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Автор: Grafiati
Опубліковано: 10 грудня 2022
Оновлено: 28 січня 2023

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Статті в журналах з теми "Plates, Aluminum Fatigue"

1

Tian, Ni, Xu Jiang, Yaozhong Zhang, Zijie Zeng, Tianshi Wang, Gang Zhao, and Gaowu Qin. "Effect of Precipitates on the Mechanical Performance of 7005 Aluminum Alloy Plates." Materials 15, no. 17 (August 28, 2022): 5951. http://dx.doi.org/10.3390/ma15175951.

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In this study, the strength, elongation, and fatigue properties of 7005 aluminum alloy plates with different configurations of precipitates were investigated by means of tensile tests, fatigue tests, and microstructural observation. We found that the number and size of GP zones in an alloy plate matrix increased and the distribution was more uniform after the aging time was extended from 1 h to 4 h at 120 °C, which led to a rise in both strength and elongation of alloy plates with the extending aging time. The fatigue life of the alloy plates shortened slightly at first, then significantly prolonged, and then shortened again with the aging time extending from 1 h to 192 h and a fatigue stress level of 185 MPa and stress ratio (R) = 0. After aging at 120 °C for 96 h, the precipitates in the alloy plate matrix were almost all metastable η′-phase particles, which had the optimal aging strengthening effect on the alloy matrix, and the degree of mismatch between the α-Al matrix and second-phase particles was the smallest; the fatigue crack initiation and propagation resistances were the largest, leading to the best fatigue performance of alloy plates, and the fatigue life of the aluminum plate was the longest, up to 1.272 × 106 cycles. When the aging time at 120 °C was extended to 192 h, there were a small number of equilibrium η phases in the aluminum plates that were completely incoherent with the matrix and destroyed the continuity of the aluminum matrix, easily causing stress concentration. As a result, the fatigue life of alloy plates was shortened to 9.422 × 105 cycles.
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2

Jian, Hai Gen, Min Xian Du, Feng Jiang, and Zhi Min Yin. "Fatigue Characteristic of Aluminum Alloy Plates with Different Thickness." Applied Mechanics and Materials 477-478 (December 2013): 1284–87. http://dx.doi.org/10.4028/www.scientific.net/amm.477-478.1284.

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The fatigue characteristic of 2124 aluminum alloy in T851 condition was investigated by means of scanning electron microscopy (SEM) and transmission electron microscope (TEM). And the result shows that, the fatigue life is closely related to the thickness of plates, this is because that different thickness of plates results in the variation of grain size, grain boundaries and substructures of alloy, which thus influence the fatigue behavior of 2124-T851 alloy. The number of grain boundaries along the propagation direction of cracks and the amount of substructures after heat treatment increase with the decline of thicknesses of 2124 alloy plates, while the grain size is reverse. However, no obvious size and dispersion changes for the precipitates. Comparatively, the fatigue resistance performance of 30mm thickness plate is better than the 40mm and 55mm thickness plates, which is due to the more profitable grain size, grain boundary and substructure.
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3

You, Xiang, Zhiyu Wang, Xiafang Zhou, Zifeng Liu, Ruijuan Jiang, and Weiming Gai. "Fatigue Life Appraisal and Its Corrected Stress Intensity Factor for Repaired Off-CentrallyCracked Aluminum Plates." Materials 13, no. 18 (September 10, 2020): 4014. http://dx.doi.org/10.3390/ma13184014.

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This paper presents an experimental study on the fatigue life estimation of off-centrally cracked aluminum plates. Typical theoretical equations for off-central, central and edge cracks were reviewed and compared in terms of their sensitive parameters and applicability. A finite element model has been validated in its capacity in modelling the influences of eccentricity and crack size on the boundary correction coefficients. The Forman equation has been employed along with numerical results for the prediction of fatigue lives. Based on the test data, the fatigue life results of aluminum plates with and without patched laminate repair have been compared with codified fatigue classes. It is demonstrated that the repair at the crack tip close to the plate edge is effective in the fatigue life improvement for off-centrally crackedaluminum plates.
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4

Yousefi, Armin, Saman Jolaiy, Reza Hedayati, Ahmad Serjouei, and Mahdi Bodaghi. "Fatigue Life Improvement of Cracked Aluminum 6061-T6 Plates Repaired by Composite Patches." Materials 14, no. 6 (March 15, 2021): 1421. http://dx.doi.org/10.3390/ma14061421.

