Identification of Mechanical Properties of Composite Plate Specimens using a Discrete Higher Order Displacement Model and Experimental Vibration Data

2009 ◽  
Author(s):  
A.L. Araujo ◽  
C.M. Mota Soares ◽  
M.J. Moreira de Freitas ◽  
P. Pedersen
Keyword(s):  
Mechanical Properties ◽  
Composite Plate ◽  
Higher Order ◽  
Vibration Data ◽  
Displacement Model

scholarly journals Instability Analysis of a Woven Fibre Composite Plate

2019 ◽  
Vol 8 (4) ◽  
pp. 2449-2454
Keyword(s):  
Mechanical Properties ◽  
Finite Element ◽  
Free Vibration ◽  
Epoxy Matrix ◽  
Composite Plate ◽  
Fibre Composite ◽  
Buckling Analysis ◽  
Instability Analysis ◽  
Critical Buckling Load ◽  
Modal Response

The instability behaviour of a woven fibre composite plate in respect of its free vibration and buckling analysis has been presented in this paper. The woven fibre composite plate has been prepared by hand layup with bidirectional woven glass fibres in epoxy matrix. The mechanical properties of the woven fibre composite plate have been characterised experimentally and a finite element investigation has been done for the instability analysis. Modal response of the plate and the critical buckling load leading to instability of the plate to varying parameters are studied and numerical results have been presented.

Modal Properties of Hybrid Carbon/Kevlar Composite Thin Plate and Hollow Wing Model

2013 ◽  
Vol 446-447 ◽  
pp. 597-601
Author(s):  
H. Haidzir ◽  
Dayang Laila Majid ◽  
A.S.M. Rafie ◽  
M.Y. Harmin
Keyword(s):  
Mechanical Properties ◽  
Thin Plate ◽  
Composite Plate ◽  
Natural Frequencies ◽  
Computational Procedure ◽  
Modal Testing ◽  
Wing Model ◽  
Natural Modes ◽  
Superior Mechanical Properties ◽  
Hybrid Carbon

In any flutter prediction analysis, modal testing is necessary because flutter, a resonant like vibration occurs at a flutter frequency and adopts a mode shape akin to its structural natural modes. Modal testing can be performed computationally with knowledge of the mechanical properties of the structure. In the present work, computational modal analysis is first performed on a cantilevered hybrid composite thin plate and validated experimentally. Then, the computational procedure is demonstrated on a composite hollow wing model of same material. The concept of hollow wing is explored due to the superior mechanical properties of carbon/kevlar composite plate. It is observed that the natural frequencies of the hollow wing model are higher than thin plate due to stiffer configuration. A breathing mode was also observed at mode 4 for the hollow wing.

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