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Numerical Results for the Initial Buckling of Some Stiffened Panels in Compression

Published online by Cambridge University Press:  07 June 2016

F W Williams  and
W H Wittrick
F W Williams
Affiliation:
Department of Civil Engineering, University of Birmingham
W H Wittrick
Affiliation:
Department of Civil Engineering, University of Birmingham
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Summary

In previous papers the basis of a matrix approach to the initial buckling or vibration of prismatic structures consisting of a series of thin flat rectangular plates rigidly connected together along their longitudinal edges has been developed. The present paper provides numerical results for the buckling, under uniform longitudinal compression, of a series of panels with unflanged or flanged integral stiffeners, or with Z-section stiffeners; the results are compared with those obtained by other methods and with published results, including an appropriate Royal Aeronautical Society Structures Data Sheet. It was found that considerable inaccuracies can arise from the usual methods of analysis and the authors believe that these justify the use of computer programmes, such as the ones used to obtain the results of this paper, at least at the final design stage.

Type
Research Article
Information
Aeronautical Quarterly , Volume 23 , Issue 1 , February 1972 , pp. 24 - 40
Copyright
Copyright © Royal Aeronautical Society. 1972

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References

1. Wittrick, W H A unified approach to the initial buckling of stiffened panels in compression. Aeronautical Quarterly, Vol XIX, pp 265-283, 1968.Google Scholar
2. Williams, F W Wittrick, W H Computational procedures for a matrix analysis of the stability and vibration of thin flat-walled structures in compression. International Journal of Mechanical Sciences, Vol 11, pp 979-998, 1969.CrossRefGoogle Scholar
3. Wittrick, W H General sinusoidal stiffness matrices for buckling and vibration analyses of thin flat-walled structures. Internationaljournal of Mechanical Sciences, Vol 10, pp 949-966, 1968.Google Scholar
4. Wittrick, W H Williams, F W Natural vibrations of thin, prismatic, flat-walled structures. IUTAM Symposium on High Speed Computing of Elastic Structures, Liège, August 1970. (To be published).Google Scholar
5. Wittrick, W H Williams, F W A general algorithm for computing natural frequencies of elastic structures. Quarterly Journal of Mechanics and Applied Mathematics, Vol XXIV, pp 263-284, August 1971.CrossRefGoogle Scholar
6. Williams, F W Natural frequencies of repetitive structures. Quarterly Journal of Mechanics and Applie Mathematics, Vol XXIV, pp 285-310, August 1971.Google Scholar
7. Williams, F W The Royal Aeronautical Society, Structures Data Sheets, Vol 2, 02.01.28-37.Google Scholar
8. Grayley, M E The limitations of wide strut analyses for determination of the optimum proportions of panels having unfianged integral stiffeners. Technical Note, Journal of the Royal Aeronautical Society, Vol 73, pp 888-890, October 1969.Google Scholar
9. Farrar, D J The design of compression structures for minimum weight. Journal of the Royal Aeronautical Society, Vol 53, pp 1041-1052, November 1949.CrossRefGoogle Scholar
10 Catchpole, E J The optimum design of compression surfaces having unflanged integral stiffeners. Journal of the Royal Aeronautical Society, Vol 58, pp 765-768, November 1954.Google Scholar
11. Rothwell, A Coupled modes in the buckling of panels with Z-section stringers in compression. Technical Note, Journal of the Royal Aeronautical Society, Vol 72, pp 159-163, February 1968.Google Scholar
12. Rothwell, A The Royal Aeronautical Society. Structures Data Sheets, Vol 2, 02.01.25.Google Scholar