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Bonded patches are widely used in several industry sectors for repairing damaged plates, cracks in metallic structures, and reinforcement of damaged structures. Composite patches have optimal properties such as high strength-to-weight ratio, easiness in being applied, and high flexibility. Due to recent rapid growth in the aerospace industry, analyses of adhesively bonded patches applicable to repairing cracked structures have become of great significance. In the present study, the fatigue behavior of the aluminum alloy, repaired by a double-sided glass/epoxy composite patch, is studied numerically. More specifically, the effect of applying a double-sided composite patch on the fatigue life improvement of a damaged aluminum 6061-T6 is analyzed. 3D finite element numerical modeling is performed to analyze the fatigue performance of both repaired and unrepaired aluminum plates using the Abaqus package. To determine the fatigue life of the aluminum 6061-T6 plate, first, the hysteresis loop is determined, and afterward, the plastic strain amplitude is calculated. Finally, by using the Coffin-Manson equation, fatigue life is predicted and validated against the available experimental data from the literature. Results reveal that composite patches increase the fatigue life of cracked structures significantly, ranging from 55% to 100% for different applied stresses.
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5

Yang, Xiao Hua, Ding Zhang, and Yong Zhang. "2D FE Modeling of Cracked Aluminum Plates Repaired with Adhesively Bonded Composite Patches." Advanced Materials Research 152-153 (October 2010): 1024–30. http://dx.doi.org/10.4028/www.scientific.net/amr.152-153.1024.

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A 2D FE model of cracked aluminum plates repaired with adhesively bonded composite patches was established in this paper, and then the model was validated by comparing the calculated SIF and fatigue life of repaired structure with existing results. The result shows that the model is accurate enough to be used to analyze the mechanical property of cracked aluminum plates repaired with adhesively bonded composite patches.
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6

Albedah, A., Sohail MA Khan, B. Bachir Bouiadjra, and F. Benyahia. "Fatigue crack propagation in aluminum plates with composite patch including plasticity effect." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 11 (June 1, 2017): 2122–31. http://dx.doi.org/10.1177/0954410017710273.

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In this paper, we analyzed experimentally and numerically the behavior of fatigue crack in aluminum plates repaired with bonded composite patch. We studied the behavior of repaired crack in AA 2024 T3 and AA 7075 T6 under two levels of applied fatigue stresses: maximal stresses of 70 and 120 MPa at a load ratio of 0.1. In the experimental part, the fatigue life of unrepaired and repaired notched specimens were determined. In the numerical part, the J integral around repaired and unrepaired crack tips was calculated. The numerical and the experimental results were used to plot the crack velocity (da/dN) as a function of the J integral. The analysis was completed with scanning electron microscopic observations on fracture surfaces of repaired and unrepaired specimens. It was found that patch improves the fatigue life but this improvement is considerably reduced with the increase in the applied fatigue load. The Al 2024 T3 presents better resistance to fatigue crack propagation in both repaired and unrepaired cases.
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7

Wang, Q. Y., and R. M. Pidaparti. "Static characteristics and fatigue behavior of composite-repaired aluminum plates." Composite Structures 56, no. 2 (May 2002): 151–55. http://dx.doi.org/10.1016/s0263-8223(01)00176-3.

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8

Sano, Yuji, Kiyotaka Masaki, and Keiichi Hirota. "Improvement in Fatigue Strength of Friction Stir Welded Aluminum Alloy Plates by Laser Peening." Advanced Materials Research 891-892 (March 2014): 969–73. http://dx.doi.org/10.4028/www.scientific.net/amr.891-892.969.

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Plane bending fatigue testing was performed to study the fatigue properties of friction stir welded (FSW) 3 mm thick AA6061-T6 aluminum alloy plates. Fatigue cracks propagated with bends and curves on the specimens, showing large deviation from a linear line. This might be reflecting the material flow and microstructure in the weld zone. The fatigue strength of the unwelded base material (BM) was 110 MPa at 107 cycles and FSW deteriorated it to 90 MPa. However, laser peening (LP) restored the degraded fatigue strength up to 120 MPa which is higher than that of the BM.
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9

Jia, Yinglian, Zhichao Huang, Yongchao Zhang, and Fan Zhang. "Forming Quality and Fatigue Behavior of Self-Piercing Riveted Joints of DP590 and AA6061 Plates." Advances in Materials Science and Engineering 2021 (October 18, 2021): 1–10. http://dx.doi.org/10.1155/2021/4381544.

