Relevant bibliographies by topics / Riveted joints

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
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Academic literature on the topic 'Riveted joints'

Author: Grafiati
Published: 4 June 2021
Last updated: 17 February 2022

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Journal articles on the topic "Riveted joints"

1

Witek, Lucjan, and Monika Lubas. "Experimental Strength Analysis of Riveted Joints Using Blind Rivets." Journal of KONES 26, no. 1 (March 1, 2019): 199–206. http://dx.doi.org/10.2478/kones-2019-0024.

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Abstract This article presents results of experimental investigations of the lap blind riveted joint. The main goal of the work is determination of destructive load of the blind riveted joints. The blind rivets were originally used in the aircraft structures where access to both sides of the riveted structure is impossible. Blind rivets are now commonly used in many branches of industry because of their low cost. Moreover, the riveting process is uncomplicated. There are many publications about analysis of strength of solid rivets in the research literature. However, the strength analysis of the blind rivets was rarely undertaken. There is the research gap in the analysis of both the strength and the load capacity of blind riveted joints. The influence of selected geometrical parameters of the joint on the stress distribution and the destructive force was not widely described in literature. The first part of the work presents a review of standards and publications related to stress and strength analysis of blind riveted joints. The next part of the study describes experimental investigations of joints. The examined specimens were made out of AW 2017 aluminum alloy, cut from 1 [mm] thick sheet. Investigated blind rivets were made out of aluminum alloy. The lap joint with one rivet and the single row five-rivet joint were investigated. Moreover, the different size of hole chamfer were considered. The experimental tests were performed with the use of Zwick-Roell tension machine. The main results of experimental investigations are ultimate shear load diagrams. The influence of both the hole chamfer and the number of rivets on destructive force and shear diagrams of blind riveted joints were in detail analysed. After shear tests, the fractured rivets were magnified in order to explain the failure phenomenon of blind rivets. In the future research works the obtained results will be used in strength analysis of the blind riveted joints using the finite element method.
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Dourado, Marco Daniel Malheiro, and José Filipe Bizarro de Meireles. "A Simplified Finite Element Riveted Lap Joint Model in Structural Dynamic Analysis." Advanced Materials Research 1016 (August 2014): 185–91. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.185.

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This paper proposes a simplified finite element model to represent a riveted lap joint in structural dynamic analysis field. The rivet is modeled byspring-damperelements. Several numerical models are studied with different quantities of rivets (1, 3 and 5) andspring-damperelements (4, 6, 8, 12, 16 and 20) per rivet. In parallel, samples of two aluminum material plates connected by different quantities of rivets (1, 3 and 5) are built and tested in order to be known its modal characteristics – natural frequencies and mode shapes. The purpose of the different settings is to get the best numerical riveted lap joint representation relatively to the experimental one. For this purpose a finite element model updating methodology is used. An evaluation of the best numerical riveted lap joint is carried out based on comparisons between the numerical model after updating and the experimental one. It is shown that the riveted lap joints composed by eight and twelvespring-damperelements per rivet have the best representation. A stiffness constant valuekis obtained for the riveted lap joints in study.
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Fortier, Vincent, Jean-E. Brunel, and Louis L Lebel. "Fastening composite structures using braided thermoplastic composite rivets." Journal of Composite Materials 54, no. 6 (August 14, 2019): 801–12. http://dx.doi.org/10.1177/0021998319867375.

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Aerospace composite material components are currently joined using heavy titanium bolts. This joining method is not ideal when considering its weight, thermal expansion, electrical conductivity, and risk of unbalanced load distribution. We propose here an innovative fastening technology using thermoplastic composite rivets. A rivet blank is heated above its melting temperature using Joule heating and is formed directly in the composite laminates by an automated process. Carbon fiber and polyamide blanks were used with two fiber architecture: 2D braid and unidirectional. The braided architecture showed superior manufacturing performance and repeatability. Joints were riveted in less than 40 s per rivet. The temperature measured in the riveted composite laminate in the vicinity of formed rivet reached only 136℃ during riveting. Double fastener lap shear testing showed breaking load of 6146 N per fastener. This joint strength is higher than comparable aluminum-riveted joints, and the specific joint strength is higher than titanium-bolted joints. With these advantages, the technology could be developed and used in the next generations of lighter, cleaner, and safer aircraft.
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Rudawska, Anna, Izabela Miturska, Dana Stančeková, and Jacek Mucha. "The strength of traditional and self-pierced riveted joints." MATEC Web of Conferences 244 (2018): 01007. http://dx.doi.org/10.1051/matecconf/201824401007.

