Abstract
This paper details investigations into the importance of the crack growth rate data used in conjunction with FASTRAN to make fatigue crack growth predictions. Selected fighter and transport aircraft load spectra have been used in the present investigation to determine the regions of the crack growth rate curve that dominate the crack growth predictions. The results of the analysis show that universally crack growth predictions under typical aircraft load spectra utilize a significant portion of the crack growth rate curve close to the threshold region. Of note is the observation that both fighter and transport aircraft display this same behaviour throughout the entire crack growth prediction. This finding demonstrates the requirement for accurate crack growth rate data for small cracks to obtain appropriate total fatigue life predictions.
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References
Newman Jr., J.C., Phillips, E.P., Swain, M.H.: International Journal of Fatigue 21(2), 109–119 (1999)
Ranganathan, N., et al.: International Journal of Fatigue 33(3), 492–499 (2008)
Wu, X.R., et al.: Fatigue and Fracture of Engineering Materials and Structures 21(11), 1289–1306 (1998)
Molent, L., Singh, R., Woolsey, J.: Engineering Failure Analysis 12(1), 13–24 (2005)
Goldsmith, N.T., Clark, G.: Analysis and Interpretation of Aircraft Component Defects Using Quantitative Fractography. In: Bernard, S.M., Susil, P.K. (eds.) ASTM International on Quantitative Methods in Fractography (1990)
Barter, S., et al.: Journal of Engineering Failure Analysis 12(1), 99–128 (2005)
Wallbrink, C., Hu, W.: Advanced Materials Research 41-42, 189–197 (2008)
Jones, R., Molent, L., Pitt, S.: In. Proceedings of International Conference on Fatigue Damage of Structural Materials VI, Hyannis, USA (2006)
Tiong, U.H., Jones, R.: International Journal of Fatigue 31(6), 1046–1053 (2009)
Newman Jr., J. C.: Fastran II - a Fatigue Crack Growth Structural Analysis Program. NASA TM-104159, NASA (1992)
Elber, W.: The Damage Tolerance in Aircraft Structures. In: ASTM STP, vol. 486. p. 230-242 (1971)
Diab, H., Goldsmith, R.: Fractography Results of F-111 Loads Interpretation and Truncation Validation (LITV) Coupon Test Program. DSTO-TR-2000, DSTO (2007)
Barter, S.A.: Fatigue Crack Growth in 7050-T7451 Aluminium Alloy Thick Section Plate with Surface Condition Simulating Some Regions of the F/A-18 Structure. DSTO-TR-1458 (2003)
Mongru, D.: Direct Current Potential Drop System Calibration of 1015-T6 Notched and Centre Crack Growth Coupons. DSTO-DP-1110, Melbourne, DSTO (2009)
Iyyer, N., et al.: International Journal of Fatigue 29(9-11), 1584–1607 (2007)
Newman, J.A., Piascik, R.S.: International Journal of Fatigue 26(9), 923–927 (2004)
Newman Jr., J.C., Yamada, Y.: International Journal of Fatigue 32(6), 879–885 (2010)
Ruschau, J.J., Newman Jr., J.C.: Journal of ASTM International 5(7) (2008)
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Wallbrink, C., Jackson, P., Hu, W. (2011). Crack Growth Rate Curves: Which Part Dominates Life Prediction and When?. In: Komorowski, J. (eds) ICAF 2011 Structural Integrity: Influence of Efficiency and Green Imperatives. Springer, Dordrecht. https://doi.org/10.1007/978-94-007-1664-3_24
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DOI: https://doi.org/10.1007/978-94-007-1664-3_24
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