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Approximations in Complicated Critical Buckling and Free Vibration Analyses of Prismatic Plate Structures

Published online by Cambridge University Press:  07 June 2016

F W Williams
F W Williams*
Affiliation:
Department of Civil Engineering, University of Birmingham
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Summary

An exact method has recently been presented for computing the critical buckling loads, or the natural frequencies of vibration, of prismatic assemblies of rigidly inter-connected, thin, flat, rectangular plates. The plates can carry uniform in-plane longitudinal, transverse and shear stresses and may be isotropic or anisotropic, with the elastic coupling stiffness matrix B = 0. This method can be used even if some of the plates have curved cross sections, are non-uniformly longitudinally compressed or, in certain circumstances, have B ≠ 0. However, approximations are then involved when representing the plates. Results presented herein indicate that good answers can be obtained despite these approximations.

Type
Research Article
Information
Aeronautical Quarterly , Volume 25 , Issue 3 , August 1974 , pp. 180 - 185
Copyright
Copyright © Royal Aeronautical Society. 1974

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References

1 Wittrick, W H, Williams, F W, Buckling and vibration of anisotropic or isotropic plate assemblies under combined loadings. International Journal of Mechanical Sciences, Vol 16, pp 209–239, 1974.CrossRefGoogle Scholar
2 Viswanathan, A V, Tamekuni, M, Tripp, L L, Elastic stability of biaxially loaded longitudinally stiffened composite structures. AlAA Journal, Vol 11, pp 1553–1559, 1973.Google Scholar
3 Viswanathan, A V, Tamekuni, M, Baker, L L, Elastic stability of laminated, flat and curved, long rectangular plates subjected to combined inplane loads. NASA-CR-2330, 1973.Google Scholar
4 Williams, F W, Computation of natural frequencies and initial buckling stresses of prismatic plate assemblies. Journal of Sound and Vibration, Vol 21, pp 87–106, 1972.CrossRefGoogle Scholar
5 Plank, R J, Williams, F W, Critical buckling of some stiffened panels in compression, shear and bending. Aeronautical Quarterly, Vol XXV, pp 165–179, August 1974. (Precedes this paper).CrossRefGoogle Scholar
6 Flügge, W, Stresses in Shells. Springer-Verlag, Berlin, 1960.Google Scholar
7 Jones, R M, Buckling and vibration of unsymmetrically laminated cross-ply rectangular plates. AlAA Journal, Vol 11, pp 1626–1632, 1973.Google Scholar
8 Viswanathan, A V, Tamekuni, M, Elastic buckling analysis for composite stiffened panels and other structures subjected to biaxial in-plane loads. NASA-CR-2216, 1973.Google Scholar