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Volume 49 Issue 9
Oct.  2023
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Journal of Beijing University of Aeronautics and Astronautics  > 2023  >  49(9): 2361-2373.
BAI L Y，WU Z G，YANG C. Nonlinear flutter modes and flutter suppression of an all-movable fin with freeplay[J]. Journal of Beijing University of Aeronautics and Astronautics，2023，49（9）：2361-2373 （in Chinese） doi: 10.13700/j.bh.1001-5965.2022.0162
Citation: BAI L Y，WU Z G，YANG C. Nonlinear flutter modes and flutter suppression of an all-movable fin with freeplay[J]. Journal of Beijing University of Aeronautics and Astronautics，2023，49（9）：2361-2373 （in Chinese） doi: 10.13700/j.bh.1001-5965.2022.0162
shu

Nonlinear flutter modes and flutter suppression of an all-movable fin with freeplay

doi: 10.13700/j.bh.1001-5965.2022.0162

  • School of Aeronautic Science and Engineering，Beihang University，Beijing 100191，China

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  • Corresponding author: E-mail：wuzhigang@buaa.edu.cn
  • Received Date: 18 Mar 2022
  • Accepted Date: 20 May 2022
  • Publish Date: 31 May 2022
    Abstract

  • Freeplay nonlinearity widely exists in the structure of aircraft, which can bring limit cycle oscillations (LCO), leading to the fatigue failure of the structure. There is relatively little research on the mechanism and passive suppression of the nonlinear flutter for all-movable fins. Therefore, this paper proposes two different nonlinear flutter modes and provides passive suppression methods. The dynamic model is developed using the describing function method and piston theory. Considering that the torsional stiffness is reduced due to the existence of the freeplay, nonlinear flutter characteristics under different torsional stiffnesses are compared and two different nonlinear flutter modes are defined, in which mode Ⅱ doesn’t contain stable LCO, effectively suppressing the LCO below the linear flutter boundary. Then the influence of bending and torsional stiffnesses and mass moments of inertia on nonlinear flutter modes and the dynamic pressure of LCO appearance is studied, and some nonlinear flutter passive suppression methods are proposed. The findings indicate that reasonable adjustment of the bending and torsional stiffnesses or mass moments of inertia can raise the dynamic pressure of LCO appearance and even change the nonlinear flutter mode, so as to suppress the nonlinear flutter.

     

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