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The objective of this study is to compare the strength of riveted joints fabricated by traditional riveting (with pre-drilled holes) and self-piercing riveting (SPR) for different types of joints. Riveted joints were produced using steel and aluminum alloy rivets and two types of sheet material: 235JR steel sheet and EN AW 6060 aluminum alloy sheet with the following dimensions: length l = 100 ± 1 mm, width b = 50 ± 1 mm and thickness g = 2 mm. For all tested types of riveted joints (pre-drilled and SPR), 5 sets of joints were fabricated, each set containing 6 samples. The sets of joints differed with respect to the number of rivets (1, 2, 3, 4 and 6 rivets), joint type (single-, three- and four-riveted joints) and lap length. For all tested joints, the highest load capacity was obtained for self-pierced riveted joints, while the lowest - for pre-drilled joints with aluminum alloy rivets. In addition, it was found that the shear strength of self-pierced riveted joints is higher than that of aluminum and steel blind rivets.
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Liu, Jintong, Anan Zhao, Zhenzheng Ke, Zhendong Zhu, and Yunbo Bi. "Influence of Rivet Diameter and Pitch on the Fatigue Performance of Riveted Lap Joints Based on Stress Distribution Analysis." Materials 13, no. 16 (August 16, 2020): 3625. http://dx.doi.org/10.3390/ma13163625.

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Interference-fit riveting is one of the most widely used mechanical joining ways in aircraft assembly. The fatigue performance of riveted joints has a significant impact on the service life and reliability of aircraft. In this paper, the fatigue performance of the riveted lap joints with various rivet diameters and pitches are studied based on stress distribution analysis under tensile load. First, a theoretical model of the riveted lap joint under tensile load is developed by using the spring-mass model. The rivet-load stress, bypass stress, and interference stress around the riveted hole are analyzed. Then, the finite element (FE) model of riveted lap joints are established. The influence of rivet diameter and pitch on stress distribution around the riveted hole are discussed. Finally, the fatigue tests are conducted with riveted lap joint specimens to verify the theoretical model and FE results, and a good agreement is observed. Based on the simulation and experimental results, a good combination of structural parameters of the riveted lap joint is found which can optimize the stress distribution around the riveted hole and improve the fatigue life of the riveted lap joint.
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Rośkowicz, Marek, Jan Godzimirski, Michał Jasztal, and Jarosław Gąsior. "Improvement of fatigue life of riveted joints in helicopter airframes." Eksploatacja i Niezawodnosc - Maintenance and Reliability 23, no. 1 (January 2, 2021): 167–75. http://dx.doi.org/10.17531/ein.2021.1.17.

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Using original cold-formed rivets in repairs of airframes of helicopters is difficult due to no access to inside parts of the airframe. Thus, the main aim of the study was to investigate the possibility to use the blind rivets or hybrid joints by verification the fatigue performance of such joints that must be better than with original rivets. Riveted and hybrid joints have been experimentally tested under static and fatigue loads. Furthermore, numerical calculations of stress distribution for strapped joint have been conducted. The test results covered fatigue life of lap joints and models of repaired airframe sheets using ordinary mushroom head rivets ref. 3558A-4-10, titanium driven blind bolts with pin, ref. MBF2110AB-05-150 and modified hybrid joints. Using titanium driven blind bolts with pin instead of ordinary hammer-bucked rivets, can improve the fatigue life of element made of aluminum alloy AW 2024T3. There are advantages of replacing riveted joints with modified hybrid (rivet & adhesive) joints in threefold increase in fatigue life of repaired airframe structures.
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Yu, Haidong, Bin Zheng, Xun Xu, and Xinmin Lai. "Residual stress and fatigue behavior of riveted lap joints with various riveting sequences, rivet patterns, and pitches." Proceedings of the Institution of Mechanical Engineers, Part B: Journal of Engineering Manufacture 233, no. 12 (March 8, 2019): 2306–19. http://dx.doi.org/10.1177/0954405419834481.

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The residual stress of multi-rivet structures is related with the riveting sequence, the rivet pattern, and the pitch due to the deformation interaction of different rivets. The stress amplitude of riveted structures subjected to the cyclic loads is affected by the residual stress, which increases the difficulty in the prediction of fatigue life. In this article, the riveting processes for single-row and triple-row riveted lap joints with various riveting sequences, rivet patterns, and pitches are studied numerically and experimentally. The residual stresses for both types of riveted structures are verified by the testing data. Significant difference appears in the residual stress field for riveted lap joints with various riveting sequences and rivet patterns. The decrease in the rivet pitch increases the compressive residual stress at the edge of the rivet hole. Furthermore, the fatigue life prediction model is developed for multi-rivet structures, in which the coupling effect of residual stress and cyclic load is considered. The fatigue experiments are conducted for riveted lap joints with various riveting sequences, rivet patterns, and pitches. The accuracies of the numerical results obtained from the Homan model and the developed model are compared with the experimental data. The proposed fatigue model shows better performance to predict fatigue life for multiple rivet structures.
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Kondo, Atsushi, Toshiyuki Kasahara, and Atsushi Kanda. "A Simplified Finite Element Model of Riveted Joints for Structural Analyses with Consideration of Nonlinear Load-Transfer Characteristics." Aerospace 8, no. 7 (July 19, 2021): 196. http://dx.doi.org/10.3390/aerospace8070196.

