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Journal articles on the topic 'Riveted joints'

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

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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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2

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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3

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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4

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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5

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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6

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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7

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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8

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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9

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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10

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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11

Sadowski, Tomasz, and Przemysław Golewski. "Effect of Tolerance in the Fitting of Rivets in the Holes of Double Lap Joints Subjected to Uniaxial Tension." Key Engineering Materials 607 (April 2014): 49–54. http://dx.doi.org/10.4028/www.scientific.net/kem.607.49.

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The study focused mainly on one of the parameters of mount technology - tolerance for fitting the rivet in the hole in riveted and hybrid (riveted adhesive) joints. The research included numerical simulations of double lap joints with four rivets arranged in two rows and subjected to uniaxial tension. Simulations were carried out in Abaqus both for the purely mechanical and the hybrid joints. The connections without clearance (neat-fit) and with clearance of 0.2 mm, as well as with interference of-0.2 mm. The presence of clearance in one of the holes in the hybrid joint causes a decrease in the capacity of the hybrid connection by about 15% in configuration 1 (Fig. 2). This decrease can be even higher (21%) in the worse clearance placement, i.e. in configuration 2 (Fig. 2). The study shows that the occurrence of clearance in the holes can lead to dangerous consequences, so it is recommended to use holes calibration or develop a special type of rivet.
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12

LEONTYEV, V. V. "ANALYSIS OF THE STRESS-STRAIN STATE OF A RIVET JOINT USING THE ABAQUS CAE SYSTEM." Fundamental and Applied Problems of Engineering and Technology 6 (2020): 51–57. http://dx.doi.org/10.33979/2073-7408-2020-344-6-51-57.

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The method for analyzing of stress-strain state characteristics of unloaded riveted joints performed with OST 1 11781-74 rivets has been developed using Coupled Euler-Lagrange finite element approach implemented in the CAD / CAE system Abaqus. A comparative analysis of the stress-strain state characteristics of the examined riveted joint’s finite element models using the Lagrangian and the Coupled Lagrangian-Eulerian finite element approaches has been conducted. A three- dimensional finite element model based on the CLE method has been proposed for further study of fatigue strength and durability of the loaded riveted joints.
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13

Machniewicz, Tomasz, Małgorzata Skorupa, Andrzej Skorupa, and Adam Korbel. "Applicability of Empirical Formulae for the Fatigue Notch Factor to Estimate Riveted Lap Joint Fatigue Strength." Solid State Phenomena 224 (November 2014): 81–86. http://dx.doi.org/10.4028/www.scientific.net/ssp.224.81.

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A semi-empirical fatigue life prediction model under development by the present authors for riveted lap joints used in aircraft structures is outlined. In contrast to existing models, it will account for the influence of the rivet squeeze force on the fatigue life of riveted joints. To determine the effect of rivet-hole interference on the fatigue behaviour of a riveted joint, a series of fatigue tests on filled hole coupons with different amounts of interference will be carried out under loading conditions representing the bypass load, transfer load and secondary bending. These experiments will allow evaluating of the dependency of the fatigue notch factors on rivet hole expansion. Preliminary results obtained so far are presented in this paper.
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14

Černý, Michal, and Josef Filípek. "Corrosion damage of rivet joints." Acta Universitatis Agriculturae et Silviculturae Mendelianae Brunensis 56, no. 4 (2008): 37–46. http://dx.doi.org/10.11118/actaun200856040037.

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The work describes the effect of the atmospheric corrosion upon the mechanical properties of blind rivets. The subject of given research is: corrosion of metal materials, system resistance, design modification and others means of prevention against the corrosion attack. The problem of blind rivets, blind rivet setting, setting equipment, terminology and definitions, characteristic, and special blind rivet setting is also analysed. The experiment itself, the experimental method and the evaluation of the test are described. Mechanism of riveted joint damage produced by galvanic corrosion is proposed. Considerable corrosion damage occurred at combination of the joint members and connected materials with different electrochemical potentials. Exposition to the corroding environment produces release of rivet clam, together with decrease of rivet stiffness. The proof of these mechanisms is documented by functional dependence F – ∆L and metallographic tests.
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15

Liu, Jintong, Anan Zhao, Zhenzheng Ke, Zhiqiang Li, and Yunbo Bi. "Investigation on the Residual Stresses and Fatigue Performance of Riveted Single Strap Butt Joints." Materials 13, no. 15 (August 4, 2020): 3436. http://dx.doi.org/10.3390/ma13153436.

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In aircraft manufacturing, riveting is one of the most important connection ways to fasten the sheet metal parts. The riveted single strap butt joints are mainly used in the load-bearing components of the aircraft such as the fuselage and wing panels. The connection quality and fatigue performance of the riveted joints directly affect the reliability and safety of the aircraft. In this paper, under the assumption of constant temperature, the fatigue strengthening mechanism of interference-fit riveting is introduced based on elastic-plastic mechanics and fracture mechanics. On this basis, the finite element (FE) models of the riveted single strap butt joints with various strap thickness and rivet sizes/arrangements are established. The residual stresses distribution around the riveted hole is analyzed. Furthermore, the fatigue tests of the riveted single strap butt joints with cyclic loading are carried out. The experimental results verified the correctness and effectiveness of the simulation model. Finally, the conclusion is drawn that increasing rivet size and strap thickness within the allowable weight range can improve the fatigue performance of the riveted single strap butt joints. The knowledge could be used to guide the structural design and optimization of the riveted butt joints against fatigue.
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16

Lipski, Adam, and Zbigniew Lis. "Improving Fatigue Life of Riveted Joints by Rivet Hole Sizing." Key Engineering Materials 598 (January 2014): 141–46. http://dx.doi.org/10.4028/www.scientific.net/kem.598.141.

