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Research Papers

Stochastic Nonlinear Free Vibration Analysis of Piezolaminated Composite Conical Shell Panel Subjected to Thermoelectromechanical Loading With Random Material Properties

[+] Author and Article Information
Achchhe Lal1

Paras Choski

Department of Mechanical Engineering Sardar Vallabhbhai National Institute of Technology, Surat-395007, Indiachoski_paras@yahoo.com

B. N. Singh

Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur-721302, Indiabnsingh@aero.iitkgp.ernet.in

1

Corresponding author.

J. Appl. Mech 79(6), 061008 (Oct 18, 2012) (17 pages) doi:10.1115/1.4006765 History: Revised April 19, 2011; Received June 17, 2011; Accepted May 03, 2012; Published October 18, 2012

This paper presents the effect of randomness in material properties on piezolaminated composite geometrically nonlinear conical shell panel subjected to thermoelectromechanical loading acting simultaneously or individually. Material properties such as modulus ratio, Poisson’s ratio, and thermal expansion coefficients are modeled as independent random variables. The temperature field considered is assumed to be a uniform distribution over the shell panel surface and through the shell thickness and the electric field is assumed to be the transverse component Ez only. It is assumed that the mechanical properties do not depend on temperature and electric fields. The basic formulation is based on higher order shear deformation theory (HSDT) with von-Karman nonlinearity. A C0 nonlinear finite element model based on direct iterative approach in conjunction with mean centered first order perturbation technique (FOPT) used by the present author for plate is now extended for conical shell panel to solve a random nonlinear generalized eigenvalue problem. Parametric studies are carried out to examine the effect of amplitude ratios, stacking sequences, cone angles, circumferential length to thickness ratios, piezoelectric layers, applied voltages, change in temperature, types of thermoelectromechanical loadings, and support boundary conditions on the dimensionless mean and coefficient of variance (COV) of laminated conical shell panels. The present outlined approach has been validated with those available results in literature and independent Monte Carlo simulation (MCS).

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Geometry of laminated composite cone lamina with geometrical coordinates

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Figure 2

(a) Flow chart for overview of present analysis; (b) convergence study for mean fundamental frequency of composite angle-ply square simply supported cylindrical shell panel having R/h = 50 and LC/h = 10 with mesh size

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Figure 3

Validation of present DISFEM approach with the available literature of Tripathi [24] for fundamental frequency of angle ply [-45 deg/45 deg]s simply supported conical panel, with R/h = 50 and LC/h = 40 and random material properties

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Figure 4

Validation of present DISFEM results with independent MCS results of nonlinear natural frequency of piezolaminated cross-ply simply supported conical shell panel subjected to thermoelectromechanical loading having random change in only one material property, E1 , keeping others as deterministic to mean value for LC/h = 70, ΔT = 100 °C, ΔV = 100 V for mode 1 and mode 2

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