Variations in crack growth rate behavior
Variations in crack growth rate behavior
- New search for: Artley, M.E.
- New search for: Gallagher, J.P.
- New search for: Stalnaker, H.D.
- New search for: Artley, M.E.
- New search for: Gallagher, J.P.
- New search for: Stalnaker, H.D.
Three variable amplitude stress histories based on a single repeating flight of a bomber aircraft are applied to two 610 mm wide, 4.6 mm thick,center-crack panels of 7075-T6 aluminum. The stresses in each stress history are controlled so that the stress intensity factor coefficient is maintained constant as the crack grows. The resulting fatigue crack growth (FCG) data are utilized to show that the derived variable amplitude fatigue crack growth rate (FCGR) behavior is controlled by a stress intensity factor parameter, These FCG data are also used to evaluate the influence that differentiation method, crack length measurement interval, and stress history have on the FCGR behavior and its variability. Within the limits spelled out in the text, the value of the (statistical) mean FCGR is shown to be independent of differentiation method and of crack length measurement interval. The choice of stress history is shown to affect the mean FCGR value as would be expected. (Kursetz)
Document information
Variations in crack growth rate behavior
Unterschiede im Verhalten der Groessenordnung des Risswachstums
1979
14 Seiten, 7 Bilder, 3 Tabellen, 11 Quellen
Conference paper
English
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