Eventos Anais de eventos
DINAME 2017
XVII International Symposium on Dynamic Problems of Mechanics
A MODEL REDUCTION METHOD FOR AEROVISCOELASTIC SYSTEMS
Submission Author:
Antonio Marcos de Lima , MG
Co-Authors:
André Cunha Filho, Yvon Briend, Antonio Marcos de Lima, Mauricio Donadon
Presenter: André Cunha Filho
doi://10.26678/ABCM.DINAME2017.DIN17-0023
Abstract
It is well-known that the flutter boundary prediction for complex aeroelastic panels of industrial interest is not easy. It is due to the complexity of the resulting aeroelastic models normally composed by a large number of degrees of freedom. Moreover, if the aeroelastic system incorporates a control strategy with the aim of reducing the flutter phenomenon, such as the use of viscoelastic materials, the computational cost required to predict the flutter speed of the aeroviscoelastic system is very high, sometimes unfeasible. For this situation in which the flutter boundary must be determined based on the resolution of the complex eigenvalue problem, the use of a model reduction technique is required. However, in the quest for model reduction techniques based on modal projection for aeroelastic systems incorporating viscoelastic materials with frequency- and temperature-dependent damping, the construction of the reduction basis is an issue. Since, the reduction basis must be considered the frequency- and temperature-dependency of the viscoelastic properties and the dynamic behavior of the system as a function of dynamic pressure. In the quest for reduction of aeroviscoelastic systems, few works have been proposed in the open literature, which motivates the study reported herein. Shin et al. [1] studied the aeroelastic characteristics of a cylindrical hybrid composite panel with viscoelastic materials based on the use of a modal approach. However, they do not compare the results obtained by the reduced model with the corresponding obtained for the exact solutions. Moreover, as shown in Fig. 1, the authors have proved that the strategy suggested by Shih et al. [1] is not completely adequate to predict the flutter speed of aeroviscoelastic systems. Hence, the main interest of this paper is to propose a new reduction method for aeroelastic systems incorporating viscoelastic materials based on modal projection. The main idea is to construct an iterative Ritz-method with aerodynamic residues iterations. This approach is inspired on the technique proposed by Bobillot and Balmès [2] used to reduce finite element models involving damped structures coupled with compressible fluids. The numerical results for a thin rectangular three-layer sandwich plate under supersonic flow, in which the amplitudes of the FRFs, the flutter boundary and the computational efficiency for the proposed new reduction method and compared with the corresponding obtained by applying the most used methods suggested in the open literature are presented.
Keywords
aeroelastic systems, viscoelastic materials, model reduction, finite element