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Two kinds of self-piercing riveted (SPR) joints were prepared with DP590 and AA6061 plates. The forming qualities of the joints were studied using the finite element method. The relationships between the fatigue life and failure forms of the joints with different upper plates were discussed. Finally, the failure mechanisms of the joints were analyzed. The results show that the maximum static tension of DA32 joints (with an upper plate of DP590) is significantly greater than that of the other kind, and the fatigue life of DA32 joints is always longer than that of AA40 joints when with a 2.0 mm thick AA6061 aluminum alloy upper plate under the same fatigue load. The failure mode of SPR joints changes obviously due to different upper plates, and the fatigue life of the joints can be effectively improved by reducing the microvibration wear.
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10

Azouaoui, Krimo, and Said Mouhoubi. "Study on Damage Modes of a Sandwich Panel Impacted Repeatedly." Advanced Materials Research 980 (June 2014): 147–51. http://dx.doi.org/10.4028/www.scientific.net/amr.980.147.

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This paper describes an experimental investigation for determining the damage modes under low energy impact-fatigue of sandwich panels consisting of aluminum skins supported by honeycomb core made of aluminum. Square samples of 125mm by 125mm sides and 10mm thickness (skin of 0.6mm and 8.8mm of core) were subjected to impact fatigue loading using a testing machine at four different energy levels (2J, 3J, 5J and 7J). The square plates are clamped in a fixture system over a 100mm diameter hole. Three different diameters of impactor head (15mm, 25mm and 35mm) are used to study their influence on life duration of the sandwich plates. Results showed that damage area at impacted face and propagation of multi-cracks at rear face are greatly affected by energy level and impactor diameter.
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Більше джерел

Дисертації з теми "Plates, Aluminum Fatigue"

1

Lemke, Kevin L. "A comparison of the fatigue properties of aluminum lithium 8090 forgings and 7050 aluminum plate in low strength orientations." Thesis, Georgia Institute of Technology, 1993. http://hdl.handle.net/1853/19971.

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2

Kieboom, Orio Terry Aerospace Civil &amp Mechanical Engineering Australian Defence Force Academy UNSW. "The conjunctive use of bonded repairs and crack growth retardation techniques." Awarded by:University of New South Wales - Australian Defence Force Academy. School of Aerospace, Civil and Mechanical Engineering, 2007. http://handle.unsw.edu.au/1959.4/38712.

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In an attempt to find a way of improving the damage tolerance of composite bonded repairs to metallic aircraft structures, the effect of using conventional crack growth retardation techniques in conjunction with bonded repairs was experimentally investigated. Hence, an experimental test program was set up to determine whether fatigue crack growth under bonded repairs is retarded further by giving the crack to be repaired a crack growth retardation treatment prior to repair patch application. In addition, it was set up to determine the influence of a bonded repair on the effectiveness of a crack growth retardation method. Centrally cracked aluminium plates were used. Stop drilling followed by cold hole expansion and the application of single overloads were selected as retardation treatments. Two patch materials were considered; boron/epoxy and Glare 2. Further test variables were the aluminium alloy and the plate thickness. Fatigue testing was carried out under constant amplitude loading and baseline results were determined first. In addition to optically monitoring the crack growth, local and global out-of-plane deformations were visualised with holographic interferometry and shadow moire??. Furthermore, the stress intensity factors under the repair patch were examined with strain gauges and measurement of the central crack opening displacement. Disbonds and fracture surfaces were studied after residual strength tests. The crack growth results obtained showed that retardation treatments decrease crack growth rates under a repair patch and that the effectiveness of a retardation treatment is increased by the patch. Although identical crack growth rates were observed under boron/epoxy and Glare 2 patches, the reinitiation period after the retardation treatment lasted longer when Glare 2 patches were applied. Analytical predictions of the extent of retardation based on existing models showed that the conjunctive effect of retardation treatments and bonded repairs was underestimated. A sustained reduction in crack growth rates was observed under bonded repairs with a prior overload retardation treatment. It was concluded that the damage tolerance of bonded repairs is increased by the application of a crack growth retardation treatment because the crack growth is retarded further. These findings indicate that the range of cracks in aircraft for which bonded repairs can be considered is expanded and that economic benefits can be obtained.
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3

Lombard, Hannalie. "Optimized fatigue and fracture performance of friction stir welded aluminium plate : a study of the inter-relationship between process parameters, TMAZ, microstructure, defect population and performance." Thesis, University of Plymouth, 2007. http://hdl.handle.net/10026.1/2389.