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A simplified finite element model of riveted joints for structural analyses which effectively incorporates nonlinear response of riveted joints is proposed. Load-transfer characteristics of riveted joints were experimentally and numerically studied. First, a detailed finite element analysis for the process of a tensile test of a single-row joint which consists of squeezing of the rivet and tensile loading to the joint was conducted to confirm the validity of a conventional method of analysis. The load–relative displacement behaviors of single-row joints observed in the detailed finite element analysis and previously conducted experiments agreed well. Then, a simplified method of the analysis was developed based on the detailed analysis and the experiments and was applied to analyses of multiple-row joints. A nonlinear relationship between load and relative displacement in the simplified analyses had good agreement with the detailed one. Distributed loads to the multiple rivets in the simplified analysis coincided with those of the detailed analysis under the maximum load. Memory and CPU time required to run the simplified analyses were reduced to about 1/4 and 1/6 compared to those of the detailed analysis, respectively.
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Sadowski, T., and E. Zarzeka-Raczkowska. "Hybrid Adhesive Bonded and Riveted Joints – Influence of Rivet Geometrical Layout on Strength of Joints / Połączenia Hybrydowe Klejowo-Nitowe - Wpływ Geometrii Rozmieszczenia Nitów Na Wytrzymałość Połączeń." Archives of Metallurgy and Materials 57, no. 4 (December 1, 2012): 1127–35. http://dx.doi.org/10.2478/v10172-012-0126-0.

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The hybrid adhesive bonded and riveted joints have wider and wider application in different branches of engineering: aerospace, mechanical, civil etc. The hybrid joints’ strength is 1.5 to 3 times higher than only adhesive bonded joints’ strength. The hybrid joints characterize higher reliability during long-term working. In this article we present the influence of rivets’ lay-out geometry on the hybrid adhesive bonded/riveted joints response to mechanical loading. Experimental research was carried using 3-D digital image correlation system ARAMIS. This system enables monitoring of the deformation processes of the hybrid joint specimen up to failure. We analysed the state of deformation of the adhesive bonded double-lap joints reinforced by different numbers of rivets. The hybrid joint specimens were subjected to the uniaxial tensile test. Moreover, the influence of geometry of individual number of rivets’ layout (rivets arranged in one or more rows) for hybrid joint strength was studied. Experimental research was completed and supported by the computer simulations of the whole deformation processes of metal layers (aluminum), adhesive layers and rivets. Numerical simulations were conducted with the ABAQUS programme. The analysis of stress concentrations in different parts of the hybrid joint and their behaviour up to failure were investigated. Finally, the analysis and the comparison of the obtained results confirmed the influence of rivets’ lay-out geometry not only on rivets joints but also on the hybrid adhesive bonded/riveted joints.
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Mucha, Jacek, and Waldemar Witkowski. "The Structure of the Strength of Riveted Joints Determined in the Lap Joint Tensile Shear Test." Acta Mechanica et Automatica 9, no. 1 (March 1, 2015): 44–49. http://dx.doi.org/10.1515/ama-2015-0009.

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Abstract The article presents the analysis of the structure of the load capacity of riveted joints. For the four joining systems the lap joint specimens were made and tested in the shearing test. The joints were prepared for the three combinations of the DC01 steel and EN AW- 5754 aluminium alloy sheets with the thickness of 2mm. On the basis of the obtained load-elongation diagram tensile shear test curves, the basic parameters defined in the ISO/DIS 12996 standard were determined. In the case of the conventional riveted joints the maximum load capacity of the joint is determined by the strength of the fastener. For the joints with aluminium-steel blind rivet , the load capacity of the joint was on the strength limit of the rivet tubular part and on the strength limit of the sheet material. The strength of the SSPR joint is determined by the mechanical properties of the material of the joined sheets. From all sheets and rivet specimens arrangements the highest load capacity of the joint was obtained for the DC01 sheet material joints, and the lowest load capacity of the joint was obtained for the EN AW-5754 sheet material joints.
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Dissertations / Theses on the topic "Riveted joints"

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Kecelioglu, Galip. "Stress And Fracture Analysis Of Riveted Joints." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/12610132/index.pdf.

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The objective of this study is to model and analyze a three dimensional single riveted lap joint (with and without a crack). By using finite element method, stress and fracture analyses are carried out under both the residual stress field and external tensile loading. Using a two step simulation, riveting process and subsequent tensile loading of the lap joint are simulated to determine the residual and overall stress state. Residual stress state due to riveting is obtained by interference and clamping misfit method. By employing different interference and clamping misfit values, the effects of riveting process parameters on stress state are examined. Two cracks namely the semi elliptical surface crack at faying surfaces of plates and the quarter elliptical corner crack at rivet hole are the most widely observed crack types in riveted joints. Fracture analysis of cracked riveted joints is carried out by introducing these two crack types to the outer plate at a plane perpendicular to the loading. The mixed mode stress intensity factors (SIFs) and energy release rates (G) around the crack front are obtained by using displacement correlation technique (DCT). Effects riveting process parameters (interference and clamping ratios) and geometrical parameters (crack shape and size) on fracture parameters are studied. The stress intensity factor solutions presented herein could be useful for correlating fatigue crack growth rates, fracture toughness computation, and multiple site damage (MSD) analysis in aircraft bodies.
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Garcia, Abilio Neves. "Multiple site damage of aeronautical riveted joints." Thesis, Cranfield University, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.427165.

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Han, Li. "Mechanical behaviour of self-piercing riveted aluminium joints." Thesis, University of Hertfordshire, 2003. http://hdl.handle.net/2299/14159.

