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<p>Full-span tests in transonic wind tunnels frequently experience unsteady flow, which induces vibrations in the model–balance–sting assembly. These vibrations compromise test accuracy, restrict the test envelope, and may lead to structure failure. This paper first measures and analyzes the vibration characteristics of typical transonic wind tunnel full-span tests with different methods. The correlation analysis indicates that the shift of the correlation between normal force and pitching moment is a precursor to the dangerous vibration. The vibration problem is then modeled as a double-section cantilever beam incorporating lumped mass and inertia. A finite element method utilizing a beam–brick mixed element is proposed. The method evaluates changes in the frequency and mode shape of the model–balance–sting assembly resulting from variations in the lumped mass and inertia of the scaled aircraft model. Experimental validation confirms the method's effectiveness and accuracy. The proposed approach enables rapid and precise assessment of the scaled aircraft model's impact on overall dynamic characteristics and provides practical guidance for optimal vibration sensor placement.</p>

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Dynamic Response and Rapid Analysis of the Aircraft Model Vibration in Transonic Wind Tunnels

  • 期刊论文

  • 发表日期：

    2026年3月12日

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  • Lei Zhang,
  • Lulu Chang,
  • Jijun Liu,
  • Tao Liu,
  • Xing Shen

摘要

Full-span tests in transonic wind tunnels frequently experience unsteady flow, which induces vibrations in the model–balance–sting assembly. These vibrations compromise test accuracy, restrict the test envelope, and may lead to structure failure. This paper first measures and analyzes the vibration characteristics of typical transonic wind tunnel full-span tests with different methods. The correlation analysis indicates that the shift of the correlation between normal force and pitching moment is a precursor to the dangerous vibration. The vibration problem is then modeled as a double-section cantilever beam incorporating lumped mass and inertia. A finite element method utilizing a beam–brick mixed element is proposed. The method evaluates changes in the frequency and mode shape of the model–balance–sting assembly resulting from variations in the lumped mass and inertia of the scaled aircraft model. Experimental validation confirms the method's effectiveness and accuracy. The proposed approach enables rapid and precise assessment of the scaled aircraft model's impact on overall dynamic characteristics and provides practical guidance for optimal vibration sensor placement.