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The compressive buckling performance of anti-symmetric composite laminates and the effect on behaviour of membrane-flexural coupling

Published online by Cambridge University Press:  04 July 2016

J. Loughlan
J. Loughlan*
Affiliation:
Department of Aeronautical and Automotive Engineering, Loughborough University, UK
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Abstract

The compressive stability of anti-symmetric angle-ply laminated plates with particular reference to the degrading influence of membrane-flexural coupling is reported in this paper. A specific configuration of anti-symmetric laminate is dealt with in the paper and this takes the form [θ/-θ]n whereby 2n is the total number of plies in the laminated stack. With regard to compressive buckling the paper gives an indication that anti-symmetric laminates with 8 plies or more will yield performance levels which are almost identical to their symmetric counterparts. The degree of membrane-flexural coupling in the laminated composite plates is varied, essentially, by changing the ply angle and also by altering the number of plies in the laminated stack, for a given composite material system. The coupled compressive buckling solutions are determined using the finite strip method of analysis. In order to provide an adequate level of flexibility in the analysis procedure and to ensure a high level of accuracy of solution, the buckling displacement fields of the strip formulation are those which are described in a multi-term form.

Results are given for anti-symmetric angle-ply laminated plates subjected to uniaxial and biaxial compression and these have been obtained from fully converged finite strip structural models. Validation of the finite strip formulation is indicated in the paper through comparisons with exact solutions where appropriate. The natural half-wavelength of the compressive buckling mode of the composite plates is shown to be significantly influenced by variation in the ply angle. Increasing the number of plies in the laminated system is seen to reduce the degree of coupling and the critical stress levels are noted to tend towards the plate orthotropic solutions. The ply angle corresponding to the optimised, compressive buckling stress for any particular laminate is noted in the paper to be influenced by the support boundary conditions at the plates unloaded edges.

Type
Research Article
Information
The Aeronautical Journal , Volume 106 , Issue 1065 , November 2002 , pp. 595 - 606
Copyright
Copyright © Royal Aeronautical Society 2002 

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References

1. Prabhakara, M.K. Post-buckling behaviour of simply-supported cross-ply rectangular plates, Aeronaut Q, 1976, 27, pp 309–316.Google Scholar
2. Sharma, S., Iyengar, N.G.R. and Murthy, P.N. Buckling of antisymmetric cross- and angle-ply laminated Plates, Int J Mech Sci, 1980, 22, pp 607–620.Google Scholar
3. Hui, D. Shear buckling of anti-symmetric cross-ply rectangular plates, Fibre Sci and Tech, 1984, 21, pp 327–340.Google Scholar
4. Leissa, A.W. Conditions for laminated plates to remain flat under inplane loading, Composite Structures, 1986, 6, pp 261–270.Google Scholar
5. Ewing, M.S., Hinger, R.J. and Leissa, A.W. On the validity of the reduced bending stiffness method for laminated composite plate analysis, Composite Structures, 1988, 9, pp 301–317.Google Scholar
6. Jensen, D.W. and Lagace, P.A. Influence of mechanical couplings on the buckling and postbuckling of anisotropic plates, AIAA J, 1988, 26, (10).Google Scholar
7. Thangaratnam, K.R., Palaninathan, and Ramachandran, J. Thermal buckling of composite laminated plates, Computers & Structures, 1989, 32, (5), pp 1117–1124.Google Scholar
8. Adali, S. and Duffy, K.J. Design of anti-symmetric hybrid laminates for maximum buckling load: I. Optimal fibre orientation, Composite Structures, 1990, 14, pp 49–60.Google Scholar
9. Duffy, K.J. and Adali, S. Design of anti-symmetric hybrid laminates for maximum buckling load: II. Optimal layer thickness, Composite Structures, 1990, 14, pp 113–124.Google Scholar
10. Chow, S.T., Liew, K.M. and Lam, K.Y. Transverse vibration of symmetrically laminated rectangular composite plates, Composite Structures, 1992, 20, pp 213–226.Google Scholar
11. Chai, G.B. Free vibration of generally laminated composite plates with various edge support conditions, Composite Structures, 1994, 29, pp 249–258.Google Scholar
12. Chai, G.B. Buckling of generally laminated composite plates with various edge support conditions, Composite Structures, 1994, 29, pp 299–310.Google Scholar
13. Lam, K.Y. and Chun, L. Analysis of clamped laminated plates subjected to conventional blast, Composite Structures, 1994, 29, pp 311–321.Google Scholar
14. Nemeth, M.P. Buckling of symmetrically laminated plates with compression, shear and in-plane bending, AIAA J, 1992, 30, (12), pp 2959–2965.Google Scholar
15. Nemeth, M.P. Buckling behaviour of long anisotropic plates subjected to combined loads, NASA Technical Paper 3568, November 1995.Google Scholar
16. Nemeth, M.P. Buckling behaviour of long symmetrically laminated plates subjected to shear and linearly varying axial edge loads, NASA Technical Paper 3659, July 1997.Google Scholar
17. Nemeth, M.P. Nondimensional parameters and equations for buckling of anisotropic shallow shells, ASME, J App Mech, 1994, 61, pp 664–669.Google Scholar
18. Dawe, D.J. and Wang, S. Postbuckling analysis of thin rectangular laminated plates by spline FSM, Thin-Walled Structures, 30, 1998, pp 159–179.Google Scholar
19. Wang, S. and Dawe, D.J. Spline FSM postbuckling analysis of shear-deformable rectangular laminates, Thin-Walled Structures, 1999, 34, pp 163–178.Google Scholar
20. Loughlan, J. The influence of bend-twist coupling on the shear buckling response of thin laminated composite plates, Thin-Walled Structures, 1999, 34, pp 97–114.Google Scholar
21. Loughlan, J. The shear buckling behaviour of thin composite plates with particular reference to the effects of bend-twist coupling, Int J Mech Sci, 2001, 43, pp 771–792.Google Scholar
22. Jones, R.M. Mechanics of Composite Materials, McGraw-Hill Kogakusha, 1975.Google Scholar