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http://dx.doi.org/10.5762/KAIS.2020.21.7.638

A Study on the Life Management and Improvement of Vulnerable Parts of Aircraft Structures  

Choi, Hyoung Jun (Defense Agency for Technology and Quality)
Park, Sung Jae (Defense Agency for Technology and Quality)
Publication Information
Journal of the Korea Academia-Industrial cooperation Society / v.21, no.7, 2020 , pp. 638-644 More about this Journal
Abstract
This study examines cracks that occur under the load of an aircraft. The life of aircraft vulnerability structures was analyzed and structural fitting improvements were made. Structural integrity and safety have been achieved through preemptive life expectancy and life management of aircraft structures. The crack size inspection capability of the aircraft under analysis is 0.03inch, compared with 0.032inch, which is the lowest of the three vulnerable parts. In addition, the fatigue life analysis results in approximately 1450 operating hours, the lowest of the three vulnerable parts relative to the aircraft's required life of more than 15000 operating hours, which increased the repeat count of the aircraft's initial and re-inspection times, and hence raised the resulting costs and manpower consumption. Finally, the features were improved through structural fitting of the identified three weak parts. The lowest critical crack size was secured at 0.13 through increased structural resistance to generated cracks and increased aircraft safety. The lowest structural fatigue life for cracks occurring during aircraft operation is 25000 operating hours, which are analyzed above the required structural life, resulting in more optimized improvements than the repair costs and excessive fitting range caused by cracks and fractures.
Keywords
Structure Flaw; Critical Flaw; Fatigue Life; Structural Life Analysis; Structural Fitting;
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  • Reference
1 "Aircraft Structural Integrity Program (ASIP)," MIL-STD-1530D, 2016.
2 S.J. Iee, S.W. Jin, D.H. Kim, J.H. Yoon, "Advance Damage Tolerance Analysis Methodology for Service Life Extension Program of Military Aircraft," Journal of the Korean Society for Aviation and Aeronautics, pp. 178-181, 2010.   DOI
3 "Department of Defense Joint Service Specification Guide : Aircraft Structures," JSSG-2006.
4 D.Y. Hwang, "Damage Tolerance Design and Prediction of Fatigue Life in Aircraft Structure," The Korean Society of Mechanical Engineers, 35(6) pp. 468-480, 1995.
5 Osgood, C. C, "Fatigue Design," Pergamon Press, 1982.
6 Forman, R. G, Kearney, V. E, Eagle, R. M, “Numerical Analysis of Crack Propagation in Cyclic-Loaded Structures,” Tran. ASME. J. Basic En., Vol. 89, No. 3, pp. 459-464, 1967.   DOI
7 S.W. Jin, J.H. Jung, S.I. Beak, C.O. Moon, "RoKAF F-16C/D Block 32 Airframe Durability and Damage Tolerance Analysis Update Based on Actual Operational CSFDR Data," Journal of the Korean Society for Aviation and Aeronautics, pp. 227-230, 2013.
8 Y.C. Chun, Y.J. Jang, T. J, Chung, K. W. Kang, "TStress Spectrum Algorithm Development for Fatigue Crack Growth Analysis and Experiment for Aircraft Wing Structure," Transactions of the Korea Society of Mechanical Engineers-A 39(1), pp. 1281-1286, 2015. DOI: http://dx.doi.org/10.3795/KSME-A.2015.39.12.1281   DOI
9 "Damage Tolerance and Fatigue Evalution of Structure," AC 25.571.