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The aim of this paper is to assess the impact of the rivet hole sizing process on the fatigue life based on the example of the structural connections characteristic for riveted joints used in aviation industry. Test specimens reflected the structural connection consisting in a riveted lap joint of an airplane plating stiffened with a T-bar. Connected plates and the T-bar are made of D16CzATW aluminum alloy. 3 mm diameter oval head solid rivets for aviation-related purposes were made of PA24 aluminum. During fatigue tests, individual specimens with non-sized holes and with sized holes were subjected to uniaxial, one-sided, fixed-amplitude loading (R = 0). It can be concluded from the fatigue life comparison that introduction of an additional operation in the riveting process, i.e. the hole sizing, results in significant, about two-fold increase of the fatigue life of the riveted structural connection, even at slight sizing degree. The difference of the specimen damage nature was observed between specimens with sized and non-sized holes.
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17

Fung, C.-P., and J. Smart. "Riveted single lap joints. Part 1: A numerical parametric study." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 211, no. 1 (January 1, 1997): 13–27. http://dx.doi.org/10.1243/0954410971532460.

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Snap and countersunk riveted single lap joints with either one or two-rows of rivets have been analysed using finite elements and fatigue tests have been performed. In this first paper, a numerical parametric study, the joints are subjected to an alternating cyclic load and plasticity and non-linear geometry are considered. The stresses around the rivet hole and the deformed shapes of the joints are presented together with the effects of varying the clamping force, the interference fit of the rivet, the coefficient of friction and the geometry of the joints when the joints are subjected to various loading histories. The effect of changing the variables is shown to be in agreement with other published data
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18

Lei, Changyi, Qinggai Huang, and Yunbo Bi. "Tensile Load Distribution Improvement of Three-Row Riveted Lap Joint Based on Different Squeezing Displacement Combinations." Coatings 11, no. 7 (July 16, 2021): 856. http://dx.doi.org/10.3390/coatings11070856.

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Many previous studies have mainly focused on the effects of riveting parameters on single-row riveted lap joints. Little attention has been paid to multi-row riveted lap joints. The outer rows of a normal multi-row riveted lap joint usually bear a larger part of the tensile load. However, none of the studies relate the phenomenon to the squeezing displacement combination of a multi-row riveted lap joint. To improve the performance of a three-row riveted lap joint, this paper aims to reveal the internal relation between tensile load distribution, structural deformation and squeezing displacement combination. Theoretical discussion, numerical simulation and an experimental test have been conducted. Four different squeezing displacement combinations have been studied. The result indicates that an appropriate squeezing displacement combination can effectively make tensile load distribution more homogeneous. Each rivet can take approximately 33% tensile load. Structural deformation magnitude can be reduced as well. Compared with the worst situation, at the region most sensitive to tensile load, the max strain value can reduce about 53.22–79.76%. A suitable squeeze displacement combination is a simple approach for the performance enhancement of a three-row riveted lap joint. It can be practically applied in aircraft manufacturing without any additional equipment or skill learning.
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19

Skorupa, Andrzej, Małgorzata Skorupa, Tomasz Machniewicz, and Adam Korbel. "An Experimental Investigation on Crack Initiation and Growth in Aircraft Fuselage Riveted Lap Joints." Materials Science Forum 726 (August 2012): 211–17. http://dx.doi.org/10.4028/www.scientific.net/msf.726.211.

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Effects of variables related to design and production of riveted lap joints representative of longitudinal sheet connections for a pressurized transport aircraft fuselage were experimentally investigated. The specimens from an aircraft Al alloy D16 Alclad sheets of three different thicknesses (1.9, 1.2 and 0.8 mm) were assembled under load control using round head rivets and rivets with the compensator from a P24 Al alloy. For the joints from 1.9 mm thick sheets fatigue tests indicated a dependency of the crack initiation site and crack path on the squeeze force level and on the rivet type. At the same time, increasing the squeeze force led to improved fatigue properties of the joints, specimens assembled using the rivets with the compensator showing fatigue lives consistently longer than joints with the round head rivets. All observed trends have been explained based on hole expansion and load transfer measurements. For thin sheets connected using the round head rivets, local deformations and indentations under the driven rivet head promoted crack initiation and failure in the adjacent sheet. Fatigue test results indicated that the detrimental effect of this type imperfections could outweigh the benefits associated with a decrease in secondary bending due to thinning the sheets. The rivets with the compensator were observed to cause significant local imperfections beneath the manufactured head, which adversely affected the joint fatigue performance.
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20

Reddy, Ch Vinay kumar. "Efficiency of Riveted Joints: Lozenge Joint." International Journal for Research in Applied Science and Engineering Technology 6, no. 2 (February 28, 2018): 542–44. http://dx.doi.org/10.22214/ijraset.2018.2105.

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21

Fongsamootr, Thongchai, Charoenyut Dechwayukul, Notsanop Kamnerdtong, Carol A. Rubin, and George T. Hahn. "Parametric Study of Combined Adhesive-Riveted Lap Joints." Key Engineering Materials 261-263 (April 2004): 399–404. http://dx.doi.org/10.4028/www.scientific.net/kem.261-263.399.