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The introduction of alternative materials and in particular aluminium alloys, for vehicle body applications has impelled the development of new joining techniques. Traditional joining methods such as spot-welding and arc-welding are being challenged. Self-piercing riveting has attracted considerable interest by the automotive industry and has been used as an alternative to spot-welding in vehicle body assembly. However, self-piercing riveting is a relatively new joining method and as such it is not well understood. The aim of this project was therefore to develop an understanding of the mechanical behaviour of self-piercing riveted joints. The effects of paint-baking, shelf-life, pre-straining and surface condition of the sheet material on the joint quality and behaviour were therefore examined. Aluminium alloy sheet materials, 5754 and AA6111, were used in this investigation. The project began with a metallographic inspection of cross-sections of samples that were joined under different conditions in order to examine the effect of process variables on the joint quality. This part of the investigation led to the identification of suitable setting parameters that produced joints which, by metallographic inspection, were of good quality. It was also observed that some process variables, such as sheet thickness combination, rivet and die design and setting force, affected the joint quality and therefore needed to be taken into consideration in the choice of the processing parameters. Subsequent work focused on mechanical testing. Lap shear, T-peel, pull-out and fatigue tests were carried out in order to examine the mechanical behaviour and to analyse the failure mechanisms of the joints. The work showed that the strength, the thickness and the surface condition of the riveted sheets affected the strength and the failure mechanisms of the joints. The joint strength was also observed to be dependent on the rivet and anvil design as well as the setting force. In addition, the joint strength and behaviour differed as the specimen geometry thus emphasising the need for a test standard for self-piercing riveted joints. Paint baking led to a marginal and insignificant reduction in the static strength, whilst resulting in a reduction in the fatigue strength of the joints as a consequence of recovery of the 5754 alloy and the removal of the wax-based surface lubricant. The effect of 3%, 5% and 10% pre-straining of the 5754 sheet on the quality and performance of the self-piercing riveted joints was also examined. It was established that it was possible to produce joints of good quality, higher strength and superior fatigue performance by using the same setting parameters as for joints without additional pre-straining. An investigation of the effect of the shelf-life of AA6111 indicated that this only had a minor and insignificant effect on the joint quality and behaviour. It was therefore deduced that the quality and performance of joints would not be compromised even after an AA6111 self-life of 21 months. The effect of the interfacial characteristics on the joint quality and behaviour was examined by placing a PTFE layer at the interface between the riveted sheets. It was observed that the PTFE insert significantly reduced the joint strength and changed the failure mechanism. Three distinct failure modes, referred to as rivet pull-out, rivet fracture and sheet material failure, were observed during this investigation. All shear tested samples failed by rivet pull-out. The same failure mechanism was the only one observed for the pull-out tests. The failure mechanism for the peel test depended on the thickness of the rivet sheet. For joints with a (1 mm+2mm)/(0.9mm+2mm) combination, fracture of the thinner sheet material dominated the failure mechanism, whilst for joints with a (2mm+2mm) combination, rivet pull-out was the only failure system. Rivet fracture and sheet material failure were also observed during fatigue testing. Examination of samples following fatigue testing led to the observation of fretting which had not been reported by previous investigators working with self-piercing rivets. Fretting had an important effect on the fatigue strength and fatigue failure mechanisms. Inspection of fatigue fractured samples which were tested at maximum applied loads ranging from 50% to 85% of the ultimate shear load of the joints exhibited fretting scars at three different interfaces. Flange-face fretting was observed to take place at one side of the interface between the two riveted sheets and led to the formation of mainly A1203 debris. Pin-bore fretting was observed to occur between the rivet shank and the aluminium alloy sheet and led to debris containing oxides of aluminium and iron together with the oxides of zinc and tin from the wear of the corrosion protective coating of the rivet. Both types of fretting were affected by the applied load and the surface condition of the riveted sheets. Further examination indicated that fretting contributed to the initiation and propagation of fatigue cracks. The failure modes during fatigue testing were affected by the fretting behaviour and were dependent on the applied load and the interfacial conditions. A PTFE layer introduced a very low coefficient of friction leading to a significantly reduction in the amount of fretting. However, this was accompanied with a change in the load transfer mechanism resulting in rivet fracture and a shorter fatigue life. The paint-baking process led to the removal of the wax-based surface lubricant and fretting cracks therefore initiated at an earlier stage of the fatigue test. In addition, fretting also led to a significant work-hardening of the riveted sheets. It was observed that there was an increase in microhardness at the regions immediately below the fretting area from the riveted sheets. The depth of the work-hardened area below the fretting interface after different periods of fretting represented the depth of damage as a result of fretting fatigue. It was therefore further indicated that fretting played an important role in the fatigue behaviour and would probably affect the crash behaviour of the joints. The effect of secondary bending, an inherent feature of lap joints, was examined and analysed using strain gauge measurements. It was established that secondary bending contributed to the failure mechanism and led to a significant reduction in the fatigue strength of such joints. Using the experimental data an analysis has been carried out to predict the fatigue strength in the absence of secondary bending.
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Abdulla, Warda Ibrahim. "FATIGUE BEHAVIOR AND SCALE EFFECTS IN RIVETED JOINTS." University of Akron / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=akron161651595564376.

