Predicting Fatigue Crack Growth and Fatigue Life Under Variable Amplitude Loading

• Autorzy: Jasztal M. , Kocanda D. , Tomaszek H.

Identyfikatory

DOI

10.2478/v10164-010-0024-8

• Języki publikacji: EN

Abstrakty

EN

A probabilistic approach to the description of fatigue crack growth and fatigue life estimation of a component subjected to variable amplitude loading is presented in the paper. The core of the model is a differential equation originated from the Paris formula. In order to consider the influence of overload-underload cycles existing in an exploitive load spectrum on crack growth rate for an aeronautical aluminum alloy sheet, the modified Willenborg retardation model was applied.

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Fatigue of Aircraft Structures
• Rocznik: 2010
• Tom: Iss. 2
• Strony: 37--51
• Opis fizyczny: Bibliogr. 4 poz., rys., tab., wykr., wzory

Twórcy

autor

Jasztal M.

• Military University of Technology, Warsaw, Poland

autor

Kocanda D.

• Military University of Technology, Warsaw, Poland

autor

Tomaszek H.

• Military University of Technology, Warsaw, Poland

Bibliografia

• [1] D. Kocańda, J. Torzewski, Prediction of fatigue crack growth for 2024-T3 aluminium alloy under block program loading, Biull. MUT Warsaw, Vol. LVI 4, 2007, pp. 37-55 (in Polish).
• [2] J. Torzewski, Fatigue crack growth rate and the ability of its reconstruction on the basis of the fractographic analysis for 2024-T3 aluminium alloy sheet subjected to program loadings, Ph.D. Thesis, MUT, Warsaw 2007 (in Polish).
• [3] A. Rama Chandra Murthy, G.S. Palani, Nagesh R. Iyer, An improved Wheeler model for remaining life prediction of cracked plate panels under tensile-compressive overloading. SID Vol. 1, No 3, 2005, pp. 203-213.
• [4] H. Tomaszek, J. Żurek, M. Jasztal, Forecasting of damage menaced the safety of aircraft flights. ITE-PIB Radom 2008, (in Polish).