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Friction stir welding (FSW) is an exciting new solid-state welding process with the potential to advantageously impact many fabrication industries. Current take-up of the process by industry is hindered by lack of knowledge of suitable welding parameters for any particular alloy and sheet thickness. The FSW process parameters are usually chosen empirically and their success is evaluated via simple mechanical property testing. There are severe drawbacks with such methods of determining manufacturing conditions. These include indirect relationships between tensile and fatigue properties, particularly for welds, and a high probability of totally missing real optimized conditions. This research is therefore undertaken as a first step in providing information that will assist manufacturing industry to make sound decisions with respect to selecting FSW parameters for weldable structural alloys. Some of the key issues driving material selection for manufacturing are weld quality in terms of defects, fatigue strength and crack growth, and fracture toughness. Currently a very limited amount of data exists regarding these mechanical properties of FSW welds, and even less information exists regarding process parameter optimization. This is due to the mechanical microstructural complexity of the process and the relatively large number of process parameters (feed, speed, force and temperature) that could influence weld properties. In order to advance predictive understanding and modeling for FS welds, it is necessary to develop force and energy based models that reflect the underlying nature of the thermo-mechanical processes that the material experiences during welding. This project aims at determining the influence and effect of Friction Stir Welding process control parameters on the microstructure of the thermo-mechanically affected zone, the defect population in the weld nugget, hardness, residual stresses, tensile and fatigue performance of 6 mm plate of 5083-H321 aluminium alloy, which is known to be susceptible to planar defect formation. Welds were made with a variety of process parameters (that is feed rate and rotational speed) to create different rates of heat input. Forces on the FSW tool (horizontal and vertical), torque and tool temperature were measured continuously during welding from an instrumented FSW tool. Detailed information on fatigue performance, residual stress states, microstructure, defect occurrence, energy input and weld process conditions, were investigated using regression models and contour maps which offer a unique opportunity to gain fundamental insight into the process-structure-property relationships for FS welds. Weld residual strains have been extensively measured using synchrotron X-ray diffraction strain scanning to relate peak residual stresses and the widths of the peak profiles, taken from a single line scan from the mid depth of the FS welds, with the weld process conditions and energy input into the welds. Several residual stress maps were also investigated. The optical and scanning electron microscope were used to determine the type of intrinsic defects present in the FSW fatigue and tensile specimens. Vickers hardness measurements were taken from the mid depth of the welds and were compared with the weld input parameters. The main contribution of this thesis is as follow: (i) the relationship between input parameters and process parameters; (ii) the relationship between input weld parameters (that is feed rate and rotational speed) and process parameters (that is vertical downwards force Fz, tool temperature, tool torque and the force footprint data), energy input and tensile strength, fatigue life and residual stresses to obtain regions of optimum weld conditions; (iii) identification of the defects present in FSW, their relationship with process parameters and their effect on tensile strength and fatigue life; and (iv) the usefulness of the real time process parameter monitoring automated instrumented FSW tool to predict the mechanical properties of the welds.
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4

Issam, Jassim Khadim. "Contribution à l'étude de fissures longues et courtes se propageant en mode tridimensionnel dans un alliage d'aluminium." Compiègne, 1987. http://www.theses.fr/1987COMPD057.

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Revue des solutions analytiques proposées dans la littérature pour déterminer les facteurs d'intensités de contraintes et les mécanismes mis en jeu dans la propagation des fissures courtes. Analyse du comportement en fatigue des fissures tridimensionnelles. Présentation des résultats expérimentaux sur les fissures courtes prenant naissance sur des surfaces libres. Analyse de l'ensemble des résultats en terme de facteur d'intensité de contrainte efficace sur le concept d'ouverture fermeture de la fissure.
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5

Yuan, Shin Ching, and 施清淵. "Effects of Flame Strengthening on Fatigue Limit of Aluminium Alloy Plates." Thesis, 2012. http://ndltd.ncl.edu.tw/handle/09413416704154543874.

