Fatigue crack growth tests on 6082-T6 aluminium specimens have been carried out. The single edge notched tension specimens had a spark eroded 0.2 mm deep starter notch. In order to measure the crack growth, a special direct current potential drop method was used. The experiments were carried out at
VARIABLE AMPLITUDE LOADING OF SMALL FATIGUE CRACKS IN 6261-T6 ALUMINIUM ALLOY
β Scribed by M. N. James; E. R. de los Rios
- Book ID
- 109013761
- Publisher
- John Wiley and Sons
- Year
- 1996
- Tongue
- English
- Weight
- 989 KB
- Volume
- 19
- Category
- Article
- ISSN
- 8756-758X
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The fatigue crack growth (FCG) behavior of 7075-T651 aluminum alloy was studied under constant and variable amplitude loadings in vacuum, air and 1% NaCl solution. In the study of constant amplitude loading fatigue, the stress ratios were 0.1 and 0.85 and the loading frequency was 10 Hz. In the stud
Abe&&-A technique for &meting fatigue crack prope&on in notched plates subjected to variable amplitude~boutlincdinthirpeper.Ane~~~tic~~ekmcntmodelisusedtodetermiaetbe eht of notch geometry and the rehal plastic deformations. The analytic model for crack growth is based on an eactive StreSl intensity