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Riveted lap joints are widely used to assemble complex structures, e.g. aircraft fuselages. A thin layer of adhesive (sealant), is normally applied to lap joints in order to restrict the entry of moisture and retard corrosion. In this work, combined adhesive-riveted lap joints were studied to understand the effect of three parameters: panel thickness, adhesive stiffness and adhesive layer thickness, on single row non-countersunk riveted lap joints. Finite element analysis (FEA), along with Thin Adhesive Layer Analysis (TALA-developed for simulating the adhesive layer in lap joint models), were used to analyze the joint behavior. In previous studies, the stress concentration factor for single row riveted lap joints was found to be approximately 6.1, and the stress concentration factor for sealed riveted lap joints was approximately 5.2 for a 180 micron thick sealant layer. In this study, panel thickness, adhesive stiffness and adhesive layer thickness were varied parametrically in FEA analyses to determine their affects on the joints. The FEA/TALA results were used to predict the fatigue life of the joints as functions of the three parameters. The results show that the maximum tensile stress is smaller with a smaller panel thickness. The results also showed that the stress concentration factor in the joints was reduced when the stiffness of the adhesive layer was increased or when the thickness of the adhesive layer was decreased. Finally, fatigue tests showed that the fatigue life of the combined adhesive-riveted lap joints was greater than for riveted lap joints without adhesive.
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22

Nedelcu, Roxana, Daniela Bartiș, Anca Lupaș, Constantin Ilie, and Daniela Voicu. "Studies on Establishing a Methodology for Predicting the Riveted Joints Fatigue Durability in Aircraft Structures." Advanced Materials Research 1036 (October 2014): 668–73. http://dx.doi.org/10.4028/www.scientific.net/amr.1036.668.

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In this paper are described fatigue physical tests that were performed on a great number of riveted specimens with different constructive and technological parameters. Some of the purposes of the experimental tests, they were: determining the number of load cycles at which cracks by fatigue occurred, determining the moment of initiation, the location and propagation speed of the fatigue crack. For fatigue crack evolution study numerical models were designed. A simplified model for FEM analysis was proposed that reduced considerable the calculus effort and allows models for complex riveted joints. From the described experiments on specimens and numerical simulations there are some important conclusions regarding the fatigue phenomenon in riveted joints such as: important peculiarity of damage by multiple cracks is the cracks junction of adjacent rivet holes, which contributes, by jumping, to increase the degradation rate of assembly; the riveted joint model can be applied with good accuracy to estimate the durability of the structures inclusively to identify and prevent the cases of widespread fatigue damage.
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23

Wronicz, Wojciech, and Jerzy Kaniowski. "The Analysis of the Influence of Riveting Parameters Specified in Selected Riveting Instructions on Residual Stresses." Fatigue of Aircraft Structures 2014, no. 6 (June 1, 2014): 63–71. http://dx.doi.org/10.1515/fas-2014-0005.

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Abstract The riveting parameters strongly affect residual stresses induced during riveting, which in turn have an impact on the fatigue life of riveted joints. Since rivets are established as critical from the fatigue point of view, the fatigue life of riveted joints often determines the life of the whole structure. The authors were able to become acquainted with three riveting instructions (process specifications) used by the aerospace companies from western Europe. This work presents the analysis of the riveting parameters' influence on residual stresses around the rivets. The impact of the clearance between a rivet shank and a hole as well as driven head dimensions and a rivet length were investigated based on the numerical simulations. The aim of the analysis was to determine the range of stresses variation when the requirements of the riveting instructions are fulfilled. For the purposes of comparison, the calculations were performed also with the parameters as specified in the Polish industry standards. For all calculations, the geometry of the universal rivet MS20470 was used. The results show that residual stresses can vary strongly depending on the parameters in the instructions and standard requirements.
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24

Otroshi, Mortaza, Gerson Meschut, Christian Bielak, Lukas Masendorf, and Alfons Esderts. "Modeling of Stiffness Anisotropy in Simulation of Self-Piercing Riveted Components." Key Engineering Materials 883 (April 2021): 35–40. http://dx.doi.org/10.4028/www.scientific.net/kem.883.35.

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The so-called substitute models based on shell elements can be used to design the self-piercing riveted components economically and with sufficient accuracy. In this study, the SPR3 (Self-Piercing Rivet) model with anisotropic stiffness parameters implemented in commercial simulation software LS-DYNA is used to describe the stiffness of self-piercing riveted joints subjected to different loading conditions. The model provides the basis for the subsequent fatigue life estimation of self-piercing riveted joints under cyclic loading. By accurate prediction of the stiffness of self-piercing riveted joints subjected to cyclic loading, the accuracy of the fatigue life estimation can be improved. To identify the stiffness parameters, the self-piercing riveted joints are subjected to loading conditions: axial tension, shear tension, and bending. To validate the model, the specimens are simulated under different loading conditions and the results are compared to the experiments. It is shown that the model with anisotropic stiffness parameters predicts the stiffness of specimens more accurately compared to the model with isotropic stiffness parameter.
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Borba, Natascha Z., Jorge F. dos Santos, and Sergio T. Amancio-Filho. "The Influence of Clamping Pressure on Joint Formation and Mechanical Performance of Ti6Al4V/CF-PEEK Friction-Riveted Joints." Materials 12, no. 5 (March 4, 2019): 745. http://dx.doi.org/10.3390/ma12050745.