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碩士
國防大學理工學院
機械工程碩士班
100
The unsuitability of flame-straightening methods used on aluminum ship's structure will reduce the mechanical and corrosion resistance properties of 5456-H116 marine aluminum alloys. Therefore, the purpose of this study is to investigate the effects of annealing temperature on the microstructure, mechanical and corrosion resistance properties of a 5456-H116 marine aluminum alloy via hardness testing, tensile testing and metallographic examination. Meanwhile, the fatigue limit changes of the 5456-H116 specimens after sensitization and recrystallization were also evaluated by bending testing and scanning electron microscope (SEM). The experiment results show that the mechanical and sensitization properties of the 5456-H116 marine aluminum alloys are highly related to the annealing temperature and holding time. A significant change in mechanical properties occurred during the recrystallization process while hardness, UTS and YS dropped rapidly and the uniform elongation increased considerably. Microstructure observation of the specimens annealed at 175°C showed that β phase (Mg2Al3) tend to precipitate along grain boundaries, which not only promoted the sensitization formed but also caused the obstruction at grain boundary while the fatigue crack propagation.
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6

Дивдик, О. В., та O. V. Dyvdyk. "Підвищення залишкової довговічності елементів авіаційних конструкцій пластичним деформуванням матеріалу в околі отворів". Diss., 2020. http://elartu.tntu.edu.ua/handle/lib/33012.

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Дана робота стосується актуальної науково-технічної проблеми підвищення залишкової довговічності елементів авіаційних конструкцій з концентраторами напружень. Високі вимоги до надійності конструкцій і їх безпечної експлуатації мають особливе значення в умовах циклічного навантаження і високих напружень. Важливою є наукова задача оцінки залишкової довговічності конструктивних елементів з експлуатаційними пошкодженнями (втомними тріщинами) в околі функціональних і кріпильних отворів з підвищеними вимогами до безпечної експлуатації.
This work concerns the topical scientific and technical problem of increasing the residual lifetime of elements of aircraft structures with stress concentrators. High requirements for the reliability of structures and their safe operation are of particular importance in conditions of cyclic loading and high stresses. An important scientific task is to assess the residual lifetime of structural elements with operational damage (fatigue cracks) in the vicinity of functional and mounting holes with high requirements for safe operation
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Книги з теми "Plates, Aluminum Fatigue"

1

Wanhill, R. J. H. Damage tolerance property comparisons for 2000 and 8000 series aluminium plate alloys. Amsterdam: National Aerospace Laboratory, 1995.

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2

Center, Langley Research, ed. Fracture testing of 2324-T39 aluminum alloy. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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3

Fracture testing of 2324-T39 aluminum alloy. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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4

Center, Langley Research, ed. Fracture testing of 2324-T39 aluminum alloy. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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5

High intensity acoustic tests of a thermally stressed aluminum plate in tafa. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

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6

A, Clevenson Sherman, and Langley Research Center, eds. High intensity acoustic tests of a thermally stressed aluminum plate in tafa. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

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Частини книг з теми "Plates, Aluminum Fatigue"

1

Fang, Ziwei, Jingjing He, and Jie Liu. "Imbalanced Classification of Fatigue Crack for Aluminum Plates Using Lamb Wave." In Lecture Notes in Civil Engineering, 161–70. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-64908-1_15.

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2

Fang, Ziwei, Jingjing He, and Jie Liu. "Imbalanced Classification of Fatigue Crack for Aluminum Plates Using Lamb Wave." In Lecture Notes in Civil Engineering, 161–70. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-64908-1_15.

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3

Ahmed, Faraz, S. M. A. K. Mohammed, Faycal Benyahia, Bel Abbes Bachir Bouiadjra, and Abdulmohsen Albedah. "Plasticity Analysis in Aluminum Alloy Plates Repaired with Bonded Composite Patch Under Overload." In Proceedings of the 10th International Conference on Fracture Fatigue and Wear, 21–27. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-7808-1_3.

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4

Chellil, A., S. Lecheb, I. Gahlouz, H. Mechakra, T. Djedid, and H. Kebir. "Identification of Defects and Fatigue of Aluminum Plates by Control of Vibration Characteristics." In Proceedings of the 4th International Symposium on Materials and Sustainable Development, 71–85. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-43268-3_7.

