TY  - 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 . .