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Journal articles on the topic 'Aluminum alloys – Fatigue'

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Published: 4 June 2021
Last updated: 31 January 2023

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1

Dostál, Petr, Michal Černý, Jaroslav Lev, and David Varner. "Proportional monitoring of the acoustic emission in crypto-conditions." Acta Universitatis Agriculturae et Silviculturae Mendelianae Brunensis 59, no. 5 (2011): 31–38. http://dx.doi.org/10.11118/actaun201159050031.

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The work is aimed at studying corrosion and fatigue properties of aluminum alloys by means of acoustic emission (AE). During material degradation are acoustic events scanned and evaluated. The main objective of the article is a description of behavior of aluminum alloys degraded in specific conditions and critical degradation stages determination. The first part of the article describes controlled degradation of the material in the crypto–conditions. The acoustic emission method is used for process analyzing. This part contains the AE signals assessment and comparing aluminium alloy to steel.
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2

Zhao, Xuehang, Haifeng Li, Tong Chen, Bao’an Cao, and Xia Li. "Mechanical Properties of Aluminum Alloys under Low-Cycle Fatigue Loading." Materials 12, no. 13 (2019): 2064. http://dx.doi.org/10.3390/ma12132064.

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In this paper, the mechanical properties of 36 aluminum alloy specimens subjected to repeated tensile loading were tested. The failure characteristics, stress-strain hysteresis curves and its corresponding skeleton curves, stress cycle characteristics, and hysteretic energy of specimens were analyzed in detail. Furthermore, the finite element model of aluminum alloy specimens under low-cycle fatigue loading was established and compared with the experimental results. The effects of specimen parallel length, parallel diameter, and repeated loading patterns on the mechanical properties of aluminu
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KURUMADA, Akira, Makoto SOUMA, Takahito WATAKABE, and Goroh ITOH. "OS18F099 Effect of Hydrogen on the Fatigue Crack Propagation in Aluminum Alloys." Abstracts of ATEM : International Conference on Advanced Technology in Experimental Mechanics : Asian Conference on Experimental Mechanics 2011.10 (2011): _OS18F099——_OS18F099—. http://dx.doi.org/10.1299/jsmeatem.2011.10._os18f099-.

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4

BUAHOMBURA, Panya, Yukio MIYASHITA, Yoshiharu MUTOH, and NOBUSHIRO Seo. "409 Fatigue Crack Growth Behavior of FSWed Joint in Different Aluminum Alloys." Proceedings of the Materials and processing conference 2012.20 (2012): _409–1_—_409–4_. http://dx.doi.org/10.1299/jsmemp.2012.20._409-1_.

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5

HARLOW, D. GARY. "PARTICLE STATISTICS IN ALUMINUM ALLOYS." International Journal of Reliability, Quality and Safety Engineering 13, no. 04 (2006): 379–95. http://dx.doi.org/10.1142/s021853930600232x.

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Pitting corrosion and fatigue crack growth are primary degradation mechanisms that affect the durability and integrity of structures made of aluminum alloys, and they are concerns for commercial transport and military aircraft. The heterogeneous nature of aluminum alloys is the reason that these are operative damage mechanisms. Typically, there are about 2,000 constituent particles per mm2on polished surfaces. Corrosion pits commence at the constituent particles and evolve into severe pits by sustained growth through clusters of particles. The severe pits are nucleation sites for subsequent fa
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6

BIAN, Jian-Chun, Keiro TOKAJI, and Takeshi OGAWA. "Study on Fatigue Properties of Aluminum-Lithium Alloys,IV. Notch Sensitivity of Aluminum-Lithium Alloys in Fatigue." Journal of the Society of Materials Science, Japan 43, no. 490 (1994): 840–46. http://dx.doi.org/10.2472/jsms.43.840.

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7

Fan, Chao Hua, Yu Ting He, Heng Xi Zhang, Hong Peng Li, and Feng Li. "Predictive Model Based on Genetic Algorithm-Neural Network for Fatigue Performances of Pre-Corroded Aluminum Alloys." Key Engineering Materials 353-358 (September 2007): 1029–32. http://dx.doi.org/10.4028/www.scientific.net/kem.353-358.1029.

