Crack growth resistance curves have been determined for crack-divider laminates in which layers of 2024T3 aluminum alloy are adhesively bonded to layers of 7075-T6 alloy. Results are compared with the fracture resistance of laminates consisting wholly of each material, the layer thickness being the
Fatigue failure of adhesively patched 2024-T3 and 7075-T6 clad and bare aluminium alloys
โ Scribed by D. L. DUQUESNAY; P. R. UNDERHILL; H. J. BRITT
- Book ID
- 109014060
- Publisher
- John Wiley and Sons
- Year
- 2005
- Tongue
- English
- Weight
- 260 KB
- Volume
- 28
- Category
- Article
- ISSN
- 8756-758X
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For transport aircraft with long lifetimes, crack growth data to implement the durability life requirements in the low AK range are needed. This is the region comprising most of the lifetime for the cracks of interest, and it is also the region where there is little data available. Crack growth data
## Experimental investigations have been carried out to study the effect of specimen configuration and loading history on the crack growth behaviour of 2024-T3 aluminium alloy at room temperature. It has been observed that fatigue crack growth rate in specimens loaded symmetrically is higher than