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Scott, Jason P. "Corrosion and multiple site damage in riveted fuselage lap joints." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1997. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp04/mq22127.pdf.

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Scott, Jason P. (Jason Philip) Carleton University Dissertation Engineering Mechanical and Aerospace. "Corrosion and multiple site damage in riveted fuselage lap joints." Ottawa, 1997.

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Ioannou, John. "Mechanical behaviour and corrosion of interstitial-free steel-aluminium alloy self-piercing riveted joints." Thesis, University of Hertfordshire, 2010. http://hdl.handle.net/2299/4611.

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The overall aim of the project is to examine the rivetability of new steels and to investigate the mechanical behaviour of self-piercing riveted (SPR) aluminium-steel hybrid structures for automotive applications. Interstitial Free Steel (I.F.) of 1.2 mm thickness was joined to Aluminium 5754 of 2 mm thickness and Aluminium 5182 (coated and uncoated) of 1.5 mm thickness. The work began by initially conducting a quality assessment of the various joints that were produced in order to establish the optimum conditions for joining the various sample combinations to be investigated. A relationship was established between the head height and the interlock distance on the one hand and between the interlock distance and the lap shear strength of samples. It was also established that for higher lap shear strength, it is preferable to use the stronger material (I.F. steel) as the pierced sheet and the weaker material (5182) as the locked sheet. However, the results showed that this rule could not be applied for predicting the fatigue behaviour of SPR joints between I.F. steel and 5182. An investigation of the fatigue failure mechanisms was undertaken and possible reasons for this behaviour are discussed. The influence of fretting was also investigated by using scanning electron microscopy and reported. The fatigue behaviour of Dual Phase (DP600 + 5182) SPR joints was investigated. It was observed that the position of fatigue crack initiation differed with the maximum applied load. An explanation for this observation was provided by considering the failure mechanism of the samples under different load levels. The study also showed how fretting led to the initiation of fatigue cracks. The corrosion behaviour of (I.F. steel + 5182) samples was investigated by conducting tests in a salt spray according to the ASTM B117-97 standard. Three types of corrosion were observed; galvanic corrosion, differential aeration corrosion, uniform corrosion and are discussed. The weight change with time was monitored and was used to describe the corrosion behaviour. The lap shear strength was measured as a function of corrosion time. The presence of the corrosion product within the overlap was observed to greatly influence the lap shear strength behaviour. A further study was carried out in order to examine the influence of the individual alloys on the corrosion of the SPR samples. In this part the potential influence of pulse current treatment on corrosion was also investigated and was observed to increase greatly the corrosion resistance of the I.F. steel. Principal findings for this observation are also provided.
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Bajracharya, Bijay Cheraghi Hossein Krishnan Krishna. "Effect of variations of riveting process on the quality of riveted joints." Diss., Click here for available full-text of this thesis, 2006. http://library.wichita.edu/digitallibrary/etd/2006/t085.pdf.

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Thesis (M.S.)--Wichita State University, Dept. of Industrial and Manufacturing Engineering.
" December 2006." Title from PDF title page (viewed on January 29, 2007). Thesis advisers: Hossein Cheraghi, Krishna Krishnan. Includes bibliographic references (leaves 62-64).
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Atre, Amarendra. "A Finite Element and Experimental Investigation on the Fatigue of Riveted Lap Joints in Aircraft Applications." Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/10494.

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Aircraft fuselage skin panels are joined together by rivets. The initiation and propagation of fatigue cracks in aircraft structures at and around the rivet/skin interface is directly related to residual stress field induced during the riveting process and subsequent service loads. Variations in the manufacturing process, such as applied loading and presence of sealant can influence the induced residual stress field. In previous research, the riveting process has been simulated by a 2D axisymmetric force-controlled analysis. The 2D analysis cannot capture the unsymmetrical residual stress state resulting from process variations. Experimental work has also been limited to observing effects of squeeze force on fatigue crack initiation in the riveted lap joint. In this work, a 3D finite element model of the riveting process that incorporates plasticity and contact between the various surfaces is simulated using ABAQUS finite element code to capture the residual stress state at the rivet/skin interface. The finite element model is implemented to observe the effects of interference, sealant and hole quality on the residual stress state using Implicit and Explicit solvers. Effects of subsequent load transfer are also analyzed with the developed model. A set of controlled lap joint fatigue experiments for the different conditions provides validation to the model.
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Borba, Natascha Zocoller [Verfasser]. "Design and mechanical integrity of friction riveted joints of thermoplastic composite / Natascha Zocoller Borba." Hamburg : Universitätsbibliothek der Technischen Universität Hamburg-Harburg, 2020. http://d-nb.info/1219963526/34.

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Books on the topic "Riveted joints"

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Skorupa, Andrzej, and Malgorzata Skorupa. Riveted Lap Joints in Aircraft Fuselage. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-4282-6.

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Kulak, Geoffrey L. Guide to design criteria for bolted and riveted joints. 2nd ed. New York: Wiley, 1987.