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In the paper, genetic algorithm is introduced in the study of network authority values of BP neural network, and a GA-NN algorithm is established. Based on this genetic algorithm-neural network method, a predictive model for fatigue performances of the pre-corroded aluminum alloys under a varied corrosion environmental spectrum was developed by means of training from the testing dada, and the fatigue performances of pre-corroded aluminum alloys can be predicted. The results indicate that genetic algorithm-neural network algorithm can be employed to predict the underlying fatigue performances o
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8

Wang, Xi-Shu, Xu-Dong Li, Hui-Hui Yang, Norio Kawagoishi, and Pan Pan. "Environment-induced fatigue cracking behavior of aluminum alloys and modification methods." Corrosion Reviews 33, no. 3-4 (2015): 119–37. http://dx.doi.org/10.1515/corrrev-2014-0057.

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AbstractThis paper reviews the current corrosion fatigue strength issues of light metals, which include the corrosion fatigue cracking behaviors, such as the prior-corrosion pit deformation mechanism, the synergistic interaction between prior-corrosion pits and local stress/strain, the coupling damage behavior under mechanical fatigue loading, and the surrounding environmental factors such as a high humidity and a current 3.5 wt.% or 5.0 wt.% NaCl aqueous solution. The characterization of corrosion fatigue crack growth rate based on simple and measurable parameters (crack propagation length an
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9

Chen, Xu, Rui Si Xing, and Xiao Peng Liu. "Multiaxial Fatigue of 6061-T6 Aluminum Alloy under Corrosive Environment." Applied Mechanics and Materials 853 (September 2016): 77–82. http://dx.doi.org/10.4028/www.scientific.net/amm.853.77.

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Aluminium alloys are widely used in the fields of automobile, machinery and naval construction. To investigate the effect of non-proportional loadings and corrosive environment on the fatigue resistance of 6061-T6 aluminum alloy, a set of uniaxial and multiaxial low cycle fatigue tests were carried out. Firstly, the results of uniaxial tests showed that the alloy exhibited cyclic hardening then cyclic softening. With the increase of stress amplitude the cyclic softening became pronounced. The increasing of plastic deformation was basically cyclically stable with small plastic strain amplitude
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10

Yankin, Andrey, A. I. Mugatarov, and V. E. Wildemann. "Influence of different loading paths on the multiaxial fatigue behavior of 2024 aluminum alloy under the same amplitude values of the second invariant of the stress deviator tensor." Frattura ed Integrità Strutturale 15, no. 55 (2020): 327–35. http://dx.doi.org/10.3221/igf-esis.55.25.

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2024 aluminum alloy is a common aeronautic material. During operations, construction elements made of aluminum alloys undertake complex cyclic loadings. Therefore, it is important to estimate the influence of these loadings on the durability of the material. Hereby, multiaxial fatigue tests with the same amplitude values of the second invariant of the stress deviator tensor are conducted, and test data are analyzed. The modified Sines method is utilized to predict fatigue experimental data. Results show that the model is accurate enough to fatigue behavior prediction of 2024 aluminum alloy.
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11

Gebhardt, Christian, Johannes Nellessen, Andreas Bührig-Polaczek, and Christoph Broeckmann. "Influence of Aluminum on Fatigue Strength of Solution-Strengthened Nodular Cast Iron." Metals 11, no. 2 (2021): 311. http://dx.doi.org/10.3390/met11020311.

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The fatigue strength of high silicon-alloyed nodular cast iron is influenced by casting defects and graphite precipitates. The literature as well as the findings of this work show that these microstructural constituents can be tailored by controlling silicon microsegregation. In addition, segregations also affect the ferritic matrix microstructure locally. In the present work, silicon segregations in high silicon-alloyed ductile iron are specifically manipulated by small additions of aluminum. It was demonstrated how the aluminum content affects a wide range of microstructural constituents acr
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12

Gangloff, Richard P., Robert S. Piascik, Dennis L. Dicus, and James C. Newman. "Fatigue crack propagation in aerospace aluminum alloys." Journal of Aircraft 31, no. 3 (1994): 720–29. http://dx.doi.org/10.2514/3.46553.

