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Experimental Buckling Loads of Sandwich Panels with Carbon Fibre Faceplates

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

Experiments to determine the overall buckling and faceplate wrinkling loads of sandwich panels with carbon fibre reinforced plastic faces and honeycomb cores when loaded under uniaxial compression are described. The results are compared with theoretical predictions which assume that the faceplates are orthotropic. The effect on the experimental loads of certain coupling terms, which occur in the constitutive equations of those faceplates which are not orthotropic, is then considered.

Type
Research Article
Information
Aeronautical Quarterly , Volume 24 , Issue 4 , November 1973 , pp. 295 - 312
Copyright
Copyright © Royal Aeronautical Society. 1973

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References

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