Shepherd, G.E. (2000, June). The potential for using solid phase welding to repair cracks that may occur on thin aluminium aircraft wing structures. 2nd International Symposium.
Shepherd G E. "The potential for using solid phase welding to repair cracks that may occur on thin aluminium aircraft wing structures". 2nd International Symposium (Jun.2000).
Shepherd, G E. "The potential for using solid phase welding to repair cracks that may occur on thin aluminium aircraft wing structures". 2nd International Symposium (Jun.2000).
Shepherd G.E.The potential for using solid phase welding to repair cracks that may occur on thin aluminium aircraft wing structures. 2nd International Symposium. 2000 Jun; .
Shepherd 2000, 'The potential for using solid phase welding to repair cracks that may occur on thin aluminium aircraft wing structures', 2nd International Symposium. Available from: https://www.twi-global.com/technical-knowledge/fsw-symposium-papers/FSWSymposia-200006-9Paper03.pdf.
Shepherd GE. The potential for using solid phase welding to repair cracks that may occur on thin aluminium aircraft wing structures. 2nd International Symposium. 2000;. https://www.twi-global.com/technical-knowledge/fsw-symposium-papers/FSWSymposia-200006-9Paper03.pdf.
Shepherd GE . The potential for using solid phase welding to repair cracks that may occur on thin aluminium aircraft wing structures. 2nd International Symposium. 2000 Jun;. https://www.twi-global.com/technical-knowledge/fsw-symposium-papers/FSWSymposia-200006-9Paper03.pdf.
The potential for using solid phase welding to repair cracks that may occur on thin aluminium aircraft wing structures
- Shepherd G.E.
- Shepherd G.E.
June 2000
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The use of friction stir welding for the repair of cracks in aluminium alloy 2024 aircraft wing skin structures, and the repair fatigue life were investigated. An artificial crack, 42 mm in length, in a flat section 2024-T351 alloy of 3.2 mm thickness was welded using a run-off plate, a landing plate attached by riveting to simulate service conditions, and the assembly subjected to fatigue testing. The fatigue results were compared with those of the parent material.
2nd International Symposium, 26-28 Jun 2000, Session 9, Paper 03
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