Components of machines and structures are frequently subjected to repeated loading which may lead to their failure due to fatigue. For prevention of such failures, it is very important to establish efficient methods that enable determination of fatigue life. In view of complexity of fatigue as process, fatigue life analysis has to be considered as crack initiation phase and crack growth phase. In this paper authors have formulated computational method for crack growth life prediction of structural components subjected to cyclic loading. For fatigue life estimation it is necessary to consider and include adequate criteria. Criteria analysed in this paper are based on the theory of fracture mechanics. As a primary parameter, the stress intensity factor is defined for fatigue life analysis. The functional relationship between the stress intensity factor and crack length, which is needed for fatigue life estimation for crack propagation from the initial to the critical length is obtained using analytical and/or numerical approaches. An special attention in this work is focused on aircraft wing skin structural components.
Predicted results were compared with available experimental data. A good agreement between the computation and experimental results has been obtained.
Mehanika i konstrukcije