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Research Papers

Static/Dynamic Edge Movability Effect on Non-Linear Aerothermoelastic Behavior of Geometrically Imperfect Curved Skin Panel: Flutter and Post-Flutter Analysis

[+] Author and Article Information
Laith K. Abbas1

 Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing, 210094, P. R. C.laithabbass@yahoo.com

Xiaoting Rui

 Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing, 210094, Chinaruixt@163.net

P. Marzocca

 Mechanical and Aeronautical Engineering Department, Clarkson University, Potsdam, NY, 13699pmarzocc@clarkson.edu

M. Abdalla

R. De Breuker

 Department of Aerospace Structures, Delft University of Technology, Kluyverweg 1, Delft, 2629HS, The NetherlandsR.deBreuker@tudelft.nl

1

Corresponding author.

J. Appl. Mech 79(4), 041004 (May 09, 2012) (13 pages) doi:10.1115/1.4005537 History: Received June 15, 2009; Revised August 27, 2011; Posted January 25, 2012; Published May 09, 2012; Online May 09, 2012

This paper addresses the problem of the aerothermoelastic modeling behavior and analyses of skin curved panels with static and dynamic edge movability effect in high supersonic flow. Flutter and post-flutter behavior will be analyzed toward determining under which conditions such panels will exhibit a benign instability, that is a stable limit cycle oscillation, or a catastrophic instability, that is an unstable LCO. The aerothermoelastic governing equations are developed from the geometrically non-linear theory of infinitely long two dimensional curved panels. Von Kármán non-linear strain-displacement relation in conjunction with the Kirchhoff plate-hypothesis is adopted. A geometrically imperfect curved panel forced by a supersonic/hypersonic unsteady flow is numerically investigated using Galerkin approach. These equations are based on the third-order piston theory aerodynamic for modeling the flow-induced forces. Furthermore, the effects of thermal degradation and Kelvin’s model of structural damping independent of time and temperature are also considered in this model. Computational analysis and discussion of the finding along with pertinent conclusions are presented.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Two-dimensional panel with initial curvature

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Figure 2

Comparison of flutter dynamic pressure versus the curvature ratio (Case #1)

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Figure 3

Effect of the imperfections on the flutter speed versus the curvature ratio (Case #1)

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Figure 4

Frequency coalescence for different values of δem

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Figure 5

Flutter speed versus δem

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Figure 6

Bifurcation diagram of the aero-thermo- elastic curved panel (Case #2) with respect to the variation of flight Mach number and static edge degree movability (without thermal degradation and damping)

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Figure 7

Bifurcation diagram of the aero-thermo- elastic curved panel (Case #2) with respect to the variation of flight Mach number and static edge degree movability (without thermal degradation and damping) under the effect of imperfections

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Figure 8

Time histories and phase portraits of the aero-thermo- elastic curved skin panel (Case #2) for different flight Mach number (gsb=gsm=0  ,  δem=1  ,  q1=0.005)

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Figure 9

Bifurcation diagram of the aero-thermo- elastic curved panel (Case #2) with respect to the variation of flight Mach number and static edge degree movability (with thermal degradation and no damping)

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Figure 10

Bifurcation diagram of the aero-thermo- elastic curved panel (Case #2) with respect to the variation of flight Mach number, degrees of movability, and its starting time

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