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5

Schubbe, Joel. "Fatigue Crack Growth In Thick Plate 7050 Aluminum." In ICAF 2009, Bridging the Gap between Theory and Operational Practice, 909–20. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-90-481-2746-7_49.

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6

Pantelakis, Sp, and P. Papanikos. "Fatigue crack growth in a center-cracked thin aluminium plate." In Problems of Fracture Mechanics and Fatigue, 439–40. Dordrecht: Springer Netherlands, 2003. http://dx.doi.org/10.1007/978-94-017-2774-7_92.

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7

Pantelakis, S., and P. Papanikos. "Effect of fatigue crack length on failure mode of a center-cracked thin aluminium plate." In Problems of Fracture Mechanics and Fatigue, 445–47. Dordrecht: Springer Netherlands, 2003. http://dx.doi.org/10.1007/978-94-017-2774-7_94.

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8

Lee, C. K., Jonathan J. Scholey, Paul D. Wilcox, M. R. Wisnom, M. I. Friswell, and B. W. Drinkwater. "Guided Wave Acoustic Emission from Fatigue Crack Growth in Aluminium Plate." In Advanced Materials Research, 23–28. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-420-0.23.

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9

Kemp, R. M. J., R. N. Wilson, and P. J. Gregson. "The Role of Crack Closure in Corrosion Fatigue of Aluminium Alloy Plate for Aerospace Structures." In Fracture of Engineering Materials and Structures, 700–705. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3650-1_103.

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10

Kermanidis, Al Th, V. K. Spiliadis, and Sp G. Pantelakis. "Fatigue Crack Growth Rate under Constant Amplitude Loading and under Tensile Overloads in Sheet and Plate 2024 Aluminum Alloy." In Particle and Continuum Aspects of Mesomechanics, 649–56. London, UK: ISTE, 2010. http://dx.doi.org/10.1002/9780470610794.ch67.

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Тези доповідей конференцій з теми "Plates, Aluminum Fatigue"

1

Grondel, Sebastien, Emmanuel Moulin, and Christophe Delebarre. "Lamb wave assessment of fatigue damage in aluminum plates." In 1999 Symposium on Smart Structures and Materials, edited by Norman M. Wereley. SPIE, 1999. http://dx.doi.org/10.1117/12.350716.

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2

Khalili, S. Mohammad Reza, Reza Eslami Farsani, and Pasha Mojahedi. "Fatigue Behavior of Notched Aluminum Plates Repaired by Smart and Composite Patches." In ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2010. http://dx.doi.org/10.1115/esda2010-24893.

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In this study, mode I fatigue crack growth behavior of single edge notched thin aluminum plates repaired with single side composite patches is investigated experimentally. Three patches are investigated in this analysis, 1- three layers carbon/epoxy laminated composite patch, 2- smart patches contained shape memory alloy (SMA) wires without pre-strain embedded in between the carbon/epoxy layers, and 3- smart patches contained SMA wires with pre-strain embedded in between the carbon/epoxy layers. The results are compared with the results obtained for un-repaired notched plate and the influence of SMA wires is also studied. The experimental results show a significant increase in crack growth life in all repaired plates compared with un-repaired plate. The repaired plates with smart pre-strained SMA patches show greater life as compared to other plates repaired by other patches. The three layers carbon/epoxy patches show better results compared to smart SMA un-strained patches. Also, numerical modeling is done by ANSYS software to obtain the stress intensity factor in mode I fatigue loading and then applied to Paris law for prediction of the fatigue crack growth life. The results are compared with the experimental results and a good agreement is obtained.
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3

Aggelis, D. G., I. F. Spiridon, and T. E. Matikas. "Acoustic emission for fatigue damage monitoring in cross-welded aluminum plates." In SPIE Smart Structures and Materials + Nondestructive Evaluation and Health Monitoring, edited by Kara J. Peters, Wolfgang Ecke, and Theodoros E. Matikas. SPIE, 2013. http://dx.doi.org/10.1117/12.2009103.

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4

Benyahia, F., A. Albedah, and B. Bachir Bouiadjra. "Bonded Composite Repairs of Aluminum Alloy 2024T3 Cracked Plates." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-36316.