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Adamson, Daniel Edward Joseph. Fatigue tests of riveted bridge girders. Edmonton, Canada: University of Alberta, Dept. of Civil Engineering, 1995.

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DiBattista, Jeffrey D. Fatigue of riveted tension members. Edmonton: Dept. of Civil Engineering, University of Alberta, 1995.

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Åkesson, B. Fatigue life of riveted steel bridges. Boca Raton, Fla: CRC Press/Balkema, 2010.

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Wolfe, Ronald W. Timber rivets in structural composite lumber. Madison, WI: U.S. Dept. of Agriculture, Forest Service, Forest Products Laboratory, 2004.

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Fatigue life of riveted steel bridges. Boca Raton, Fla: CRC Press/Balkema, 2010.

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Skorupa, Andrzej. Riveted Lap Joints in Aircraft Fuselage: Design, Analysis and Properties. Dordrecht: Springer Netherlands, 2012.

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Fung, Chin-Ping. An experimental and numerical study of riveted single lap joints. Manchester: University of Manchester, 1994.

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Piascik, Robert S. The characteristics of fatigue damage in the fuselage riveted lap splice joint. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Book chapters on the topic "Riveted joints"

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Homan, J. J., R. P. G. Müller, F. Pellenkoft, and J. J. M. de Rijck. "Fatigue of riveted joints." In Fibre Metal Laminates, 173–95. Dordrecht: Springer Netherlands, 2001. http://dx.doi.org/10.1007/978-94-010-0995-9_12.

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Josephs, Harold, and Ronald L. Huston. "Riveted and Bolted Joints." In Blake’s Design of Mechanical Joints, 135–76. Second edition. | Boca Raton: CRC Press, Taylor & Francis, 2019. | Series: Mechanical engineering | Revised edition of: Design of mechanical joints / Alexander Blake. c1985.: CRC Press, 2018. http://dx.doi.org/10.1201/9781315153827-5.

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Altuntop, Elif, Murat Aykan, and Melin Şahin. "Parameter Identification of Riveted Joints Using Vibration Methods." In Shock & Vibration, Aircraft/Aerospace, and Energy Harvesting, Volume 9, 47–53. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-15233-2_6.

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Skorupa, Andrzej, and Małgorzata Skorupa. "Riveted Lap Joints in a Pressurized Aircraft Fuselage." In Solid Mechanics and Its Applications, 1–9. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-4282-6_1.

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He, Xiao Cong, Ian Pearson, and Ken W. Young. "Finite Element Analysis of Self-Pierce Riveted Joints." In Sheet Metal 2007, 663–68. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-437-5.663.

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Skorupa, Andrzej, and Małgorzata Skorupa. "Multiple-Site Damage in Riveted Lap Joints – Experimental Observations." In Solid Mechanics and Its Applications, 207–40. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-4282-6_8.

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Horst, Peter. "Assessment of Multiple Site Damage in Riveted Aircraft Joints." In Structural Connections for Lightweight Metallic Structures, 1–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/8611_2010_50.

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Skorupa, Andrzej, and Małgorzata Skorupa. "Residual Strength Predictions for Riveted Lap Joints in Fuselage Structures." In Solid Mechanics and Its Applications, 273–314. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-4282-6_10.

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Skorupa, Andrzej, and Małgorzata Skorupa. "Production Variables Influencing the Fatigue Behaviour of Riveted Lap Joints." In Solid Mechanics and Its Applications, 27–100. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-4282-6_3.

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Skorupa, Andrzej, and Małgorzata Skorupa. "Design Parameters Influencing the Fatigue Behaviour of Riveted Lap Joints." In Solid Mechanics and Its Applications, 101–14. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-4282-6_4.

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Conference papers on the topic "Riveted joints"

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Ferracci, Michele, Francesco Vivio, and Vincenzo Vullo. "Structural Analysis of Riveted Structures Using a New FE Modelling Technique." In ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2010. http://dx.doi.org/10.1115/esda2010-24875.

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A theoretical approach, in order to define the structural behaviour of riveted joints, is presented. The closed form solutions lead to the definition of a Rivet Element useful to FE models of multi-riveted structures. The objective is an accurate evaluation of the local stiffness of riveted joints in FE analysis, which is fundamental to perform a reliable simulation of multi-joint structures and, consequently, a good estimate of loads acting on connections; this makes it possible to introduce new general criteria allowing, for example, to predict fatigue behaviour. On the other hand, a low number of degrees of freedom is needed when several connections are present in a complex structure. The goal is to reach a reliable model of the rivet region which can be used as the basis to develop a Rivet Element in FE analysis. The proposed Rivet Element combines the precision in the simulation with a very limited number degrees of freedom in the finite element model of a complex structure having several rivets. In the present paper the structural behavior of two simple riveted specimens is investigated experimentally and numerically using a new Rivet Element. A comparison with a joint model performed with very refined non-linear 3D models of rivet and with experimental data is performed and a good agreement is shown.
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Notohardjono, Budy, Richard Ecker, and Shawn Canfield. "Dynamics Modeling and Analysis of Riveted Mainframe Computer Structure." In ASME 2017 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/pvp2017-65140.

