Dynamic Behavior Analysis of Moderately Thick Composite Laminated Plates Containing Square Delamination Using Spline-Finite Strip Method

Document Type : Research Article

Author

Aerospace Research Institute, Tehran, Iran

Abstract

ABSTRACT: The dynamic behavior of laminated composite panels subjected to in-plane endloads is investigated using finite strip method. The panel is assumed to contain square delamination. Friction and contact conditions at delaminated interfaces are not considered. It is also assumed that the delamination exists before loading and delamination growth is not considered. A general loading consisted of time varying as well as constant component is assumed and the static buckling, natural frequencies and also parametric instability of the panel have been investigated. The loading assumed to be uniformly distributed throughout the panel area. The dynamic behavior of the delaminated panel has been extracted by using an enhanced B-spline finite strip formulation on the basis of the principle of virtual work. A third order Reddy type shear deformation theory is utilized in order to bring the effects
of moderately thick laminate into account. The effects of loading as well as boundary conditions on the dynamic behavior of the structure are studied. The dynamic instability regions are extracted using the Bolotin’s first order approximation. In order to demonstrate the capabilities of the developed method in predicting the structural dynamic behavior, some representing results are obtained and compared with those available in the literature.

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References

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Amirkabir Journal of Mechanical Engineering
Volume 50, Issue 1
May and June 2018
Pages 63-72

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