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This work aims at investigating the influence of pre-set clamping pressure on the joint formation and mechanical strength of overlapping direct-friction-riveted joints. A pneumatic fixture device was developed for this work, with clamping pressure varying from 0.2 MPa to 0.6 MPa. A case study on overlapping joints using Ti6Al4V rivets and woven carbon fiber-reinforced polyether-ether-ketone (CF-PEEK) parts were produced. Digital image correlation and microscopy revealed the expected compressive behavior of the clamping system and the continuous pressure release upon the joining process owing to the rivet plastic deformation and the polymer squeezing flow. Two preferential paths of material flow were identified through the alternate replacement of the upper and lower composite parts by a poly-methyl-methacrylate (PMMA) plate—the composite upward and squeezing flow between the parts which induced their separation. The ultimate lap shear forces up to 6580 ± 383 N were achieved for the direct-friction-riveted CF-PEEK overlap joints. The formation of a gap to accommodate squeezed polymer between the composite parts during the process had no influence on the joint mechanical performance. The increase in the clamping pressure for joints produced with a low friction force did not affect the joint-anchoring efficiency and consequently the joint strength. On the other hand, the combined effect of a high-friction force and clamping pressure induced the inverted bell shape of the plastically deformed rivet tip, a lower anchoring efficiency, and the delamination of the composite, all of which decrease the mechanical strength by 31%. Therefore, the higher the friction force and clamping pressure, the more defects would be generated in the composite parts and the more changes in the shape of the plastically deformed rivet tip, leading to a lower level of quasi-static mechanical performance. All the joints failed by initial bearing of the composite and final rivet pull-out. The findings of this work can contribute to further improvement of the clamping design for industrial application.
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Fung, C.-P., and J. Smart. "An Experimental and Numerical Analysis of Riveted Single Lap Joints." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 208, no. 2 (July 1994): 79–90. http://dx.doi.org/10.1243/pime_proc_1994_208_257_02.

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Countersunk and snap riveted single lap joints have been examined both experimentally and numerically. A total of 11 specimens were fatigued to failure with failures occurring in either the plate or the rive***r. The failures have been metallurgically examined to determine the cause of failure. The joints have also been analysed using the finite element method. Initially a single lap joint has been modelled as a ‘stepped plate’ and the results for the stress concentration factor found to be in reasonable agreement with published data. However, the stress concentration for this joint occurred at a point away from the point of failure of a riveted joint. A fuller three-dimensional finite element model has been constructed and the stress patterns around the rivet determined. These stress patterns are discussed in relation to the results from the metallurgical examination.
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Běhal, Jiří, and Roman Růžek. "EFFECT OF THE RIVET-HOLE TOLERANCE ON THE STRESS-SEVERITY FACTOR." Materiali in tehnologije 55, no. 2 (April 15, 2021): 237–42. http://dx.doi.org/10.17222/mit.2020.146.

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This work is focused on a quantitative procedure for estimating the generally unfavourable effects that incorrectly drilled holes, characterized by the initial clearance between a rivet and a hole, have on the fatigue life of riveted joints. The solution is based on an analytical approach using the stress-severity-factor concept. An experimental programme with riveted-joint specimens characterized by low-load transfer factors was realized in the Czech Aerospace Research Centre (VZLU) test lab under constant amplitude loading. The holes for rivet joints with 4-mm diameters were prepared with the clearance in a range of 0.0–0.16 mm. Force-controlled riveting was applied using a constant pressure force to form the driven head. To prevent fretting events between the joined parts, their anodized contact surfaces were lubricated with MOLYKA, plastic grease with molybdenum disulphide and graphite. The experimental data showed that the load-transfer factor and the fatigue life depend on the initial clearance between a rivet and a hole. The presented procedure introduced the hole-filling factor, integrated in the stress-severity-factor concept as a function of the initial clearance between a rivet and a hole.
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Mańkowski, Jarosław. "Numeric simulations of surface pressure and microslip phenomena occurring in riveted joints of semi-monococque structures in effect of the action of tension field." Advanced Technologies in Mechanics 3, no. 1(6) (March 2, 2017): 7. http://dx.doi.org/10.17814/atim.2016.1(6).34.

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Tension fields are shown to have an influence on surface pressure and on material deformation in the riveted joints in thin walled structures and particularly in semistressed skin structures. Stresses and materials displacements were analyzed in the riveted joints performing under such conditions. Special attention has been attached to estimation of the microslips occurring between rivets and holes. A thin plate panel has been used for the test sample, which under effort condition revealed tension fields.
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Kamińska, Paulina, Piotr Synaszko, Patryk Ciężak, and Krzysztof Dragan. "Analysis of the Corrosion Resistance of Aircraft Structure Joints with Double-Sided Rivets and Single-Sided Rivets." Fatigue of Aircraft Structures 2020, no. 12 (December 1, 2020): 57–68. http://dx.doi.org/10.2478/fas-2020-0006.

