Prediction of Fatigue Crack Growth in Airframe Structures

##plugins.themes.bootstrap3.article.main##

##plugins.themes.bootstrap3.article.sidebar##

Jindřich Finda Andrew Vechart Radek Hédl

Abstract

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

Finda, J., Vechart, A., & Hédl, R. (2012). Prediction of Fatigue Crack Growth in Airframe Structures. PHM Society European Conference, 1(1). https://doi.org/10.36001/phme.2012.v1i1.1418
Abstract 58 | PDF Downloads 93

##plugins.themes.bootstrap3.article.details##

Keywords

maintenance, prognostics, SHM, fatigue, aircraft

References
Augustin, P. (2009). Simulation of Fatigue Crack Growth in the High Speed Machined Panel under the Constatnt Amplitude and Spectrum Loading. 25thICAF Symposium. Rotterdam.
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.
Section
Technical Papers