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In this study, the behavior of repaired cracks, located in aluminum alloy sheets 2024T3, with bonded composite patch is analyzed experimentally and numerically. The experimental study has been conducted through fatigue tests on aluminum cracked plate repaired with Carbon/epoxy patch. In the numerical analysis, the stress intensity factor at the crack front is computed using three-dimensional finite element method. The obtained results show that the stress intensity factor at the crack front is highly reduced by the presence of the patch repair. Therefore, the fatigue life of the damaged structure can be significantly improved especially if the patch repair is applied at small crack lengths.
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5

Conrad, David, and Andrei Zagrai. "Active Detection of Structural Damage in Aluminum Alloy Using Magneto-Elastic Active Sensors (MEAS)." In ASME 2011 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2011. http://dx.doi.org/10.1115/smasis2011-5219.

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Many structural damage detection methods utilize piezoelectric sensors. While these sensors are efficient in supporting many structural health monitoring (SHM) methodologies, there are a few key disadvantages limiting their use. The disadvantages include the brittle nature of piezoceramics and their dependence of diagnostic results on the quality of the adhesive used in bonding the sensors. One viable alternative is the utilization of Magneto-Elastic Active Sensors (MEAS). Instead of mechanically creating elastic waves, MEAS induce eddy currents in the host structure which, along with an applied magnetic field, generate mechanical waves via the Lorentz force interaction. Since elastic waves are generated electromagnetically, MEAS do not require direct bonding to the host structure and its elements are not as fragile as PWAS. This work explores the capability of MEAS to detect damage in aluminum alloy. In particular, methodologies of detecting fatigue cracks in thin plates were explored. Specimens consisted of two identical aluminum plates featuring a machined slot to create a stress riser for crack formation. One specimen was subjected to cyclic fatigue load. MEAS were used to transmit elastic waves of different characteristics in order to explore several SHM methodologies. Experiments have shown that the introduction of fatigue cracks created measurable amplitude changes in the waves passing through the fatigued region of the aluminum plate. The phase indicated sensitivity to load conditions, but manifestation in the cracked region lacked stability. Nonlinear effects were studied using plate thickness resonance, which revealed birefringence due to local stresses at the site of the fatigue crack. The resonance spectrum has also shown a frequency decrease apparently due to stiffness loss. Preliminary results suggest opportunities for fatigue damage detection using MEAS. Application of MEAS for the diagnosis of complex structures is currently being investigated.
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6

Saeed, Khalid, and Muhammad Abid. "Crack growth performance of aluminum plates repaired with composite and metallic patches under fatigue loading." In 2015 Fourth International Conference on Aerospace Science and Engineering (ICASE). IEEE, 2015. http://dx.doi.org/10.1109/icase.2015.7489504.

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7

Cui, Xiaodong, Xiaohu Liu, Eugene Fang, and Phillip Liu. "Co-Simulation of Fatigue Crack Growth and Delamination Evolution in Cracked Aluminum Plates Repaired with a Composite Patch." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-2065.

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8

Tarar, Wasim, and M. H. Herman Shen. "A New Finite Element Approach to Biaxial Fatigue Life Prediction in Gas Turbine Engine." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23095.

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High cycle fatigue is the most common cause of failure in gas turbine engines. Different design tools have been developed to predict number of cycles to failure for a component subjected to fatigue loads. An energy-based fatigue life prediction framework was previously developed in recent research for prediction of axial and bending fatigue life at various stress ratios. The framework for the prediction of fatigue life via energy analysis was based on a new constitutive law, which states the following: the amount of energy required to fracture a material is constant. A finite element approach for uniaxial and bending fatigue was developed by authors based on this constitutive law. In this study, the energy expressions that construct the new constitutive law are integrated into minimum potential energy formulation to develop a new QUAD-4 finite element for fatigue life prediction. The newly developed QUAD-4 element is further modified to obtain a plate element. The Plate element can be used to model plates subjected to biaxial fatigue including bending loads. The new QUAD-4 element is benchmarked with previously developed uniaxial tension/compression finite element. The comparison of Finite element method (FEM) results to existing experimental fatigue data, verifies the new finite element development for fatigue life prediction. The final output of this finite element analysis is in the form of number of cycles to failure for each element in ascending or descending order. Therefore, the new finite element framework can predict the number of cycles to failure at each location in gas turbine engine structural components. The new finite element provides a very useful tool for fatigue life prediction in gas turbine engine components. The performance of the fatigue finite element is demonstrated by the fatigue life predictions from Al6061-T6 aluminum and Ti-6Al-4V. Results are compared with experimental results and analytical predictions.
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9

Hölzl, Reinhold, and Rainer Flüggen. "Experimental Fatigue Evaluation of Aluminum Brazed Plate Fin Heat Exchangers." In ASME 2013 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/pvp2013-97915.

