Total fatigue life estimation of aircraft structural components under general load spectra
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Maksimović, KatarinaPosavljak, S.
Maksimović, Mirko S.
Vasovic Maksimović, Ivana
Balać, Martina
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This work presents total fatigue life prediction methodology of aircraft structural components under general load spectrum. Here is presented an effective computation procedure, that combines the finite element method (FEM) and strain-life methods to predict fatigue crack initiation life and fatigue crack growth model based on the strain energy density (SED) method. To validate computation procedure in this paper has been experimental tested specimens with a central hole under load spectrum in form of blocks. Total fatigue life of these specimens, defined as sum of crack initiation and crack growth life, was experimentally determined. Crack initiation life was computed using the theory of low cycle fatigue. Computation of crack initiation life was realized using Palmgreen-Miner’s linear rule of damage accumulation, applied on Morrow’s curves of low cycle fatigue. Crack growth life was computed using strain energy density (SED) method. The same low cyclic material properties of quenched... and tempered steel 13H11N2V2MF, used for crack initiation life computation, were used for crack growth life computation. Residual life estimation of cracked duraluminum aircraft wing skin/plate 2219-T851 under multiple overload/underload load spectrum was considered too. Presented computation results were compared with own and available experimentally obtained results.
Keywords:
SED / FEM / Fatigue life / Crack initiation / Crack growth / Aircraft structuresSource:
Lecture Notes in Networks and Systems, 2021, 153, 394-412Publisher:
- Springer
Funding / projects:
- Ministry of Education, Science and Technological Development
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Mašinski fakultetTY - CHAP AU - Maksimović, Katarina AU - Posavljak, S. AU - Maksimović, Mirko S. AU - Vasovic Maksimović, Ivana AU - Balać, Martina PY - 2021 UR - https://machinery.mas.bg.ac.rs/handle/123456789/3680 AB - This work presents total fatigue life prediction methodology of aircraft structural components under general load spectrum. Here is presented an effective computation procedure, that combines the finite element method (FEM) and strain-life methods to predict fatigue crack initiation life and fatigue crack growth model based on the strain energy density (SED) method. To validate computation procedure in this paper has been experimental tested specimens with a central hole under load spectrum in form of blocks. Total fatigue life of these specimens, defined as sum of crack initiation and crack growth life, was experimentally determined. Crack initiation life was computed using the theory of low cycle fatigue. Computation of crack initiation life was realized using Palmgreen-Miner’s linear rule of damage accumulation, applied on Morrow’s curves of low cycle fatigue. Crack growth life was computed using strain energy density (SED) method. The same low cyclic material properties of quenched and tempered steel 13H11N2V2MF, used for crack initiation life computation, were used for crack growth life computation. Residual life estimation of cracked duraluminum aircraft wing skin/plate 2219-T851 under multiple overload/underload load spectrum was considered too. Presented computation results were compared with own and available experimentally obtained results. PB - Springer T2 - Lecture Notes in Networks and Systems T1 - Total fatigue life estimation of aircraft structural components under general load spectra EP - 412 SP - 394 VL - 153 DO - 10.1007/978-3-030-58362-0_23 ER -
@inbook{ author = "Maksimović, Katarina and Posavljak, S. and Maksimović, Mirko S. and Vasovic Maksimović, Ivana and Balać, Martina", year = "2021", abstract = "This work presents total fatigue life prediction methodology of aircraft structural components under general load spectrum. Here is presented an effective computation procedure, that combines the finite element method (FEM) and strain-life methods to predict fatigue crack initiation life and fatigue crack growth model based on the strain energy density (SED) method. To validate computation procedure in this paper has been experimental tested specimens with a central hole under load spectrum in form of blocks. Total fatigue life of these specimens, defined as sum of crack initiation and crack growth life, was experimentally determined. Crack initiation life was computed using the theory of low cycle fatigue. Computation of crack initiation life was realized using Palmgreen-Miner’s linear rule of damage accumulation, applied on Morrow’s curves of low cycle fatigue. Crack growth life was computed using strain energy density (SED) method. The same low cyclic material properties of quenched and tempered steel 13H11N2V2MF, used for crack initiation life computation, were used for crack growth life computation. Residual life estimation of cracked duraluminum aircraft wing skin/plate 2219-T851 under multiple overload/underload load spectrum was considered too. Presented computation results were compared with own and available experimentally obtained results.", publisher = "Springer", journal = "Lecture Notes in Networks and Systems", booktitle = "Total fatigue life estimation of aircraft structural components under general load spectra", pages = "412-394", volume = "153", doi = "10.1007/978-3-030-58362-0_23" }
Maksimović, K., Posavljak, S., Maksimović, M. S., Vasovic Maksimović, I.,& Balać, M.. (2021). Total fatigue life estimation of aircraft structural components under general load spectra. in Lecture Notes in Networks and Systems Springer., 153, 394-412. https://doi.org/10.1007/978-3-030-58362-0_23
Maksimović K, Posavljak S, Maksimović MS, Vasovic Maksimović I, Balać M. Total fatigue life estimation of aircraft structural components under general load spectra. in Lecture Notes in Networks and Systems. 2021;153:394-412. doi:10.1007/978-3-030-58362-0_23 .
Maksimović, Katarina, Posavljak, S., Maksimović, Mirko S., Vasovic Maksimović, Ivana, Balać, Martina, "Total fatigue life estimation of aircraft structural components under general load spectra" in Lecture Notes in Networks and Systems, 153 (2021):394-412, https://doi.org/10.1007/978-3-030-58362-0_23 . .