a Paris type crack growth law can be applied to compute the crack growth driving force provided that an initial flaw has to be introduced. In order to simulate both the crack initiation and propagation, a dual spring model is implemented at each nodal point where the static failure is simulated using springs of a cohesive type material model while fatigue crack propagation is calculated using springs of an elastic penalty stiffness coupled with a virtual crack closure technique (VCCT). In order to validate the dual spring model for the fatigue damage prediction, two types of Tee-joints are fabricated and tested by the National Institute for Aviation Research (NIAR) with and without a Teflon insertion. A calibration analysis is performed to determine the fatigue crack growth parameters using Tee-joints with a Teflon insert followed by the blind fatigue prediction of the specimens without a Teflon insert.
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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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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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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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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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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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