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Abstract An important factor having a negative impact on the technical condition of aircraft structure elements is the adverse effect of the atmosphere, which causes formation of corrosion in aircraft structures, especially in riveted lap joints. The electric potential difference between the sheet material and the rivet, in the presence of humid air, may cause electrochemical corrosion. The paper presents specimens that imitate the repair on the Mi-24 helicopter with the use of blind rivets in places where solid double-sided rivets could not be used. The aim of the research was to assess the corrosion resistance of lap joints with the use of single-sided and double-sided rivets. The analysis of corrosion resistance was carried out based on accelerated aging tests in a salt spray chamber. The salt chamber tests were aimed at determining the changes taking place in the specimens exposed to the marine environment. In the course of periodic observations changes in the mass of the specimens and in the form of corrosion losses were recorded. These activities were aimed at determining whether the exposure of specimens in the salt chamber causes electrochemical corrosion or pillowing. In addition, the specimens were subjected to static strength tests to assess the effect of corrosion on the strength properties of riveted joints.
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30

Pitta, Roure, Crespo, and Rojas. "An Experimental and Numerical Study of Repairs on Composite Substrates with Composite and Aluminum Doublers Using Riveted, Bonded, and Hybrid Joints." Materials 12, no. 18 (September 14, 2019): 2978. http://dx.doi.org/10.3390/ma12182978.

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In this work, experimental and numerical analyses of repairs on carbon fiber reinforced epoxy (CFRE) substrates, with CFRE and aluminum alloy doublers typical of aircraft structures, are presented. The substrates have a bridge gap of 12.7 mm (simulated crack), repaired with twin doublers joined with riveted, adhesive bonded, and hybrid joints. The performance of the repairs using different doubler materials and joining techniques are compared under static loading. The experimental results show that riveted joints have the lowest strength, while adhesive bonded joints have the highest strength, irrespective of the doubler material. Finite element analysis (FEA) of the studied joints is also performed using commercial FEA tool Abaqus. In the FEA model, point-based fasteners are used for the rivets, and a cohesive zone contact model is used to simulate the adhesive bond. The FEA results indicate that the riveted joints have higher tensile stresses on the metal doublers compared to the composite doublers. As per the failure modes, interestingly, for hybrid joints using composite doublers, the doublers fail due to net-section failure, while, for hybrid joints using metal doublers, it is the composite substrate that fails due to net-section failure. This suggests vulnerability of the composite structures to mechanical fastener holes. Lastly, the Autodesk Helius composite tool is used for prediction of first-ply failure and ply load distribution, and for progressive failure analysis of the composite substrate.
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Woytowich, Richard. "Riveted Hull Joint Design in RMS Titanic and Other Pre—World War I Ships." Marine Technology and SNAME News 40, no. 02 (April 1, 2003): 82–92. http://dx.doi.org/10.5957/mt1.2003.40.2.82.

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Beginning with an overview of riveted joint construction, this paper shows that the efficiency of riveted joints in pre-World War I ships decreased as plate thickness increased. In the case of the RMS Titanic, some of the joints involved in the iceberg impact were only about 27% as strong as the plates they connected. A finite element model is used to show how such a joint would respond to the sort of out-of-plane load that the iceberg would have applied. For one possible load configuration, the joint failure is recreated. Finally, although Titanic and her sisters were not built to class, the design of the riveted joints is examined in the context of relevant Lloyd's Register of Shipping Rules.
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32

Han, Li, Ken W. Young, R. Hewitt, A. Chrysanthou, and J. M. O'Sullivan. "The Effect of Pre-Straining on the Mechanical Behaviour of Self-Piercing Riveted Aluminium Alloy Sheets." Advanced Materials Research 6-8 (May 2005): 157–62. http://dx.doi.org/10.4028/www.scientific.net/amr.6-8.157.

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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. Pressing and stamping are important processes in automotive production and result in additional straining on the vehicle body sheet material. It is therefore important to have knowledge of the effect of sheet pre-straining on the quality of the self-piercing riveted joints and on the mechanical behaviour of the riveted aluminium alloy sheets. This paper reports the influence of sheet pre-straining on the static and fatigue behaviour of self-piercing riveted aluminium alloy sheet. Wrought aluminium alloy sheet, NG5754 with a nominal thickness value of 2mm was used to obtain pre-strained NG5754 sheets with pre-straining levels of 3%, 5% and 10%. The pre-strained NG5754 sheets were then joined in pair to create single riveted lap joints. Lap-shear and fatigue tests were performed on the self-piercing riveted joints. Microscopic inspection showed that the joint quality was satisfactory despite the increasing sheet straining levels. The results showed that by increasing the pre-straining level up to 10%, the shear and fatigue strength also increased. The rate of increase of the static and fatigue strength differed as the pre-straining levels varied.
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33

Torres-Arellano, Mauricio, Manuel de Jesus Bolom-Martínez, Edgar Adrian Franco-Urquiza, Ruben Pérez-Mora, Omar A. Jiménez-Arévalo, and Philippe Olivier. "Bearing Strength and Failure Mechanisms of Riveted Woven Carbon Composite Joints." Aerospace 8, no. 4 (April 9, 2021): 105. http://dx.doi.org/10.3390/aerospace8040105.

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This research aimed to determine riveted carbon/epoxy composites’ mechanical performance when fabricated by resin transfer molding (RTM). As this manufacturing process is gaining importance in the aeronautics and automotive industries, assembly methods and their reliability must be studied in terms of their airworthiness and transportation implementation. The study case resumes the determination of the bearing strength of RTM-woven carbon composites for different rivet joint diameters (1/8, 5/32 and 3/16 in). The joint shear strength was obtained following the ASTM D5961 instructions, and post-failure analysis was carried out by a computerized tomography scan. A residual strength curve is provided with the results to infer the bearing strength for the riveted composites as a function of the rivet width-to-diameter ratio. A discussion of the fracture mechanism and tensile strength is carried out to assess the understanding of the riveted woven composites.
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34

Фатюхин, Дмитрий, Dmitriy Fatyukhin, Равиль Нигметзянов, Ravil Nigmetzyanov, Сергей Сундуков, Sergey Sundukov, Сергей Кузнецов, Sergey Kuznetsov, Александр Сухов, and Alexandr Sukhov. "Engineering process of manufacturing riveted joint using ultrasonic percussive impact." Science intensive technologies in mechanical engineering 2019, no. 6 (June 20, 2019): 17–21. http://dx.doi.org/10.30987/article_5ce675a19ef690.18259732.