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13

JONO, Masahiro, and Atsushi SUGETA. "Fatigue crack growth resistance in aluminum alloys." Journal of Japan Institute of Light Metals 40, no. 7 (1990): 543–53. http://dx.doi.org/10.2464/jilm.40.543.

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14

USTILOVSKY, S. "Random fatigue crack growth in aluminum alloys." International Journal of Fatigue 21 (September 1999): 275–82. http://dx.doi.org/10.1016/s0142-1123(99)00098-5.

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15

Jahn, M. T., and H. C. Voris. "SEM study of humid air effect on fatigue of aluminum alloy 2024-T351." Proceedings, annual meeting, Electron Microscopy Society of America 47 (August 6, 1989): 298–99. http://dx.doi.org/10.1017/s0424820100153464.

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There is general agreement that the fatigue life of high strength aluminum alloys is reduced in humid environment. However, there are also data supporting the theory that humidity plays an insignificant role in the reduction of the fatigue life of aluminum alloy 2024-T351. In this study we examined the effects of stress level and water vapor density on the fatigue life of aluminum alloy 2024-T351 using scanning electron microscope (SEM). SEM evidence of the deleterious effect of humid air on the fatigue life of specimens cycled at intermediate stress level was presented. Discrepancies between
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16

Krupp, Ulrich, Alexander Giertler, Stephanie Siegfanz, and Wilhelm Michels. "Mutual Interaction between Fatigue Crack Initiation/Propagation and Microstructural Features in Cast Aluminum Alloys." Advanced Materials Research 891-892 (March 2014): 488–93. http://dx.doi.org/10.4028/www.scientific.net/amr.891-892.488.

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The correlation between the microstructure, the mechanical properties and the fatigue life of the common aluminum cast alloy Al-7Si-0.3Mg (A356) was investigated. By variation the solution heat treatment temperatures and times the precipitation strengthening effect in the dendritic aluminum solid solution phase and the spheroidization of the eutectic silicon were modified. The results of fully reversed fatigues tests revealed an increase in the fatigue life of specimens that were heat treated at higher temperatures. This observation was supported by analyzing the fatigue crack propagation beha
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17

Zhang, Yuan Bin, Hui Luo, and Tong Guang Zhai. "Pore Size Distribution and the Fatigue Properties of Several Cast Aluminum Alloys." Advanced Materials Research 139-141 (October 2010): 251–54. http://dx.doi.org/10.4028/www.scientific.net/amr.139-141.251.

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The population and size of porosities in three kinds of cast aluminum alloys, i.e. A713, A356T6-1 and A356T6-2, were statistically measured using a commercial software Spirit, and several distribution functions were tried to fit the cumulative pore size distribution data. It was found that a general extreme value (GEV) distribution function was the most appropriate function to quantify the cumulative pore size distribution in these cast aluminum alloys. The stress-number of cycles to failure (S-N) curves of these alloys were characterized by four point bend fatigue testing on MTS810 materials
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18

Wang, Qing Yuan, Norio Kawagoishi, Nu Yan, and Q. Chen. "Super-Long Life Fatigue Behavior of Structural Aluminum Alloys." Key Engineering Materials 261-263 (April 2004): 1287–94. http://dx.doi.org/10.4028/www.scientific.net/kem.261-263.1287.

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The objective of this study is to determine very long life fatigue and near threshold fatigue crack growth behaviors of 7075/T6 and 6061/T6 Al-alloys using piezoelectric accelerated fatigue at 19.5KHz. The experimental results show the fatigue failure can occur beyond 107, even 109 cycles, and endurance limits could not be obtained in the Al-alloys until 109 cycles. Fatigue voids are noticed on fatigue fracture in both alloys. By using scanning electron microscopy (SEM), the crack initiation and propagation behaviors have been examined. Fatigue crack growth rates of small cracks in the Al-allo
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19

Oh, Kwang Keun, Yeon Wook Kim, and Jae Hoon Kim. "High Cycle Fatigue Characteristics of Aluminum Alloy by Shot Peening." Advanced Materials Research 1110 (June 2015): 142–47. http://dx.doi.org/10.4028/www.scientific.net/amr.1110.142.

