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Effect of rivet spacing on crippling loads of joined aluminium angles

Published online by Cambridge University Press:  04 July 2016

F. J. Appl  and
M. B. Whelton
F. J. Appl
Affiliation:
School of Aerospace, Mechanical, and Nuclear Engineering. University of Oklahoma
M. B. Whelton
Affiliation:
USAF, Norman, Oklahoma
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Extract

The possibility of failure by buckling of structural members subjected to compressive loadings concerns every structural engineer and designer. In the design of aircraft, these compression members may be stringers, spars, or other stiffeners. Various geometrical sizes and shapes of stiffeners are used in aircraft construction. They are either extruded in the desired shape, machined, or formed out of sheet metal on a hand brake. They may be I-beams, Z-beams, channels, or angles. They may be used singly or may be joined to form a built-up or composite member. The actual choice of the size and shape of the stiffener depends upon the forces and moments to which it will be subjected.

Type
Technical notes
Information
The Aeronautical Journal , Volume 77 , Issue 750 , June 1973 , pp. 302 - 304
Copyright
Copyright © Royal Aeronautical Society 1977 

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References

1. Bleich, F. Buckling strength of metal structures. New York: McGraw-Hill Book Company, Inc., pp. 302–357. 1952.Google Scholar
2. Bridget, F. J., Jerome, C. C, and Vosseller, A. B. Some newexperimentson buckling of thin-wall construction.TransactionsoftheAmericanSocietyof Mechanical Engineers, Vol 56, pp. 569–578. 1924.Google Scholar
3. Den Hartog, J. P. Advanced strength of materials. New York:McGraw-Hill Book Company, Inc., pp. 301–306. 1952.Google Scholar
4. Lundquist, E. E. The compressive strength of duralumin columns of equal angle section. NACA Technical Note No 413, Washington. 1932.Google Scholar
5. Lundquist, E. E. Local instability of centrally loaded columns of channel section and z-section. NACA Tech nical Note No 722, Washington, 1939.Google Scholar
6. Lundquist, E. E. and Fligg, C. M. A theory for primary failure of straight centrally loaded columns. NACA Tech nical Report No 582, Washington, 1937.Google Scholar
7. Metallic materials and elements for aerospace vehicle structures. Military Handbook 5A, Washington. DC: US Government Printing Office, 1966.Google Scholar
8. Parr, W. S., and Beakley, W. M. An investigation of duraluminum channel section struts under compression. Journal of the Aeronautical Sciences, Vol 3, No 1, pp. 21–25. September 1935.Google Scholar
9. Shanley, F. R. Inelastic column theory. Journal of the Aeronautical Sciences, Vol 14, No 5, pp. 261–268. May 1947.Google Scholar
10. Timoshenko, S. P., and Gere, J. M. Theory of elastic stability. New York: McGraw-Hill Book Company, Inc.. pp. 348–363. 1961.Google Scholar