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Production and Repair of Fastened Joints Incorporating Cold Expansion
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English
Abstract
Fastened joints are an integral part of aircraft design. Due to their complexity and function, they are also the primary source of structural fatigue problems. The incorporation of residual compressive stresses around a fastener hole greatly enhances the fatigue resistance and integrity of a fastened joint. This paper describes the split-sleeve cold expansion method to create residual compressive stresses which extend the fatigue life of holes in both new structure and field repairs. Data from test programs highlight process benefits and crack retardation effects for various specimen configurations. Other process features such as cold expansion to size are explained, along with the status of process automation.
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Citation
Reid, L., Easterbrook, E., and Rufin, A., "Production and Repair of Fastened Joints Incorporating Cold Expansion," SAE Technical Paper 922400, 1992, https://doi.org/10.4271/922400.Also In
References
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- Fatigue Technology Inc. “Cold Expansion to Size of Fastener and Other Holes Using the Split Sleeve System (Cx2s) and Countersink Cold Expansion Nosecap (CCx)” January 1985
- Reid, L.F. Rufin, A.C. “F-16N Fuel Shelf Joint Fatigue Life Extension by Cold Expansion of Fastener Holes” Proc. of the 1991 USAF Aircraft Structural Integrity Program Conference 1992
- Phillips, J.L. “Sleeve Coldworking Fastener Holes” 1 Air Force Materials Laboratory Report AFML-TR-74-10 February 1974
- Tiffany, C.F. Stewart, R.P. Moore, T.K. “Fatigue and Stress Corrosion Test of Selected Fasteners/Hole Processes” Aeronautical Systems Division Report ASD-TR-72-111 January 1973
- Schwarmann, L. “On Improving the Fatigue Performance of a Double Shear Lap Joint” International Journal of Fatigue 5 2 April 1983
- Bolstad, R.T. Landy, M.A. “Hole Cold Expansion of Dissimilar Aluminum Alloys Using Cx2s” Fatigue Technology Inc. Technical Report 6093-1C September 1986