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An aluminum alloy is used in airplanes and aerospace to reduce the weight of structures. Recently, researchers have studied how to intensify the strength of aluminum alloys. Shot peening is one of method to reinforce strength by hitting the surface of materials to make residual stress. In this study, high cycle fatigue characteristics of aluminum alloy Al 7075-T6 and Al 2024-T4 were analyzed. Fatigue characteristics of before and after the shot peened materials were tested by cantilever-rotary bending fatigue test machine (YRB 200, Yamamoto). Also, fractographic analysis was performed by a Sca
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20

Tenkamp, Jochen, Mustafa Awd, Shafaqat Siddique, Peter Starke, and Frank Walther. "Fracture–Mechanical Assessment of the Effect of Defects on the Fatigue Lifetime and Limit in Cast and Additively Manufactured Aluminum–Silicon Alloys from HCF to VHCF Regime." Metals 10, no. 7 (2020): 943. http://dx.doi.org/10.3390/met10070943.

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Aluminum–silicon alloys are commonly used in die-cast and additively manufactured (AM) light-weight components due to their good processability and high strength-to-weight ratio. As both processing routes lead to the formation of defects such as gas and shrinkage porosity, a defect-sensitive design of components is necessary for safe application. This study deals with the fatigue and crack propagation behavior of die-cast alloy AlSi7Mg0.3 and additively manufactured alloy AlSi12 and its relation to process-induced defects. The different porosities result in significant changes in the fatigue s
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21

Teng, Yunnan, Liyang Xie, and Hongyuan Zhang. "Experimental Study on Vibration Fatigue Behavior of Aircraft Aluminum Alloy 7050." Materials 15, no. 21 (2022): 7555. http://dx.doi.org/10.3390/ma15217555.

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It has been previously noted that the development of aerospace material technology and breakthroughs are inseparable when obtaining great achievements in the aerospace industry. Materials are the basis and precursor of modern high technology and industry. As one of the most powerful aluminium alloys, 7050 is widely used in the aerospace field. In this manuscript, the vibration fatigue behaviour of aircraft aluminium alloy 7050 is studied based on experiments. A vibration fatigue experiment and the traditional fatigue testing of aluminium alloy 7050 were performed. We found that there was an ex
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22

Li, Ning, Xiaojun Yan, Xuerong Liu, Lu Han, and Weifang Zhang. "Mechanical Properties Evolution of the 7B04-T74 Aluminum Alloy in the Marine Atmosphere." Metals 12, no. 12 (2022): 2173. http://dx.doi.org/10.3390/met12122173.

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The 7xxx-series aluminum alloys are widely used in aircrafts due to their superior performance. The evolution of the mechanical properties of the aluminum alloys caused by marine atmospheric corrosion has become a research hotspot due to the increase in aircraft service time in the marine atmospheric environment. In this work, the evolution of the mechanical properties of the 7B04-T74 aluminum alloy was studied by an alternate immersion test. The surface microstructure was analyzed by SEM, EDS, XRD, and OM. The influence of the marine atmospheric corrosion on mechanical properties was studied
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23

Ye, Xiong Lin, You Li Zhu, and Dong Hu Zhang. "Effects of Ultrasonic Deep Rolling on Fatigue Performance of Pre-Corroded 7A52 Aluminum Alloy." Advanced Materials Research 189-193 (February 2011): 897–900. http://dx.doi.org/10.4028/www.scientific.net/amr.189-193.897.

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The effects of ultrasonic deep rolling (UDR) on the fatigue behavior of pre-corroded 7A52 aluminum alloys were investigated. By means of X-Ray diffraction stress measurements and scanning electron microscopy (SEM), residual stress and fractograph of 7A52 aluminum alloys with and without UDR treatment were analyzed. The results indicated that the UDR produced compressive residual stresses with depth approaching 1mm. UDR treatment can extend the fatigue life of the pre-corroded 7A52 specimens to a large extent, depending on the level of corrosion and UDR parameter. For the slightly corrode speci
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24

KURUMADA, Akira, Makoto SOUMA, Takahito WATAKABE, and Goroh ITOH. "OS18-1-4 Effect of Hydrogen on the Fatigue Crack Propagation in Aluminum Alloys." Abstracts of ATEM : International Conference on Advanced Technology in Experimental Mechanics : Asian Conference on Experimental Mechanics 2011.10 (2011): _OS18–1–4—. http://dx.doi.org/10.1299/jsmeatem.2011.10._os18-1-4-.

