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Buckling of Sandwich Panels with Laminated Face Plates

Published online by Cambridge University Press:  07 June 2016

T R A Pearce  and
J P H Webber
T R A Pearce
Affiliation:
Department of Aeronautical Engineering, University of Bristol
J P H Webber
Affiliation:
Department of Aeronautical Engineering, University of Bristol
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Summary

The buckling of simply-supported sandwich panels, made up from fibre reinforced laminated face plates and honeycomb cores, is considered when they are subjected to uniform end loading. Numerical results are given for both overall buckling and face plate wrinkling for panels having typical carbon fibre faces with the laminations arranged to give effectively orthotropic properties.

Type
Research Article
Information
Aeronautical Quarterly , Volume 23 , Issue 2 , May 1972 , pp. 148 - 160
Copyright
Copyright © Royal Aeronautical Society. 1972

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References

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