Fatigue Crack Growth in 7050T7451 Aluminium Alloy Thick Section ...

DSTO-TR-1477Simulated flight hours0 2000 4000 6000 8000 10000 120005Simulated flight hours0 2000 4000 6000 8000 10000 12000104KSIF 191 420MPa peenKSIF 193 420MPa peenKSIF 204 420MPa peenKSIF 147 420MPa peenKSIF 142 420MPa peen0.1610.1Crack depth mm.320.120.08Crack depth inchCrack depth mm.0.10.010.001Crack depth inch1000 5 10 15 20 25 30 35 40IARPO3a + 5ML Spectra0.040.01KSIF 191 420MPa peenKSIF 193 420MPa peenKSIF 204 420MPa peenKSIF 147 420MPa peenKSIF 142 420MPa peen0.0010 5 10 15 20 25 30 35 40IARPO3a + 5ML SpectraABFigure 19 The result of the quantitative fractographic examination of cracks in the peened specimens loadedto a peak stress of 420MPa.0.0001Simulated flight hours0 1000 2000 3000 4000 5000 6000 7000 80003.5Simulated flight hours0 1000 2000 3000 4000 5000 6000 7000 80001032.5KSIF 186 450MPa peenKSIF 146 450MPa peenKSIF 164 450MPa peenKSIF 178 450MPa peenKSIF 183 450MPa peen0.120.110.1Crack depth mm.21.50.080.06Crack depth inch.Crack depth mm.0.10.010.001Crack depth inch.10.040.010.5000 5 10 15 20 25IARPO3a + 5ML SpectraA0.02KSIF 186 450MPa peenKSIF 146 450MPa peenKSIF 164 450MPa peenKSIF 178 450MPa peenKSIF 183 450MPa peen0.0010 5 10 15 20 25IARPO3a + 5ML SpectraFigure 20 The result of the quantitative fractographic examination of cracks in the peened specimens loadedto a peak stress of 450MPa.B0.000117