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25

Alexopoulos, Nikolaos D., Evangelos Migklis, and Dimitrios Myriounis. "Experimental analysis of constant-amplitude fatigue properties in 6156 (Al-Mg-Si) sheet aluminum alloy." Journal of Strain Analysis for Engineering Design 53, no. 8 (2018): 676–86. http://dx.doi.org/10.1177/0309324718775565.

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Fatigue mechanical behavior of wrought aluminum alloy (Al-Mg-Si) 6156 at T4 temper is experimentally investigated. Constant-amplitude fatigue tests, at fixed stress ratio R = 0.1, were carried out, and the respective stress–life diagram was constructed and compared against the competitive 6xxx aluminum alloys, for example, 6082 and 6061. Fatigue endurance limit of AA6156 was found to be approximately 155 ± 5 MPa, that is, almost 30% below yield stress Rp of the material. AA6156 presents almost 50% higher fatigue life in the high-cycle fatigue area and approximately 20% higher fatigue endurance
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26

Zakharchenko, Kirill, Vladimir Kapustin, Alexey Larichkin, and Yaroslav Lukyanov. "Influence of Technology of Hot Forming of Plates from Aluminum Alloys Al-Cu-Li-Zn and Al-Zn-Mg-Cu on Resistance to Fatigue Fracture." Metal Working and Material Science 22, no. 4 (2020): 94–109. http://dx.doi.org/10.17212/1994-6309-2020-22.4-94-109.

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Introduction. One of the primary objectives in the development of promising aircraft products is to reduce the weight of the aircraft structure. This problem can be solved by applying new low density materials such as aluminum alloys alloyed with lithium (for example, Al-Cu-Li-Zn) in the design of parts. The use of these materials in aircraft construction is limited by the processing technology, which must be such as not to damage the material and not reduce its strength properties. Such technologies include processing by pressure with heating, when creep processes are activated and the materi
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27

Mohin, M. A., H. Toofanny, A. Babutskyi, A. Lewis, and Y. G. Xu. "Effect of Electromagnetic Treatment on Fatigue Resistance of 2011 Aluminum Alloy." Journal of Multiscale Modelling 07, no. 03 (2016): 1650004. http://dx.doi.org/10.1142/s1756973716500049.

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Beneficial effects of the electromagnetic treatment on fatigue resistance were reported on several engineering alloys. These could be linked to the dislocation activity and the rearrangement of the crystal structure of the material under the electromagnetic field (EMF), resulting in delayed crack initiation. This paper presents an experimental study on the effect of pulsed electromagnetic treatment on the fatigue resistance of 2011 aluminum alloy. Circular cantilever specimens with loads at their ends were tested on rotating fatigue machine SM1090. Fatigue lives of treated and untreated specim
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28

OCHI, YASUO, KIYOTAKA MASAKI, TAKASHI MATSUMURA, YOHEI KUMAGAI, TATSUHIKO HAMAGUCHI, and YUJI SANO. "FATIGUE STRENGTH IMPROVEMENT BY PEENING TREATMENT IN DEGASSING PROCESSED CAST ALUMINUM ALLOYS." International Journal of Modern Physics B 20, no. 25n27 (2006): 3593–98. http://dx.doi.org/10.1142/s0217979206040040.

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Rotating bending fatigue tests were carried out in order to investigate effects of shot peening and laser peening treatment on fatigue properties of degassing processed cast aluminum alloys. Degassing was useful for decreasing cast defects and increasing the range of fatigue life and fatigue strength at 107 cycles compared with those of non-degassed cast alloys. The shot peening and the laser peening treatments also showed remarkable effects for increasing the resistance of crack propagation behaviors and improving the fatigue strength of the degassing processed cast aluminum alloys.
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29

Lee, Jungsub, Sang-Youn Park, and Byoung-Ho Choi. "Evaluation of Fatigue Characteristics of Aluminum Alloys and Mechanical Components Using Extreme Value Statistics and C-Specimens." Metals 11, no. 12 (2021): 1915. http://dx.doi.org/10.3390/met11121915.

