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An Experimental and Theoretical Investigation of Simply-Supported Thin Plates Subjected to Lateral Load and Uniaxial Compression

Published online by Cambridge University Press:  24 August 2017

P. W. Sharman  and
J. Humpherson
P. W. Sharman
Affiliation:
University of Technology, Loughborough
J. Humpherson
Affiliation:
English Electric Co, Whetstone
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Extract

In the design of compression structures, the effect of lateral loading is usually ignored. This assumption has been justified where the structure has represented the wing skin of a conventional aircraft, in which the compressive end load due to bending is high, but the lateral load due to aerodynamic pressure is comparatively low.

However, in some cases the approximation is too crude, such as where the effect of the aerodynamic pressure is added to by pressurised fuel tanks together with the possibility of the accelerated weight of fuel. Such situations arise in supersonic transport aircraft where a considerable weight of fuel is carried in the wing and aerodynamic heating causes high compressive stresses in the skin.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 72 , Issue 689 , May 1968 , pp. 431 - 436
Copyright
Copyright © Royal Aeronautical Society 1968 

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References

1. Levy, S., Goldenberg, D. and Zibritosky, G. Simply Supported Long Rectangular Plate under Combined Axial Load and Normal Pressure. NACA TN 949, 1944.Google Scholar
2. Ligtenberg, F. K. The Moiré Method. Proc. SESA XII (2), 83–98, 1955.Google Scholar
3. Fralich, R. W. Postbuckling Effects on the Flutter of Simply Supported Rectangular Panels at Supersonic Speeds. NASA TN D-1615, 1962.Google Scholar
4. Woollet, R. M., Corrick, J. N. and Levy, S. Clamped Long Rectangular Plate under Combined Axial Load and Normal Pressure. NACA TN 1047, 1946.Google Scholar
5. Timoshenko, S. Theory of Plates and Shells. McGraw Hill, 1940.Google Scholar