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Buckling of simply supported cross-ply cylindrical panels on elastic foundations

Published online by Cambridge University Press:  04 July 2016

G. J. Turvey
G. J. Turvey*
Affiliation:
Department of Engineering, University of Lancaster
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Extract

Current design studies for tomorrow’s aircraft are increasingly utilising composite materials, especially fibre reinforced plastics, in a primary load-bearing role. By suitably orienting and aggregating (stacking) uni-directional pre-pregs (laminae) of these materials, very stiff and very light laminates or sheets may be produced. These two attributes suggest that such laminates are well suited to the role of face sheets (skins) in sandwich panels, which are commonly used in a primary load-bearing context in aircraft construction.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 81 , Issue 794 , February 1977 , pp. 88 - 91
Copyright
Copyright © Royal Aeronautical Society 1977 

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References

1. Turvey, G. J. Buckling of simply supported laminated plates on elastic foundations. The Aeronautical Journal, Vol 80, No 792, pp 530–535, December 1976.Google Scholar
2. Brush, D. O. and Almroth, Bo. O. Buckling of Bars, Plates and Shells, McGraw-Hill, New York, 1975.Google Scholar
3. Pflüger, A. Stabilitatsprobleme der Elastostatik, Springer-Verlag, Berlin, Second Edition, 1964.Google Scholar