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Paper Information

Journal:   AEROSPACE MECHANICS JOURNAL   2010 , Volume 6 , Number 3 (21) (DYNAMICS, VIBRATIONS AND CONTROL); Page(s) 83 To 95.
 
Paper: 

FORCED VIBRATION OF A SANDWICH PANEL WITH COMPOSITE LAYERS AND A FGM CORE

 
 
Author(s):  KHEZRIAN R., JAFARE A.A., KHALILI S.M.R.
 
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Abstract: 
In this paper, forced vibration analysis of simply supported sandwich panel with composite layers and functionally graded material as core material is investigated using first shear deformation theory (FSDT) for face-sheet and three dimensional elasticity polynomials with unknown coefficients as Frostig method for its core. Hamilton's principle is applied to derive a set of fully coupled dynamic equations of motion. The core is assumed to have variable material properties only in the thickness direction. The forced vibration analysis has been performed using the New mark integration method for investigating the vibration characteristics and finding the response of rectangular panels under dynamic loads. The governing equations have been solved numerically using MATLAB software. Results have been verified with similar previous work. Finally, the central amplitude of sandwich panel on frequency parameter of excitation and the variation of the central deflection of sandwich panel as a function of time, subjected to different types of external force and the effects of geometry, material properties, number of layer, and different angle in composite layers are investigated. These numerical results have been then compared either with the available experimental ones or with some available theoretical results.
 
Keyword(s): FREE VIBRATION, FORCED VIBRATION, SANDWICH PANEL, FGM CORE, COMPOSITE LAYER
 
References: 
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