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The matters of riveted joint production effectiveness increase are considered. A circuit of percussive ultrasonic riveting is presented. There is offered an engineering process for riveted joint production. The test results of joints manufactured by percussive ultrasonic riveting are shown.
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35

Chen, Nanjiang, Maxime Thonnerieux, Richard Ducloux, Min Wan, and Jean-loup Chenot. "Parametric study of riveted joints." International Journal of Material Forming 7, no. 1 (September 25, 2012): 65–79. http://dx.doi.org/10.1007/s12289-012-1114-7.

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36

Konoplin, A. Yu, and N. I. Baurova. "Complex evaluation of quality of glued-mechanical joints." Adhesives. Sealants. Technologias, no. 10 (October 2020): 32–37. http://dx.doi.org/10.31044/1813-7008-2020-0-10-32-37.

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The component tree of the complex index of the glued-mechanical joint quality is presented. Its main branches are purpose and processability indices, and economy indices. The change of quality indices when replacing the traditional mechanical joints (welded, riveted) by the glued-mechanical ones (glued-welded, glued-riveted) was examined. The classification of factors that have influence on fracture processes of glued-mechanical joints is given. Based on analysis of fracture characters of glued-mechanical joints, possible causes of fractures are demonstrated.
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37

Wang, Bin, Chuanyong Hao, Jinsong Zhang, and Hongyan Zhang. "A New Self-Piercing Riveting Process and Strength Evaluation." Journal of Manufacturing Science and Engineering 128, no. 2 (April 27, 2005): 580–87. http://dx.doi.org/10.1115/1.2137746.

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Self-piercing riveting (SPR) has become an important alternative joining technique for the automotive applications of aluminum sheets. Most existing SPR machines use electrical motors to drive a rivet into the sheets. A significant amount of research has been conducted to improve an SPR joint’s strength by increasing the mechanical interlock. In this paper, a new process is presented using gunpowder to drive the riveting process. A joint formed using the new process has different geometric characteristics from one created using a conventional system. The tensile-shear, cross-tension, fatigue, and impact performances of self-piercing riveted joints using the new device are compared to those of spot-welded joints on aluminum sheets. The experiment has proven that the new SPR joints have provided a similar or higher strength than resistance spot welds.
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38

Zhao, Anan, Yongliang Zhang, Chunrun Zhu, Zhengwei Zhong, and Yunbo Bi. "Effect of the Position of the Boundary Rivets on the Quality of Riveted Single Strap Butt Joints." Materials 14, no. 18 (September 7, 2021): 5127. http://dx.doi.org/10.3390/ma14185127.

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Riveting is widely used in aircraft manufacturing. The strap butt joint is often used in the aircraft’s main bearing area such as the aircraft docking area. The connection quality affects the reliability and safety of the aircraft directly. To study the effect of the rivet position on the connection quality of the strap butt joints, this paper analyzed the distribution of stress around the rivet hole at different positions by the finite element method, and then further analyzed the influence of the different rivet layouts on the connection quality of the strap butt joints by experiments. The static load tensile failure test of the joints was carried out, and the obtained tensile strength and failure mode of the strap butt joints showed that the main static tensile failure form of the single strap butt joint is that the whole rivets is sheared and the connecting sheets are separated. By changing the layout of different rivets, the connection strength can be maximized by reducing the outer row spacing (ORSD) of rivets. The results can be used for reference in the design of the riveting structure of aircraft panels.
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39

Al-Samhan, Ali M. "Analysis of Adhesively Bonded Riveted Joints." Journal of King Saud University - Engineering Sciences 18, no. 1 (2005): 57–65. http://dx.doi.org/10.1016/s1018-3639(18)30821-3.

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40

Li, De Zhi, Li Han, Mike Shergold, Martin Thornton, and Geraint Williams. "Influence of Rivet Tip Geometry on the Joint Quality and Mechanical Strengths of Self-Piercing Riveted Aluminium Joints." Materials Science Forum 765 (July 2013): 746–50. http://dx.doi.org/10.4028/www.scientific.net/msf.765.746.

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Due to the drive from legislations, fuel efficiency, and CO2 emission, the application of aluminium lightweight structures in automotive industry have been increased significantly. Self piercing riveting (SPR) has been one of the major joining technologies for aluminium structures due to its advantages to some traditional joining technologies. There are some standard parameters that will influence the joint quality and mechanical strengths of an SPR joint. However, even for the same parameters used, sometimes the joint quality and mechanical strengths of SPR joints could still be significantly different, which may cause joint failure or strength reduction. One reason found is the variation of rivet specifications between different batches. In this paper, the influence of rivet tip geometry on the joint quality and mechanical strengths was studied. The results showed that rivets with sharper tips flared more during riveting process, and joints with sharper rivets had higher lap shear strength; however, the influence of rivet geometry on T peel strength could be different for different rivets, and rivet tip geometry did not have an obvious influence on joint fatigue strengths.
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41

He, Xiao Cong, Ian Pearson, and Ken W. Young. "Finite Element Analysis of Self-Pierce Riveted Joints." Key Engineering Materials 344 (July 2007): 663–68. http://dx.doi.org/10.4028/www.scientific.net/kem.344.663.

