Prediction of Fatigue Crack Growth in Airframe Structures
The paper describes the general proposal, function and performance of a prognostics system for fatigue crack growth in airframe structures. Prognostic capabilities are important to a superior Structural Health Monitoring System (SHM). An aim of the prognosis is estimation / prediction of a system / subsystem / structure remaining life, i.e. the time at which damage (crack, corrosion, wear, delamination, disbonding, etc.) will result in a failure of the considered element.
How to Cite
maintenance, prognostics, SHM, fatigue, aircraft
Beden, S. M. & Abdullah, S. & Ariffin, A. K. (2009). Review of fatigue Crack Propagation Models for Metallic Components. European Journal of Scientific Research. ISSN 1450-216X Vol.28 No.3.
Federal Aviation Regulations (FAR). PART 23 Airworthiness standards: Normal, utility, acrobatic, and commuter category airplanes.
Federal Aviation Advisory Circular (AC). AC 23-13A – Fatigue, Fail-Safe, and Damage Tolerance Evaluation of Metallic Structure for Normal, Utility, Acrobatic, and Commuter Category Airplanes.
Forman, R. G. & Shivakumar, V & Cardinal J.W. & Wiliams, L.C. & McKeigham, P.C. (2005), Fatigue Crack Growth Database for Damage Tolerance Analysis, DOT/FAA/AR-05/15
NASGRO Reference Manual, version 4.2, NASA Johnson Space Center, Southwest Research Institute, San Antonio.
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