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A typical mainframe computer rack is narrow, tall and long. In certain installations, during its functional operation, the server can be subjected to earthquake events. The rack is a steel structure joined together with steel rivets. One of the rack’s functions is to protect the critical components such as the processor, input-output and storage drawers from excessive motion by minimizing the amount of deflection. The riveted joints pose a challenge in accurately representing more than three thousand joints in a finite element (FE) model. In the FE model, bonding together sheet metal regions around the rivet joints will lead to a significantly stiffer model than the actual structure. On the other hand, an accurate representation of the riveted joints will lead to a better representation of the dynamic response of the server rack under vertical and horizontal loadings. This paper presents a method of analyzing rivet joints. The rivet joints are represented by beam elements with cylindrical cross-sections in the FE model. This is accomplished by identifying two parallel or overlapping plates and inserting discrete beam elements at the riveted joint. This method will be used to predict the dynamics modes of the structure. To validate the FE model, a prototype server rack was subjected to side to side vibration tests. A sine sweep vibration test identifies dominant mode shapes and the transmissibility of the input vibration. The results of the tests on the prototype rack serve as input for FE model refinement. The test data show that representing the riveted joints with beams does provide results that closely match the actual test data. A validated FE model will be used to evaluate dominant vibration modes for several configurations of rack weight as well as configurations to stiffen the structure in the side to side direction. The dynamic mode shapes visualize the effect of stiffening brackets on dominant frequencies of the rack. The optimal stiffening design will be the one that results in the minimum deflection under the standard testing profile.
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Sawa, Toshiyuki, and Ryo Nogaito. "FEM Stress Analysis and Strength of Adhesive-Rivets Combination Joints Under Tensile Shear Loadings." In ASME 2007 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/detc2007-34455.

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Stress distributions in adhesive-rivets combination joints under tensile shear loadings are analyzed using a three-dimensional finite element method. The effects of the adherend thickness, the number of rivets and the rivet locations on the stress distributions at the interfaces are examined. Experiments to measure the rupture loads of the joints were carried out. As the results, it was found that the peel stress near the edges of the interfaces decreased as the adherend thickness increased. The maximum value of the maximum principal stresses near the edges of the interfaces decreased as the interval between the two rivets in the longitudinal direction decreased in the case where two rivets were combined. However, small effect of the interval between the two rivets in the lateral direction was found in the case of two rivets. The maximum value of the maximum principal stresses near the edges of the interfaces decreased as the interval between the four rivets in the longitudinal direction decreased and that in the lateral direction increased in the case where four rivets were combined. Discussion on the rupture loads of adhesive-rivets combination joints was made. The rupture loads of the joints increased as the number of rivets increased. The rupture loads of the adhesive-rivets combination joints could be increased more than those of only-riveted joints in the case of two rivets. The rupture loads of adhesive-rivets combination joints were found to be almost the same as those of only-riveted joints in the case of four rivets.
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Vivio, Francesco, and Michele Ferracci. "Modelling of Riveted Joints with a New Rivet Element." In SAE World Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2009. http://dx.doi.org/10.4271/2009-01-0025.

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Han, L., K. Young, R. Hewitt, A. Chrysanthou, and J. M. O’Sullivan. "Fatigue Failure Modes in Self-Piercing Riveted Aluminium Alloy Joints." In ASME 7th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2004. http://dx.doi.org/10.1115/esda2004-58320.

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Self-piercing riveting, as an alternative joining method to spot-welding, has attracted considerable interest from the automotive industry and has been widely used in aluminium intensive vehicles. One of the important factors that need to be considered is the effect of cyclic loading in service, leading to possible fatigue failure. The previous work reported in the public domain on the behaviour of self-piercing rivets has mainly focused on static tests. The work which is reported in this paper is concerned with the fatigue behaviour of single-rivet joints, joining two 2mm 5754 aluminium alloy sheets. The investigation also examined the effect of interfacial conditions on the fatigue behaviour. A number of fatigue failure mechanisms were observed based on rivet fracture, sheet fracture and combinations of these. The investigation has shown that they were dependent on the applied load and the sheet surface condition. Three-parameter Weibull analysis, using Reliasoft Weibull ++5.0 software, was conducted to analyse the experimental results. The analysis enabled the prediction of early-type failure (infant mortality failure) and wear-out failure patterns depending on the condition of the self-piercing riveted joints and the alloy sheet surface.
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Rodrigues Felix, Gabriel, Luiz Henrique Jorge Machado, and Juliana Souza. "STRENGTH TEST OF RIVETED OVERLAP JOINTS." In 25th International Congress of Mechanical Engineering. ABCM, 2019. http://dx.doi.org/10.26678/abcm.cobem2019.cob2019-0749.

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Mehlsen, Henrik. "Fatigue Assessment of Existing Riveted Bridges." In IABSE Conference, Copenhagen 2018: Engineering the Past, to Meet the Needs of the Future. Zurich, Switzerland: International Association for Bridge and Structural Engineering (IABSE), 2018. http://dx.doi.org/10.2749/copenhagen.2018.031.

