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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

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