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For the verification of a finite element based calculation procedure for the strength and fatigue design of aluminum brazed Plate Fin Heat Exchangers (PFHE) an extensive experimental investigation program was planned and executed. In the first step high temperature loadings as single events were applied to the PFHEs to recognize, whether damage (a leak) can be produced by a severe single loading. After various tests on different geometries the investigations were enlarged to thermal cycling tests on small PFHEs until leaks were detected. The tests were executed with three blocks in parallel to cover a statistical influence and the tests were repeated with three new blocks under identical conditions. All six blocks gave nearly the same number of load cycles until first detection of leaks. In addition three blocks of the same geometry were loaded with lower thermal stress, giving higher load cycle numbers until a leak occurred. The experimentally determined cycle numbers were compared to calculated cycle numbers out of the finite element modeling and showed very good agreement. Those tests and comparisons are a strong basis for fatigue and lifetime considerations on large scale PFHEs in the process industry.
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10

Koc¸ak, Mustafa, Eduard Seib, and Afshin Motarjemi. "Improvements to the Fracture Assessment of Welds Using FITNET Fitness for Service Assessment Procedure." In ASME 2005 24th International Conference on Offshore Mechanics and Arctic Engineering. ASMEDC, 2005. http://dx.doi.org/10.1115/omae2005-67568.

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Recent developments of the advanced welding processes such as laser beam welding (LBW), solid state friction stir welding (FSW) and hybrid welding, numbers of advanced structures are being designed and constructed in industries such as aerospace, power generation, oil and gas transmission and transportation. Development of new structural aluminum and magnesium alloys as well as high strength steels provide further possibilities for the welded structures in similar and dissimilar (material-mix) configurations. Consequently, there is an increasing demand for “Fitness-for-Service” (FFS) assessment of those advanced welded structures by considering the specific features of these weld joints (such as narrow weld width, high strength mis-match, etc.). In year 1999, Structural Integrity Assessment Procedure SINTAP has been developed for analysis of flaws to avoid fracture within the European Commission funded project SINTAP. Recently, the European Community funded project FITNET in the form of a Thematic Network (TN) organisation has started to review the existing FFS procedures and develop an updated, unified and verified European FITNET FFS Procedure to cover structural integrity analysis to avoid failures due to fracture, fatigue, creep and corrosion. This new FFS Procedure has adopted the SINTAP approach for assessing of the welded structures. This paper describes the FITNET FFS weld assessment route and also aims to demonstrate suitability of weld joint assessment route of the FITNET FFS Procedure in prediction of the critical conditions of various advanced welded joints containing flaw. The welded specimens used in this work cover conventional multi-pass welded Inconel-718 turbine blade (T-joint), center cracked wide plates of electron beam welded 13% Cr supermartensitic stainless steel, laser beam welded shipbuilding C-Mn steel and aluminum alloy. The results are showing that the weld strength mismatch analysis option of the FITNET FFS is conservative and degree of conservatism is similar to the analysis options for the homogeneous materials. This provides confidence in the use of the FITNET FFS procedure for assessing of the structural significance of flaws in welded structures.
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Звіти організацій з теми "Plates, Aluminum Fatigue"

1

Strizak, J., C. Brinkman, and G. Ludtka. Plate Weldment Flexural Fatigue Tests in Support of Advanced Aluminum Bridge Deck Design. Office of Scientific and Technical Information (OSTI), June 1999. http://dx.doi.org/10.2172/770423.

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2

Cervay, Russel R., and Kumar V. Jata. Effects of Humidity on the Fatigue Crack Growth Rate in Aluminum Alloy 8090-T8771 Thick Plate. Fort Belvoir, VA: Defense Technical Information Center, February 1995. http://dx.doi.org/10.21236/ada296574.

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