Anandan, K and Brahma, KK and Raju, KN (1989) Fatigue crack propagation in AI-Li alloys. Technical Report. National Aeronautical Laboratory, Bangalore, India.
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Abstract
This document describes fatigue crack growth properties of Lital-A aluminium -lithium alloy in tests conducted at NAL. Fatigue crack growth properties of 1, 2, 3 mm thick sheet and 8, 12.5 mmthick plate material under constant and combat aircraft spectrum loading are presented. Effect of stress ratio, material thickness and rolling direction on crack growth are considered. Fatigue crack growth behavior of Lital-A series of aluminium-lithium alloys is different from that of conventional aluminium alloys. Lital-a exhibits a higher threshold stress intensity and lower fracture toughness, resulting in less favorable crack growth properties
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Aluminium lithium alloy;Fatigue crack growth;Constant amplitude;spectrum loading;Crack front tortuosity |
| Subjects: | CHEMISTRY AND MATERIALS > Composite Materials |
| Division/Department: | Structures Division, Structures Division, Structures Division |
| Depositing User: | Deputy Head Poornima Narayana |
| Date Deposited: | 19 Jul 2006 |
| Last Modified: | 24 May 2010 09:45 |
| URI: | http://nal-ir.nal.res.in/id/eprint/1987 |
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