International Journal of Aerospace System Engineering

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Dynamic Analysis of Laminated Composite and Sandwich Plates Using Trigonometric Layer-wise Higher Order Shear Deformation Theory

  • Suganyadevi, S (Department of Aerospace Engineering, Indian Institute of Technology Kharagpur) ;
  • Singh, B.N. (Department of Aerospace Engineering, Indian Institute of Technology Kharagpur)
  • Received : 2016.03.23
  • Accepted : 2016.05.29
  • Published : 2016.06.30
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Abstract

A trigonometric Layerwise higher order shear deformation theory (TLHSDT) is developed and implemented for free vibration and buckling analysis of laminated composite and sandwich plates by analytical and finite element formulation. The present model assumes parabolic variation of out-plane stresses through the depth of the plate and also accomplish the zero transverse shear stresses over the surface of the plate. Thus a need of shear correction factor is obviated. The present zigzag model able to meet the transverse shear stress continuity and zigzag form of in-plane displacement continuity at the plate interfaces. Hence, botheration of shear correction coefficient is neglected. In the case of analytical method, the governing differential equation and boundary conditions are obtained from the principle of virtual work. For the finite element formulation, an efficient eight noded $C^0$ continuous isoparametric serendipity element is established and employed to examine the dynamic analysis. Like FSDT, the considered mathematical model possesses similar number of variables and which decides the present models computationally more effective. Several numerical predictions are carried out and results are compared with those of other existing numerical approaches.

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References

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