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In this study, the fatigue characteristics of aluminum alloys and mechanical components were investigated. To evaluate the effect of forging, fatigue specimens with the same chemical compositions were prepared from billets and forged mechanical components. To evaluate the cleanliness of the aluminum alloys, the cross-sectional area of specimens was observed, and the maximum inclusion sizes were obtained using extreme value statistics. Rotary bending fatigue tests were performed, and the fracture surfaces of the specimens were analyzed. The results show that the forging process not only elevate
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30

Alexopoulos, Nikolaos D., Vangelis Migklis, Stavros K. Kourkoulis, and Zaira Marioli-Riga. "Fatigue Behavior of Aerospace Al-Cu, Al-Li and Al-Mg-Si Sheet Alloys." Advanced Materials Research 1099 (April 2015): 1–8. http://dx.doi.org/10.4028/www.scientific.net/amr.1099.1.

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In the present work, an experimental study was performed to characterize and analyze the tensile and constant amplitude fatigue mechanical behavior of several aluminum alloys, namely 2024 (Al-Cu), 2198 (Al-Li) and 6156 (Al-Mg-Si). Al-Li alloy was found to be superior of 2024 in the high cycle fatigue and fatigue endurance limit regimes, especially when considering specific mechanical properties. Alloy 6156 was found to have superior constant amplitude fatigue performance that the respective 6xxx series alloys; more than 15% higher endurance limit was noticed against 6061 and almost 30% higher
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31

Zhang, Xiao Min, Jian Mao, Yun Che, and Zhong Ke Zhang. "Investigations on the Fatigue Property of the High-Strength and Toughness 211Z Casting Aluminium Alloy." Applied Mechanics and Materials 423-426 (September 2013): 197–201. http://dx.doi.org/10.4028/www.scientific.net/amm.423-426.197.

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211Z is a new type of high strength and toughness Al-Cu-Mn casting aluminum alloy. With the aid of GPS-100 high-cycle fatigue testing machine and DDL100 multifunction tensile testing machine, conventional mechanics performance tests and high-cycle fatigue tests were carried out in this paper. The conventional mechanical property results show that the tensile strength is 477.5 MPa, the theory yield strength is 397.5 MPa and the elongation is 6.625%. Fatigue experiments were performed with load control at room temperature and R =-1 in ambient air. The tensile and compression fatigue strength is
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32

Elboujdaini, Mimoun, and Edward Ghali. "Corrosion Fatigue of Aluminum Alloys in Chloride Media." Materials Science Forum 44-45 (January 1991): 153–68. http://dx.doi.org/10.4028/www.scientific.net/msf.44-45.153.

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33

Choi, Sung-Jong, Hak-Sun Lee, Cheol-Jae Lee, and Sang-Tae Kim. "Fretting Fatigue Behavior of High Strength Aluminum Alloys." Transactions of the Korean Society of Mechanical Engineers A 31, no. 2 (2007): 197–204. http://dx.doi.org/10.3795/ksme-a.2007.31.2.197.

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34

Wang, Qigui, Guoqiu He, and Yucong Wang. "Fatigue Behavior of Aluminum Alloys under Multiaxial Loading." SAE International Journal of Materials and Manufacturing 7, no. 2 (2014): 465–72. http://dx.doi.org/10.4271/2014-01-0972.

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35

Bian, J. C., K. Tokaji, and T. Ogawa. "NOTCH SENSITIVITY OF ALUMINUM-LITHIUM ALLOYS IN FATIGUE." Fatigue & Fracture of Engineering Materials and Structures 18, no. 1 (1995): 119–27. http://dx.doi.org/10.1111/j.1460-2695.1995.tb00146.x.

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36

Wang, Q. Y., T. Lib, and X. G. Zenga. "Gigacycle fatigue behavior of high strength aluminum alloys." Procedia Engineering 2, no. 1 (2010): 65–70. http://dx.doi.org/10.1016/j.proeng.2010.03.007.

