1. Stevan Maksimović, Serbia
2. Strain Posavljak, Faculty of Mechanical Engineering,
Republic of Srpska, Bosnia and Herzegovina
3. Slobodanka Boljanović, High School of Mechanical Engineering, Belgrade, Serbia
Most load-bearing components in engineering are subjected to cyclic loading, and fatigue eventually occurs. Modern technology has developed many applications in which fatigue assessment must be taken into account to assure reliable and safe performance of structural components. In view of complexity of fatigue as process, the fatigue life analysis has to be considered through the following phases: crack initiation, crack propagation and failure. The present paper proposes the computational method for the crack growth assessment of structural components subjected to cyclic loading. The crack growth process is examined by taking into account the stress analysis and fatigue life estimation. The stress field behavior is investigated through the stress intensity factor calculation. For the residual strength assessment the stress-ratio dependence crack growth model is implemented. The crack growth behavior is examined for the failure critical aircraft component, such as wing skin. The developed model is validated by employing available experimental data and comparisons between different crack growth results show a good correlation.
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