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Self-pierce riveting (SPR) is a sheet material joining technique which is suitable for joining dissimilar materials, as well as coated and pre-painted materials. Published work relating to finite element analysis of SPR joints is reviewed in this paper, in terms of process, static strength, fatigue strength, vibration characteristics and assembly dimensional prediction of the SPR joints. A few important numerical issues are discussed, including material modelling, meshing procedure, failure criteria and friction between substrates and between rivet and substrate. It is concluded that the finite element analysis of SPR joints will help future applications of SPR by allowing system parameters to be selected to give as large a process window as possible for successful joint manufacture. This will allow many tests to be simulated that would currently take too long to perform or be prohibitively expensive in practice, such as modifications to rivet geometry, die geometry or material properties. The main goal of the paper is to review recent progress in finite element analysis of SPR joints and to provide a basis for further research.
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42

Fletcher, L. S., G. P. Peterson, C. V. Madhusudana, and E. Groll. "Constriction Resistance Through Bolted and Riveted Joints." Journal of Heat Transfer 112, no. 4 (November 1, 1990): 857–63. http://dx.doi.org/10.1115/1.2910492.

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A correlation relating nondimensional macroscopic thermal resistance to the geometric variables of a bolted joint has been developed. The variables considered include the upper and lower plate thickness, the plate radius, the contact zone radius, and the bolt radius. Experiments were conducted using an electrolytic analog method. The investigation was conducted over a range of variables that include the plate thicknesses, 0.95 to 2.22 cm; the bolt radii, 0.32 to 1.27 cm; the plate radii, 5.1 to 10.2 cm; and the contact zone radii, 1.27 to 8.89 cm. A numerical technique was developed that accurately predicted the experimental results to within ±8 percent. Based on the analysis and experimental data, a correlation was developed that may be used to predict the macroscopic thermal resistance in bolted joints.
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43

Rao, Harish, Jidong Kang, Garret Huff, and Katherine Avery. "Structural Stress Method to Evaluate Fatigue Properties of Similar and Dissimilar Self-Piercing Riveted Joints." Metals 9, no. 3 (March 20, 2019): 359. http://dx.doi.org/10.3390/met9030359.

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In this paper, we discuss the application of a simple Battelle structural stress model to evaluate the fatigue life of a self-piercing riveted (SPR) carbon-fiber-reinforced polymer (CFRP) composite to aluminum AA6111. The analytical model accounts for the forces and moments acting on the rivets to determine the structural stresses which were then plotted against the laboratory-generated fatigue life data. The master S-N curve determined in this study thus accounts for various factors such as the stacking configuration, rivet head height, and fatigue load ratios. The analytical model used in this study was able to collapse a large number of fatigue life data into one master S-N curve irrespective of stack-ups, rivet head height, and load ratios. Thus, the master S-N curve derived from the model can be used to predict the fatigue life of the SPR joints.
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44

kosenko, E. A., and A. Yu Konoplin. "Analysis of equipment for performance of riveted joint in machinery construction (Patent review)." Repair, Reconditioning, Modernization, no. 12 (December 2020): 36–39. http://dx.doi.org/10.31044/1684-2561-2020-0-12-36-39.

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Structures of technological equipment for performance of riveted joints of machine parts are considered. A description of the equipment designs is presented, the technical result of which is to improve the quality of produced riveted joints, reduce the labor intensity of the technological process, and improve working conditions.
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45

He, Xiao Cong. "An Approximate Method via Coefficient of Variation for Strength Prediction of Self-Piercing Riveted Joints." Applied Mechanics and Materials 26-28 (June 2010): 334–39. http://dx.doi.org/10.4028/www.scientific.net/amm.26-28.334.

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This study deals with an application of the method of the coefficient of variation in strength prediction of the self-piercing riveted joints. Defined as the ratio of the standard deviation to the mean, the coefficient of variation may be used in both the reliability-based design of self-piercing riveted joints and in the evaluation of existing products. In this study, the concept and definition of the coefficient of variation are stated. The procedure of the use of coefficient of variation for approximate calculations of strength of the self-piercing riveted joints is presented and compared with the classical Taylor expansion method. This is illustrated with a numerical example.
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46

Haque, Rezwanul, Yat C. Wong, Anna Paradowska, Stuart Blacket, and Yvonne Durandet. "SPR Characteristics Curve and Distribution of Residual Stress in Self-Piercing Riveted Joints of Steel Sheets." Advances in Materials Science and Engineering 2017 (2017): 1–14. http://dx.doi.org/10.1155/2017/5824171.