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Fatigue failure of bridges occurs after repeated loading and unloading and hence fatigue becomes more and more severe with time. A majority of all existing riveted bridges are not explicitly designed for fatigue failures. Bridge owners should therefore have focus on fatigue life of riveted bridges. It can be difficult to discover fatigue cracks by visual inspection due to thick layers of paint and the fact that the rivets themselves may hide the cracks. Hence, it may be necessary to determine critical joints and possible fatigue cracks by using FE-modelling. Identification of critical joints may also target future inspection efforts and highlight hidden details, which may call for special inspection measures to be implemented. This paper describes a fatigue study of 11 riveted railway bridges in Denmark that includes both visual inspections and FE-modelling of bridges.
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Iyer, K., F. L. Brittman, S. J. Hu, P. C. Wang, D. B. Hayden, and S. P. Marin. "Fatigue and Fretting of Self-Piercing Riveted Joints." In ASME 2002 International Mechanical Engineering Congress and Exposition. ASMEDC, 2002. http://dx.doi.org/10.1115/imece2002-32336.

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The fatigue life and fretting characteristics of aluminum alloy 5754-O self-piercing riveted lap joints have been investigated experimentally and analytically. The experimental program involves a set of 27 cyclic tension tests on three different joints consisting of either 1 mm, 2 mm or 3 mm-thick sheet specimens. In most cases (85%), fatigue cracks are found to initiate on the faying surface of the upper sheet, adjacent to the hole, and at an angular location that lies on the sheet loading axis towards the loading end. Three-dimensional finite element analysis of the three joints has also been performed. Computed distributions of local stresses and rivet-sheet slips are interpreted in terms of experimental observations of fatigue life, crack initiation location and fretting damage observations. Significantly, the calculations provide a rationale for the surprising crack initiation location.
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Brar, Gurinder Singh, Yogeshwar Hari, and Akhil Deep Ayri. "Effect of Temperature Variation on the Service Life of a Riveted Joint." In ASME 2015 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/pvp2015-46012.

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Rivets are widely used as a means of fastening in airframe construction industry. Among the other types of fasteners riveted joints are preferred in such applications due to their permanence after installation and their economical advantages. In a riveted joint, it is known that residual stresses are present as a result of the installation process. Furthermore, during the flight of an aircraft, the fuselage comes across pressurization and depressurization cycle. During one flight pressurization-depressurization cycle is completed and such cycles are repeated throughout the service life of the aircraft. As a result, the panels and the rivets are subjected to fatigue type loading. The integrity of the joint must be maintained against this combination of service loads and the residual stresses. The present study is aimed to develop and analyze three-dimensional finite element model of riveted lap, and then the numerical analysis (SolidWorks Simulation) are carried out to calculate the residual stress values and fatigue values in the riveted lap joint under the effect of varying temperature. The result shows that the fatigue life varies inversely proportion to residual stresses whereas damage varies directly proportion to residual stresses. The maximum residual stress obtained is 292 MPa at temperature of 150°C and the minimum residual stress obtained is 15 MPa at temperature of −50°C. Maximum damage is 60% at 150°C and minimum is 8% at −50°C. Maximum life is 234346 cycles at −50°C and minimum life is 33111 cycles at 150°C.
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Chang, Zhengping, Zhongqi Wang, Jinming Zhang, Yuan Yang, and Yonggang Kang. "Investigation of Riveting Parameters Influence on the Riveted Joints Deformation During Slug Rivet Installation." In ASME 2016 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/imece2016-66618.

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Slug rivet is widely used in aircraft assembly due to the higher interference fit level and the longer fatigue life. However, the inhomogeneity of riveting interference value along the thickness direction of the aircraft panels always leads to inevitable deformation, which significantly degrades the dimensional accuracy of the final products. In this study, a quantitative model is established to describe the relationship between several riveting parameters (i.e. squeezing force, buck cavity, upsetting rise time, upsetting dwell time and clamping force between sheets) and the deformation of a formed slug rivet joint. Then the coefficient of variance (CV) is introduced to evaluate the homogeneity of deformation. Subsequently, an optimized combination of the presented parameters is obtained by using finite element method (FEM) simulation so as to generate more uniform deformation. Finally, the FEM model is validated by a series of orthogonal experiments conducted in G86 fully automated C-frame riveting machine and the results show that the squeezing force and the buck cavity are the main significant factors and contributors to the riveted joints deformation, and the sequence of this effect from the high to low are: upsetting dwell time, clamping force, and upsetting rise time. The results also indicate that the developed FE model can be used for further analysis, including the prediction of large component riveting deformation and the mechanical properties of riveted joint.
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Reports on the topic "Riveted joints"

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Han, Li, Ken William Young, Richard Hewitt, and Andreas Chrysanthou. The Effect of Breakthrough on the Mechanical Behavior of Self-Piercing Riveted Aluminum 5754-HSLA Joints. Warrendale, PA: SAE International, May 2005. http://dx.doi.org/10.4271/2005-08-0203.

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Doi, Shigeru, and Takao Mori. Tensile Shear Strength of Aluminum-Steel Rivet Joint. Warrendale, PA: SAE International, September 2005. http://dx.doi.org/10.4271/2005-08-0540.

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