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http://dx.doi.org/10.5139/JKSAS.2013.41.12.959

Fatigue Analysis to Determine the Repair Limit for the Damaged Fastener Hole of Aging Aircraft(P-3CK)  

Kim, Young-Jin (Sacheon Regional Center, Defense Agency for Technology and Quality)
Kim, Hyeung-Geun (Sacheon Regional Center, Defense Agency for Technology and Quality)
Kim, Chang-Young (Sacheon Regional Center, Defense Agency for Technology and Quality)
Chang, Joong-Jin (Sacheon Regional Center, Defense Agency for Technology and Quality)
Lee, Mal-Young (Sacheon Regional Center, Defense Agency for Technology and Quality)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.41, no.12, 2013 , pp. 959-966 More about this Journal
Abstract
In this study, based on P-3CK project using aging aircraft without any design information, the structural assessments of fastener holes to repair the short edge distance defects are investigated. For this purpose, the nacelle longeron which has many defects is selected and then conservative stress is calculated by performing the static analysis of 1.5ED, 1.8ED, 2.0ED defects of longeron fastener holes. This result applies to TWIST standard load spectrum to generate flight load spectrum. Then the crack growth analysis is performed by using flight load spectrum. Through this, the validity of a repaired fastener hole is evaluated. Finally, the standard of repair and the period of maintenance for a defected fastener hole are established.
Keywords
Aging Aircraft; Short Edge Distance; TWIST; Crack Growth Analysis;
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