In this paper, the behavior of 7075-T6 aluminum alloy under low cycle fatigue (LCF) loading is experimentally and numerically investigated using continuum damage mechanics (CDM). An experimental procedure is established to identify the damage parameters for Al 7075-T6. A damage-coupled explicit finite element code is developed using the experimentally extracted damage parameters to study the material behavior under LCF loading. Moreover, fractographic examinations are conducted to identify the fatigue crack initiation locations and propagation mechanisms. The model is employed for life-time assessment of stringer-skin connection of a fuselage and the results are compared with the data available in the literature.
Identification and Validation of a Low Cycle Fatigue Damage Model for Al 7075-T6 Alloy
Contributed by the Materials Division of ASME for publication in the JOURNAL OF ENGINEERING MATERIALS AND TECHNOLOGY. Manuscript received May 29, 2013; final manuscript received September 8, 2014; published online November 7, 2014. Assoc. Editor: Hanchen Huang.
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Masih, S., Mashayekhi, M., and Torabian, N. (January 1, 2015). "Identification and Validation of a Low Cycle Fatigue Damage Model for Al 7075-T6 Alloy." ASME. J. Eng. Mater. Technol. January 2015; 137(1): 011004. https://doi.org/10.1115/1.4028840
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