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An exact dynamic stiffness element using a higher order shear deformation theory for free vibration analysis of composite plate assemblies

Earlier dynamic theories for composite plates are generally less accurate and not suitable for thick structures because they do not include the effects of shear deformation and rotatory inertia properly. This paper eliminates deficiencies of earlier theories and gives an accurate and computationally efficient approach for vibration analysis of practical composite structures such as aircraft wings which are modelled by plate assemblies. Dynamic stiffness properties are developed by implementing higher order shear deformation theory and applying symbolic algebra for the first time to carry out modal analysis. This will have considerable impact in aircraft industry.