PSI - Issue 41

Slobodanka Boljanović et al. / Procedia Structural Integrity 41 (2022) 704 – 711 Slobodanka Boljanović et al. / Structural Integrity Procedia 00 (2019) 000 – 000

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By examining relevant comparisons shown in Fig, 6, it can be concluded that, if the value of crack length in depth direction increases by 25 %, the residual life decreases by 13%. Furthermore, from Fig. 7 it is evident that increasing the thickness by 20% the fatigue strength increases by about 95% for considered plate-type configurations with quarter elliptical flaw. 5. Conclusions The need to develop sustainable computational-based technologies that should ensure a good balance between safe-integrity protection and relevant service load environment is one of the key challenges in aerospace and automotive applications. Thus, through the analytical strategy proposed, the variational principle has been utilized to derive the governing fatigue solutions and boundary conditions, in which the driving force interactions and crack growth progression are taken into account. Therefore, the present paper can be a guide for researchers and experts in the area of sustainability of large moving systems in order to discuss reliable fatigue life trends via damage tolerance-based requirements during real-time service operations. Acknowledgements The present research work was supported by the Serbian Ministry of Education, Science and Technological Development through the Mathematical Institute of the Serbian Academy of Sciences and Arts, Belgrade and the COST Association, Brussels, Belgium within the Action CA18203, which is gratefully acknowledge. Bol janović, S., Maksimović, S., Djur ić, M., 2016 . Fatigue Strength Assessment of Initial Semi-Elliptical Cracks. International Journal of Fatigue 92, 548-556. Boljanović, S., Maksimović, S., Carpinteri, A., Ćosić, M., 2019. Fatigue Endurance Design of Plates with Two Semicircular Edge Notches and One Quarter-Elliptical Corner Crack or Through-The-Thickness Crack. International Journal of Fatigue 127, 45-52. Boljanović, S., Carpinteri, A. , 2020. Computational Analysis of a Surface Corner Crack under Cyclic Loading. Procedia Structural Integrity 28, 2370-2377. Bolj anović, S., Carpinteri, A., 2021. Modelling of the Strength Degradation Due to a Semi-Elliptical Flaw. Forces in Mechanics 4, 1000200. Carpinteri, A. Handbook of Fatigue Crack: Propagation in Metallic Structures, Amsterdam, Elsevier Science B.V., 1994. Grover, H.J., Hyler, W.S., Kuhn, P., Landers, C.B., Howell, F.M., Axial-Load Fatigue Properties of 24S-T and 75S-T Aluminum Alloy as Determined in Several Laboratories, NASA TN-2928, 1953. Huang, X., Moan, T., 2007. Improved Modeling of the Effect of R -Ratio on Crack Growth Rate. International Journal of Fatigue 29, 591 – 602. Mikheevskiy, S., Glinka, G., Algera, D., 2012. Analysis of Fatigue Crack Growth in an Attachment Lug Based on the Weight Function Technique and the UniGrow Fatigue Crack Growth Model. International Journal of Applied Fatigue 42, 88 – 94. Newman, Jr. J.C., Raju, I.S. Stress-Intensity Factor Equations for Cracks in Three-Dimensional Finite Bodies Subjected to Tension and Bending Loads, NASA TM-85793, Langley Research Center, Hampton, Virginia, 1984. Noroozi, A.H., Glinka, G., Lambert, S., 2007. A Study of the Stress Ratio Effects on Fatigue Crack Growth Using the Uni fied Two-Parameter Fatigue Crack Driving Force. International Journal of Fatigue 29, 1616 – 1633. Kim, J.H., Lee, S.B., Hong, S.G., 2003. Fatigue Crack Growth Behavior of Al7050-T7451 Attachment Lugs under Flight Spectrum Variation. Theoretical and Applied Fracture Mechanics 40(2), 135-144. Kujawski D., 2001. A New (  K + K max ) 0.5 Driving Force Parameter for Crack Growth in Aluminium Alloy. International Journal of Fatigue 23, 733 – 740. Zhan, W., Lu, N., Zhang, C., 2014. A New Approximate Model for the R – Ratio Effect on Fatigue Crack Growth Rate. Engineering Fracture Mechanics 119, 85 – 96. References