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<p>Aeronautical engineers are frequently faced with subsonic flutter phenomena. Thus, in the quest for safety requirements and to avoid catastrophes, it is important to evaluate efficient and low-cost aeroelastic control strategies for flutter suppression. Within this aim, constrained viscoelastic layers appear as an interesting alternative to be used in such situations. However, the modeling of aeroelastic systems with viscoelastic materials is still a challenge due to their inherent frequency- and temperature-dependent behavior and the need to thoroughly understand their mechanical interactions with the aeroelastic system under subsonic conditions. In most of the cases, it is due to their frequency- and temperature-dependent behavior. In this study, a modeling method of aeroviscoelastic systems under subsonic airflows to alleviate the flutter effects is proposed. The finite element model of a three-layer sandwich curved panel coupled with the unsteady aerodynamic loadings generated by the nonplanar doublet-lattice method is used, using an <i>in-house</i> code AEROSOLVER. To solve the complex eigenvalue problem, a modified version of the p-k method has been used to predict the subsonic flutter boundary and to verify the possibility of increasing the critical speeds of the aeroelastic system using viscoelastic materials. Additionally, the influence of the thickness of the layers and the operational temperature of the system on its stability were investigated here.</p>

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A modeling methodology of aeroelastic systems with constraining viscoelastic layers using the nonplanar doublet-lattice for subsonic flutter suppression

  • 期刊论文

  • 发表日期：

    2025年5月5日

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  • B. S. C. da Cunha,
  • A. M. G. de Lima,
  • D. M. Borges,
  • M. H. Belonsi

摘要

Aeronautical engineers are frequently faced with subsonic flutter phenomena. Thus, in the quest for safety requirements and to avoid catastrophes, it is important to evaluate efficient and low-cost aeroelastic control strategies for flutter suppression. Within this aim, constrained viscoelastic layers appear as an interesting alternative to be used in such situations. However, the modeling of aeroelastic systems with viscoelastic materials is still a challenge due to their inherent frequency- and temperature-dependent behavior and the need to thoroughly understand their mechanical interactions with the aeroelastic system under subsonic conditions. In most of the cases, it is due to their frequency- and temperature-dependent behavior. In this study, a modeling method of aeroviscoelastic systems under subsonic airflows to alleviate the flutter effects is proposed. The finite element model of a three-layer sandwich curved panel coupled with the unsteady aerodynamic loadings generated by the nonplanar doublet-lattice method is used, using an in-house code AEROSOLVER. To solve the complex eigenvalue problem, a modified version of the p-k method has been used to predict the subsonic flutter boundary and to verify the possibility of increasing the critical speeds of the aeroelastic system using viscoelastic materials. Additionally, the influence of the thickness of the layers and the operational temperature of the system on its stability were investigated here.