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37

Lee, E. U., and R. E. Taylor. "Fatigue behavior of aluminum alloys under biaxial loading." Engineering Fracture Mechanics 78, no. 8 (2011): 1555–64. http://dx.doi.org/10.1016/j.engfracmech.2010.11.005.

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38

Bull, C., and R. Hermann. "Fatigue crack growth and closure in aluminum alloys." Scripta Metallurgica et Materialia 30, no. 10 (1994): 1337–42. http://dx.doi.org/10.1016/0956-716x(94)90269-0.

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39

Davidson, David L. "Small and large fatigue cracks in aluminum alloys." Acta Metallurgica 36, no. 8 (1988): 2275–82. http://dx.doi.org/10.1016/0001-6160(88)90327-6.

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40

Scala, A., A. Squillace, T. Monetta, D. B. Mitton, D. Larson, and F. Bellucci. "Corrosion fatigue on 2024T3 and 6056T4 aluminum alloys." Surface and Interface Analysis 42, no. 4 (2010): 194–98. http://dx.doi.org/10.1002/sia.3190.

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41

DuQuesnay, D. L., and P. R. Underhill. "Fatigue life scatter in 7xxx series aluminum alloys." International Journal of Fatigue 32, no. 2 (2010): 398–402. http://dx.doi.org/10.1016/j.ijfatigue.2009.07.016.

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42

Barletta, M., F. Lambiase, and Vincenzo Tagliaferri. "Improvement of Fatigue Behaviour of High Strength Aluminium Alloys by Fluidized Bed Peening (FBP)." Key Engineering Materials 344 (July 2007): 87–96. http://dx.doi.org/10.4028/www.scientific.net/kem.344.87.

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This paper deals with a definition of a relatively novel technique to improve the fatigue behavior of high strength aluminum alloys, namely, Fluidized Bed Peening (FBP). Fatigue samples made from AA 6082 T6 alloy were chosen according to ASTM regulation about rotating bending fatigue test and, subsequently, treated by varying FBP operational parameters and fatigue testing conditions. First, a full factorial experimental plan was performed to assess the trend of number of cycles to rupture of fatigue samples varying among several experimental levels the factors peening time and maximum amplitud
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43

Bernstein, H., and C. Loeby. "Low-Cycle Corrosion Fatigue of Three Engineering Alloys in Salt Water." Journal of Engineering Materials and Technology 110, no. 3 (1988): 234–39. http://dx.doi.org/10.1115/1.3226042.

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Low-cycle fatigue tests were conducted under strain control in salt water on 2024 aluminum, 304 stainless steel, and 1045 steel. All three materials showed a significant reduction in life due to corrosion fatigue in the low-cycle fatigue regime. The corrosion fatigue life of the aluminum and steel was time dependent, with significantly shorter lives at lower frequencies or at longer strain hold times. The corrosion fatigue life of the stainless steel was not time dependent for the conditions studied. Elastic and plastic strain-range versus life equations were modified by a frequency term to pr
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Arcieri, Emanuele Vincenzo, Sergio Baragetti, and Emanuele Borzini. "Bending Fatigue Behavior of 7075-Aluminum Alloy." Key Engineering Materials 774 (August 2018): 1–6. http://dx.doi.org/10.4028/www.scientific.net/kem.774.1.

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Light alloys are a very interesting challenge in order to have light components with high mechanical features. One of these is the 7075 aluminum alloy, which is commonly employed in aeronautic, automotive and maritime fields.On the other hand, the application of a PVD (Physical Vapor Deposition) coating can improve the hardness of the surface and the tribological properties of the component.The effectiveness of these coatings on the fatigue behavior of the sublayer material is not already clear. For this reason, bending tests on uncoated and coated specimens in air were performed in order to e
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Malopheyev, Sergey, Igor Vysotskiy, Daria Zhemchuzhnikova, Sergey Mironov, and Rustam Kaibyshev. "On the Fatigue Performance of Friction-Stir Welded Aluminum Alloys." Materials 13, no. 19 (2020): 4246. http://dx.doi.org/10.3390/ma13194246.

