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Buckling of laminated composite plates and shell panels with some free edges under compression and shear

Published online by Cambridge University Press:  04 July 2016

M. K. Prabhakara
M. K. Prabhakara*
Affiliation:
Mechanics of Materials BranchNaval Research Laboratory, Washington, DC, USA
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Summary

A general analytical solution for the buckling of laminated composite plates and shell panels for all combinations of free, simply supported and clamped edge conditions is presented. The solution is formulated in terms of stress function and transverse deflection. All the boundary conditions for the stress function are exactly satisfied. For the transverse deflection the prescribed boundary conditions are satisfied by including them in the expression for the energy integral. Several types of boundary conditions in which at least a pair of opposite edges of the panel are free and subjected to axial compression are considered. The Galerkin method, with beam vibration functions used as shape functions, is utilised to determine the buckling loads. The results obtained are used to examine the effect of bending-extensional coupling, aspect ratio and the curvature parameter on the buckling load.

Type
Research Article
Information
The Aeronautical Journal , Volume 96 , Issue 951 , January 1992 , pp. 20 - 26
Copyright
Copyright © Royal Aeronautical Society 1992 

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References

1. Leissa, A. W. Buckling of Laminated Composite Plates and Shell Panels, Flight Dynamics Laboratory, Wright Patterson Air Force Base, Dayton, Ohio, Report AFWAL-TR-85-3069, 1985.Google Scholar
2. Ashton, J. E. and Whitney, J. M. Theory of Laminated Plates, Technomic Publishing, Stanford, Connecticut, 1970.Google Scholar
3. Jones, R. M. Buckling and vibration of unsymmetrically laminated cross-ply rectangular plates, AlAA J, 1973, 11, p 1626.Google Scholar
4. Chamis, C. C. Buckling of anisotropic composite plates, Journal of the Engineering Mechanics Division, Proceedings of the American Society of Civil Engineers, 1969, 95, p 2119.Google Scholar
5. Viswanathan, A. V., Tamekuni, M. and Baker, L. L. Elastic Stability of Laminated Flat and Curved Long Rectangular Plates Subjected to Combined and Plane Loads, NASA CR-2330, June 1974.Google Scholar
6. Zhang, Y. and Mathews, F. L. Initial buckling of curved panels of generally layered composite materials, Compos Struct, 1983, 1 p 3.Google Scholar
7. Whitney, J. M. Buckling of anisotropic laminated cylindrical plates, AlAA J, 1984, 22, p 1641.Google Scholar
8. Wang, J. T., Biggers, S. B. and Dickson, J. N. Buckling of composite plates with a free edge in edgewise bending and compression, AlAA J, 1984, 22, p 394.Google Scholar
9. Young, D.and Flegar, R. P. Tables of Characteristic Functions Representing Normal Modes of Vibration of Beam, Publication No. 4913, University of Texas, Austin, Texas, July 1949.Google Scholar
10. Timoshenko, S. P. and Gere, J. M. Theory of Elastic Stability, Second Edition, McGraw-Hill, New York, 1961.Google Scholar