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The Initial Buckling of Slightly Curved Panels Under Combined Longitudinal and Circumferential Direct Stresses

Published online by Cambridge University Press:  04 July 2016

K. H. Sayers
K. H. Sayers*
Affiliation:
Bureau de Calcul, Sud Aviation, Toulouse
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Summary

The initial buckling stresses of rectangular panels under applied axial loads are in general increased both by circumferential tensile stresses and by the curvature of the panel. The present Note gives theory to estimate these stresses for panels forming part of an unstiffened cylindrical shell. All edges are free to rotate. This condition is often closer to the actual rotational edge restraint of curved panels in conventional stressed-skin construction than the clamped condition, especially in the case of lightly-reinforced shells. The axial generators in the mid-plane of the panels are held straight at the longitudinal edges. All other axial generators are also assumed to remain straight before buckling (no “mattress effect”). The middle surface is restrained at the curved edges of the panel against radial deformation during and after buckling.

Design curves are presented for several values of the parameter (ab/Rt), followed by a typical example.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 68 , Issue 640 , April 1964 , pp. 271 - 274
Copyright
Copyright © Royal Aeronautical Society 1964

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References

1. Royal Aeronautical Society. Data Sheets for Stressed-Skin Structures, Vol. II, No. 02.01.38, September 1955.Google Scholar
2.Timoshenko, S.Theory of Elastic Stability. McGraw-Hill Book Co., Inc., 1936.Google Scholar
3.Houghton, D. S. and Iohns, D. I. Linear Buckling of an Axially Reinforced Pressurized Cylinder. College of Aeronautics Note No. 110, October 1960.Google Scholar
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