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Nonlinear metamaterial enabled aeroelastic vibration reduction of a supersonic cantilever wing plate

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  • Published: 30 September 2024
  • Volume 45, pages 1749–1772, (2024)
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Applied Mathematics and Mechanics Aims and scope Submit manuscript
Nonlinear metamaterial enabled aeroelastic vibration reduction of a supersonic cantilever wing plate
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  • Peng Sheng1,
  • Xin Fang1,
  • Dianlong Yu1 &
  • …
  • Jihong Wen1 

  • 706 Accesses

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Abstract

The violent vibration of supersonic wings threatens aircraft safety. This paper proposes the strongly nonlinear acoustic metamaterial (NAM) method to mitigate aeroelastic vibration in supersonic wing plates. We employ the cantilever plate to simulate the practical behavior of a wing. An aeroelastic vibration model of the NAM cantilever plate is established based on the mode superposition method and a modified third-order piston theory. The aerodynamic properties are systematically studied using both the timedomain integration and frequency-domain harmonic balance methods. While presenting the flutter and post-flutter behaviors of the NAM wing, we emphasize more on the pre-flutter broadband vibration that is prevalent in aircraft. The results show that the NAM method can reduce the low-frequency and broadband pre-flutter steady vibration by 50%–90%, while the post-flutter vibration is reduced by over 95%, and the critical flutter velocity is also slightly delayed. As clarified, the significant reduction arises from the bandgap, chaotic band, and nonlinear resonances of the NAM plate. The reduction effect is robust across a broad range of parameters, with optimal performance achieved with only 10% attached mass. This work offers a novel approach for reducing aeroelastic vibration in aircraft, and it expands the study of nonlinear acoustic/elastic metamaterials.

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Authors and Affiliations

  1. Laboratory of Science and Technology on Integrated Logistics Support, College of Intelligence Science and Technology, National University of Defense Technology, Changsha, 410073, China

    Peng Sheng, Xin Fang, Dianlong Yu & Jihong Wen

Authors
  1. Peng Sheng
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  2. Xin Fang
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  3. Dianlong Yu
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  4. Jihong Wen
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Correspondence to Xin Fang.

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Conflict of interest The authors declare no conflict of interest.

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Project supported by the National Natural Science Foundation of China (Nos. 52241103, 52322505, and 11991032) and the Natural Science Foundation of Hunan Province of China (No. 2023JJ10055)

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Sheng, P., Fang, X., Yu, D. et al. Nonlinear metamaterial enabled aeroelastic vibration reduction of a supersonic cantilever wing plate. Appl. Math. Mech.-Engl. Ed. 45, 1749–1772 (2024). https://doi.org/10.1007/s10483-024-3165-7

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  • Received: 13 April 2024

  • Revised: 03 July 2024

  • Published: 30 September 2024

  • Issue Date: October 2024

  • DOI: https://doi.org/10.1007/s10483-024-3165-7

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Key words

  • nonlinear acoustic metamaterial (NAM)
  • hypersonic aeroelastic vibration
  • vibration reduction
  • fluid-structure interaction

Chinese Library Classification

  • O328

2010 Mathematics Subject Classification

  • 74H45
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