Conclusions
In this paper a theoretical approach to multilayered shell and plate analysis based on a kinematical model with six degrees of freedom is presented. The theory has been confirmed by some numerical examples. From these we draft the following conclusions:
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1.
The theory proposed for laminates can be used successfully also in the case of thin sandwich structures. It seems that the determination of stiffnesses is not so sensitive with regard to the ratios of the elastic moduli.
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2.
In the case of fibre reinforced laminates the results show a strong dependence not only on the fibre orientation angle, but also on the kind of lamination. These phenomena can be explained by the transformation rules of the local stiffness values. In many practical situations, simplified calculation formulae can be used for the local stiffness.
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3.
The results based on models with five or six degrees of freedom are very similar to standard situations with a simple geometry. In the cases of complicated geometries a model of six-degree-freedom provides a better agreement with results of there authors.
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4.
Further investigations should be continued on the effect of shear correction factors (see, e.g. [24]) and new classes of shell problems (stability, failure and inelastic material behavior).
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Published in Mekhanika Kompozitnykh Materialov, Vol. 29, No. 4, pp. 500–511, July–August, 1993.
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Altenbach, H., Altenbach, J. & Nast, E. Modelling and analysis of multilayered shells based on a timoshenko-type theory with six degrees of freedom. Mech Compos Mater 29, 374–384 (1994). https://doi.org/10.1007/BF00617163
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DOI: https://doi.org/10.1007/BF00617163