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This work was undertaken in an attempt to ascertain the generic characteristics of fatigue behavior of friction-stir welded aluminum alloys. To this end, different alloy grades belonging to both the heat-treatable and non-heat-treatable types in both the cast and wrought conditions were studied. The analysis was based on the premise that the fatigue endurance of sound welds (in which internal flaws and surface quality are not the major issues) is governed by residual stress and microstructure. Considering the relatively low magnitude of the residual stresses but drastic grain refinement attrib
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Kapp, J. A., D. Duquette, and M. H. Kamdar. "Crack Growth Behavior of Aluminum Alloys Tested in Liquid Mercury." Journal of Engineering Materials and Technology 108, no. 1 (1986): 37–43. http://dx.doi.org/10.1115/1.3225839.

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Crack growth rate measurements have been made in three mercury embrittled aluminum alloys each under three loading conditions. The alloys were 1100-0, 6061-T651, and 7075-T651. The loading conditions were fixed displacement static loading, fixed load static loading, and fatigue loading at two frequencies. The results showed that mercury cracking of aluminum was not unlike other types of embrittlement (i.e. hydrogen cracking of steels). Under fixed load static conditions no crack growth was observed below a threshold stress intensity factor (KILME). At K levels greater than KILME cracks grew on
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Mahdi, Huda Salih, Hussain J. Alalkawi, Muzher T. Mohamed, and Saad T. Faris. "Evaluation of creep-fatigue life and strength for AA7001-T6 under constant amplitude loading." Eastern-European Journal of Enterprise Technologies 4, no. 12 (118) (2022): 22–28. http://dx.doi.org/10.15587/1729-4061.2022.263344.

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Aluminum alloys were widely used in the construction, automotive, marine, and aviation industries due to their low specific strength, ease of manufacture, and low weight. The fatigue behavior of aluminum alloys at different temperatures is investigated. Thanks to the rapid development of armament in recent years, 7XXX ultra-high strength aluminum alloys are now used more frequently because of their non-corrosive qualities and low weight. Aluminum alloy 7001-T6 behavior is examined at the Company State for Engineering, Rehabilitation, and Inspection (SIER) in Iraq, where chemical analysis of th
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Yamada, Ryuichi, Goroh Itoh, Akira Kurumada, and Manabu Nakai. "Further Study on the Effect of Environment on Fatigue Crack Growth Behavior of 2000 and 7000 Series Aluminum Alloys." Materials Science Forum 879 (November 2016): 2153–57. http://dx.doi.org/10.4028/www.scientific.net/msf.879.2153.

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The 7000 series alloys have the highest strength in the aluminum alloys, but lower fatigue properties than 2000 series alloys. Thus, 7000 series alloys are not applied to a large proportion of the aircraft components. However, the mechanism for this has not been elucidated yet. In humid air, hydrogen embrittlement based on intergranular cracking has been known to occur in 7000 series alloys. To date, in order to explain the difference in the fatigue crack growth behavior in the two series alloys, the effect of the test environment on the fatigue crack growth of the two series alloys has been i
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Knysh, V. V., I. N. Klochkov, M. P. Pashulya, and S. I. Motrunich. "Increase of fatigue resistance of sheet welded joints of aluminum alloys using high-frequency peening." Paton Welding Journal 2014, no. 5 (2014): 21–27. http://dx.doi.org/10.15407/tpwj2014.05.04.

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Kotyk, Maciej, and Dariusz Boroński. "Investigation of Material Properties of Layered Al-Ti Material with the Use of Microspecimens." Solid State Phenomena 224 (November 2014): 216–21. http://dx.doi.org/10.4028/www.scientific.net/ssp.224.216.

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The article presents a monotonic tensile test of two materials: aluminum alloy AA2519 and titanium alloy Ti6A14V joined by means of explosive welding. The specimens were cut out in such a way that some consisted of only titanium alloy some were made of only aluminum alloy, whereas the third series were specimens consisting of both material alloys together with the bonding layer. The main goal of the research was to compare changes in the materials fatigue properties caused by explosion welding of these two alloys.
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