Hostname: page-component-77c89778f8-rkxrd Total loading time: 0 Render date: 2024-07-17T02:30:28.606Z Has data issue: false hasContentIssue false
  • English
  • Français

Stiffened panels with varying stiffener sizes

Published online by Cambridge University Press:  04 July 2016

F. W. Williams
F. W. Williams*
Affiliation:
Department of Civil Engineering, University of Birmingham
Get access Rights & Permissions [Opens in a new window]

Extract

Stiffened panels usually consist of a skin of uniform thickness with several identical equally spaced longitudinal stiffeners. This paper demonstrates that the weight of a panel which is designed to have a specified initial buckling load, in uniform longitudinal compression, can be reduced by using more than one size of stiffener.

Initial buckling stresses quoted were all obtained using the computer program VIPAL, which is based on a recent “exact” method which allows for coupling between all possible modes. In this method the panel is considered as an assembly of thin uniform flat rectangular plates which are rigidly connected together along their longitudinal edges and are simply supported at their ends. The in-plane destabilising effects of the longitudinal compressive stress on the behaviour of these plates are included.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 77 , Issue 751 , July 1973 , pp. 350 - 354
Copyright
Copyright © Royal Aeronautical Society 1973 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Williams, F. W. Computation of natural frequencies and initial buckling stresses of prismatic plate assemblies. Journal of Sound and Vibration, Vol 21, No 1, pp 87–106. March 1972.Google Scholar
2. Wittrick, W. H. A unified approach to the initial buckling of stiffened panels in compression. Aeronautical Quarterly, Vol XIX, pp 265–283. August 1968.Google Scholar
3. Wittrick, W. H. and Williams, F. W. Natural vibrations of thin Prismatic, flat-walled structures. High speed computing of elastic structures. Proceedings of IUTAM Symposium 1970, pp 563-588.Google Scholar
4.Trie Royal Aeronautical Society. Structures data sheets, Vol II, 02.01.01.Google Scholar
5. Williams, F. W. and Wittrick, W. H. Numerical results for the initial buckling of some stiffened panels in compression. Aeronautical Quarterly, Vol XXIII, pp 24–40. February 1972.Google Scholar
6. Williams, F. W. Initial buckling curves for a simply supported plate with a vee-shaped corrugation. Civil Engineering and Public Works Review, Vol 67, pp 239–242. March 1972.Google Scholar