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Research Papers

Dynamic Stability Analysis of Stiffened Shell Panels With Cutouts

[+] Author and Article Information
S. N. Patel1

Department of Aerospace Engineering, Indian Institute of Technology Kharagpur, Kharagpur, 721 302 West Bengal, Indiashuvendu_patel@yahoo.co.in

P. K. Datta

Department of Aerospace Engineering, Indian Institute of Technology Kharagpur, Kharagpur, 721 302 West Bengal, Indiapkdatta@aero.iitkgp.ernet.in

A. H. Sheikh

School of Civil, Environmental and Mining Engineering, University of Adelaide, Adelaide, South Australia 5005, Australiaahsheikh@civeng.adelaide.edu.au

1

Corresponding author.

J. Appl. Mech 76(4), 041004 (Apr 22, 2009) (13 pages) doi:10.1115/1.3086595 History: Received April 17, 2007; Revised January 02, 2009; Published April 22, 2009

A finite element dynamic instability analysis of stiffened shell panels with cutout subjected to uniform in-plane harmonic edge loading along the two opposite edges is presented in this paper. The eight-noded isoparametric degenerated shell element and a compatible three-noded curved beam element are used to model the shell panels and the stiffeners, respectively. As the usual formulation of degenerated beam element is found to overestimate the torsional rigidity, an attempt has been made to reformulate it in an efficient manner. Moreover the new formulation for the beam element requires five degrees of freedom per node as that of shell element. Bolotin method is applied to analyze the dynamic instability regions. Numerical results of convergence studies are presented and comparison is made with the published results from literature. The effects of various parameters such as shell geometry, radius of curvature, cutout size, stiffening scheme, and dynamic load factors are considered in dynamic instability analysis of stiffened shell panels with cutout. The free vibration and static stability (buckling) results are also presented. With the consideration of radius of curvatures the panels reduce from deep shell case to shallow shell case and finally become flat plate.

Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 1

Eight-noded quadrilateral degenerated shell element

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Figure 2

Stiffener attached to the panel surface

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Figure 3

Rectangular stiffened plate

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Figure 4

Stiffened spherical shell panel having a square base

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Figure 5

Simply supported stiffened rectangular plate under uniaxial compression

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Figure 6

Perforated plate under uniaxial compression

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Figure 7

Dynamic instability regions of plate with square cutout under uniaxial compression

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Figure 8

Perforated stiffened doubly curved panel with stiffened central opening under uniaxial compression

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Figure 9

Geometry of different shell panels

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Figure 10

Dynamic instability regions of stiffened cylindrical shell panel without cutout for various radii of curvature to span ratio

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Figure 11

Same as Fig. 1 but for stiffened parabolic hyperboloid panel

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Figure 12

Same as Fig. 1 but for stiffened spherical shell panel

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Figure 13

Dynamic instability regions of stiffened cylindrical shell panel for various cutout ratios

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Figure 14

Same as Fig. 1 but for stiffened spherical shell panel

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Figure 15

Same as Fig. 1 but for stiffened parabolic hyperboloid panel

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Figure 16

Same as Fig. 1 but for stiffened plate

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