Flutter of stiffened composite panels considering the stiffener's base as a structural element

Journal article (2016)

Authors

Thiago A.M. Guimarães Federal University of Uberlândia
Domingos A. Rade Division of Fundamental Science
Maurício V. Donadon ITA: Technological Institute of Aeronautics
Research Group
Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)
Composite Semi-analytical Flutter Stiffened plate Stiffened shell Stiffener's base
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Published Date

15-04-2016

Language

English

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

Abstract

Flutter in aeronautical panels is a type of self-excited oscillation which can occur during supersonic flights. At the flutter point the vibrations of the panel become unstable and increase significantly in time. This manuscript presents a semi-analytical model taking into account the stiffener's base effects, in order to predict the aeroelastic response of laminated composite stiffened panels under supersonic flow. Krumhaar's modified supersonic piston theory, which considers the radius effect, is adopted to model the aerodynamic loading. The proposed model has been validated against results available in the literature for various configurations. A parametric study considering different panels and stiffener configurations is also presented. The numerical results indicate that the stiffener base significantly affects the panel aeroelastic behavior. Preliminary studies also indicate that redistributing the laminate plies from the stiffener's flange to its base significantly increases the torsion stiffness of the panel locally, opening new design possibilities that may lead to higher critical flutter speeds and therefore to better designs. The results also indicate that designs with plies distributed on the base may lead to a better flutter performance when the airflow is transverse to the longitudinal stiffener direction.