Advanced SearchSearch Tips
Stress Spectrum Algorithm Development for Fatigue Crack Growth Analysis and Experiment for Aircraft Wing Structure
facebook(new window)  Pirnt(new window) E-mail(new window) Excel Download
 Title & Authors
Stress Spectrum Algorithm Development for Fatigue Crack Growth Analysis and Experiment for Aircraft Wing Structure
Chun, Young Chal; Jang, Yun Jung; Chung, Tae Jin; Kang, Ki Weon;
  PDF(new window)
Fatigue cracks can be generated in aircraft as a result of the cumulative time spent during flight operations, which can extend for long periods of time and cover a variety of missions. If a crack occurs in an aircraft's main spar, it can generate many problems, including a lift time reduction. To solve this problem, it was necessary to perform an analysis of fatigue crack growth in the fatigue critical locations. Much time and expense is involved in generating the stress needed for a crack propagation analysis over a long period of time to obtain the amount of data required for an actual aircraft. In this paper, an algorithm is developed that can calculate the spectrum of stress over a long period of time for a mission by the Southwest Research Institute, which is based on the short-time load factor data produced using the peak-valley cycle counting method.
Stress-Spectrum;Algorithm;Peak-Valley Cycle Counting;Fatigue Critical Location;Wing Spar;
 Cited by
Yoon, Y. I., Kim, S. T., 2010, "Aging Aircraft's Main Damage Characteristics and Effects of Structural Degradation Induced by Pitting Corrosion Fatigue," Proceeding of Spring Conference KSME., pp.101-107.

Kim, W. D., 2007, "Fatigue Life Prediction of Composite Patch for Edge Cracked Aluminum Plate," Trans. of the KSAS., Vol. 35, No. 1, pp. 51-57.

Lee, D. H., Kwon, A. J., You, W. H., Choi, J. B. and Kim, Y. J., 2009, "Evaluation of Fatigue Crack Initiation Life in a Press-Fitted Shaft Considering the Fretting Wear," Trans. Korean Soc. Mech. Eng. A, Vol. 33, No.10, pp.1091-1098. crossref(new window)

Hur, J. W., 2010, "Study on Fatigue Life Estimation for Aircraft Engine Support Structure," Trans. Korean Soc. Mech. Eng. A, Vol. 34, No.11, pp. 1667-1674. crossref(new window)

Kim, Y. J., Kim, H. G., Kim, C. Y., Chang, J. J. and Lee, M. Y., 2013, " Fatigue Analysis to Determine the Repair Limit for the Damaged Fastener Hole of Aging Aircraft(P-3CK)," proceeding of JKSAS, pp.959-966.

Kang, K. W., Koh, S. K., Choi, D. S., Kim, T. S., 2010, "Fatigue Life and Stress Spectrum of Wing Structure of Aircraft," Trans. Korean Soc. Mech. Eng. A, Vol. 34, No. 9, pp. 1185-1191. crossref(new window)

SwRI Report, 1996, "F-5 FMS Durability and Damage Tolerance Update Revised Final DADTA Report - F-5E/F Republic of Korea Air Force," SWRI 06-4222.

Daniel Ferreira V. Mattos, Alberto W.S. Mello Junior, Fabricio N.Ribeiro, Jan.-Jun. 2009, "F-5M DTA Program," Journal of Aerospace Technology and Management, Vol.1, No.1, pp. 113-120. crossref(new window)

Lee, H. Y., Hwang, M. S. and Kim, J. W., 2002, "Analysis Fatigue Life & Damage Tolerance for Engine Mount," Proceeding of KSAS, pp. 408-411.