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Neutron diffraction was used to describe the residual stress distributions in self-piercing riveted (SPR) joints. The sheet material displayed a compressive residual stress near the joint, and the stress gradually became tensile in the sheet material far away from the joint. The stress in the rivet leg was lower in the thick joint of the softer steel sheet than in the thin joint of the harder steel sheet. This lower magnitude was attributed to the lower force gradient during the rivet flaring stage of the SPR process curve. This study shows how the residual stress results may be related to the physical occurrences that happened during joining, using the characteristics curve. The study also shows that neutron diffraction technique enabled a crack in the rivet tip to be detected which was not apparent from a cross-section.
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47

IYER, K., S. J. HU, F. L. BRITTMAN, P. C. WANG, D. B. HAYDEN, and S. P. MARIN. "Fatigue of single- and double-rivet self-piercing riveted lap joints." Fatigue Fracture of Engineering Materials and Structures 28, no. 11 (November 2005): 997–1007. http://dx.doi.org/10.1111/j.1460-2695.2005.00938.x.

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48

Wronicz, Wojciech. "Comparison of Residual Stress State on Sheets Faying Surface after Standard and NACA Riveting-Numerical Approach." Fatigue of Aircraft Structures 2016, no. 8 (June 1, 2016): 116–26. http://dx.doi.org/10.1515/fas-2016-0011.

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AbstractOne crucial characteristic of the aircraft structure are fatigue properties and rivets are usually critical areas in metal airframes due to fatigue cracks nucleation. According to literature, the NACA riveting method offers a huge increase in fatigue life of riveted lap joints. This paper presents FE simulations of quasi-static riveting on a press for standard countersunk rivets and the NACA riveting in two configurations: with a normal brazier rivet and a brazier rivet with a compensator. The analyzed configurations have been compared based on the stress courses on the sheets faying surfaces after riveting process. Due to a lack of data, the rivet length and the squeezing force value were assumed for NACA riveting based on FE simulations. The results indicated beneficial influence of the NACA riveting in the outer sheet (with a countersunk) and disadvantageous influence in the inner sheet. This effect was stronger in the case of the rivet with a compensator.
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49

Janovec, M., J. Čerňan, and F. Škultéty. "Use of non-destructive eddy current technique to detect simulated corrosion of aircraft structures." Koroze a ochrana materialu 64, no. 2 (June 1, 2020): 52–58. http://dx.doi.org/10.2478/kom-2020-0008.

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AbstractThe article deals with the issue of non-destructive testing of riveted joints. In the article, the authors used a non-destructive eddy current array technique, which was applied to detect simulated corrosion in the field of aircraft riveted joints of aluminum sheets. In aircraft maintenance, the eddy current method is used to control the outer surface of the aircraft skin, especially the areas around the riveted joints. This method makes it possible to detect hidden cracks and corrosion that may occur during aircraft operation. Especially hidden are hidden cracks and corrosion of aircraft structures, which cannot be detected during a visual inspection of the aircraft. The aim of the experimental measurements was to reveal simulated corrosion in the area of riveted joints formed on the experimental sample. Corrosion was simulated by gluing aluminum powder to the surface of the aluminum sheets from which the sample was made. The simulated corrosion in the second and third layers of the riveted sample was reliably detected. The settings, the method of control and the results of measurements are given in the article in the experimental part and the results of measurements. Measurements were performed using a defectoscope with an ECA measurement module, with appropriate measuring probes suitable for this type of inspection.
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50

Leite, Regina C. G., Abilio M. P. de Jesus, José Correia, Patricia Raposo, Renato N. Jorge, Marco Paulo Parente, and Rui Calçada. "A methodology for a global-local fatigue analysis of ancient riveted metallic bridges." International Journal of Structural Integrity 9, no. 3 (June 11, 2018): 355–80. http://dx.doi.org/10.1108/ijsi-07-2017-0047.

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Purpose Recent studies have proposed the application of local fatigue approaches based on fracture mechanics or on strain-life material relations for the fatigue analysis of metallic structures. However, only few studies in the literature apply local approaches in the riveted bridges analysis; although these approaches can be applied to any type of connections, requiring a detailed stress analysis of joints and, consequently, considerable computational resources costs. The approach based on S-N curves, formulated in nominal or net stresses, is more usual in the fatigue analysis of riveted bridges. Due to economic factors, riveted bridges have had their operating life extended, while changes in the transport system over the years have subjected such structures to overloads different from those originally planned. These bridges, most of them centenary, were not originally designed accounting for fatigue damage; they represent an important group of structures that are very likely subjected to significant fatigue damage indexes. These factors make necessary detailed residual fatigue life studies to substantiate the decisions of extend (or not) the operational period of these bridges. The paper aims to discuss these issues. Design/methodology/approach The present paper presents a methodology aiming at applying the local approaches in the fatigue analysis of riveted joints of metallic bridges, through the use of sub-modeling techniques and procedures automation. The use of such techniques made such an application viable by keeping the computational costs involved at a moderate level. The proposed procedures were demonstrated using the Trezói Railway Bridge, located on the Beira Alta line, Portugal, built shortly after the Second World War. The proposed set of procedures allowed, through finite elements analysis, to obtain the relevant stresses to perform local fatigue damage analysis. A global structural model was constructed, using beam elements, and local models of a critical node were built with solid finite elements. The structure is analyzed under the passage of regulatory trains. The details of the modeling performed and the computation of the principal stresses in the vicinity of a node and the tangential/circumferential stresses at the holes of two critical riveted connections of that node are analyzed and a fatigue damage analysis is carried out. Findings In the proposed submodelling approach, disassembling the complex riveted nodes into riveted subassemblies allowed the evaluation of the local stresses at riveted holes at an affordable computational cost. Originality/value A methodology is proposed to allow the application of local fatigue analysis in real complex riveted joints, mitigating the computational costs that would result from a full model of the node with all rivets.
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