Behaviour of laminated composite twisted plates subjected to in-plane loading

Kachhap, Vikas (2013) Behaviour of laminated composite twisted plates subjected to in-plane loading. MTech thesis.



The twisted panel has various applications in turbine blades, compressor blades, fan blades and particularly in gas turbines. Many of these plates are subjected to in-plane load due to fluid or aerodynamic pressures.Hence it is necessary to study their behaviour under differnt types of loads. In these days,composite materials are increasingly used as load bearing structural components in aerospace and naval structures, automobiles, pressure vessels, turbine blades and many other engineering applications because of their high specific strength and stiffness. The analysis is carried out using ANSYS software. An eight-node isoparametric quadratic element is considered in the present analysis with five degrees of freedom per node.In ANSYS, the shell 281 element with five degrees of freedom per node is used. An eight by eight mesh is found to give good accuracy.Thevibration and stability behaviour of composite laminated twisted plate under various types of non-uniform in-plane loading is studied. The effect of number of layers, changing angle of twist, width to thickness ratio, aspect ratio, etc on the vibration and buckling loads are presented. It is observed that for increasing angles of twist of laminated composite plate with different in-plane load conditions, the vibration and buckling both decreases. Also as the number of layersincreases, the vibration and buckling parameters of the laminated twisted plate are both observed to increase.

Item Type:Thesis (MTech)
Uncontrolled Keywords:specific strength, stiffness,isoparametric,vibration, buckling
Subjects:Engineering and Technology > Civil Engineering > Structural Engineering
Divisions: Engineering and Technology > Department of Civil Engineering
ID Code:4717
Deposited By:Hemanta Biswal
Deposited On:29 Oct 2013 15:13
Last Modified:20 Dec 2013 15:11
Supervisor(s):Asha, A V

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