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<p>The stochastic vibration of the aircraft with tail support degrades the sensor’s data accuracy seriously in wind tunnel test, a magnetic-controlled magnetorheological damper (MRD) based tail support (MRTS) can suppress the vibration adaptively. Nevertheless, system distributed features and the nonlinearity of MRTS pose challenges for controller design. This paper proposes an indirect measurement approach for characterization of MRD on distributed structure, and bases on this, deduces maximum hysteresis loop criterion based fuzzy controller (MHL-FC) for vibration control. Initially, the dynamic response of MRD, was obtained by subtracting the real-time force–displacement response of the original support from that of the MRTS. Subsequently, aiming at increase the area (energy dissipation) of the MRD’s force–displacement hysteresis loop, MHL-FC with strategy describes by ‘apply current when velocity and displacement are in the same direction, and withhold it otherwise’ was designed, and its effectiveness was then evaluated. Impulse excitation tests demonstrate 3 times increase in damping ratio and 12.8 dB attenuation of the resonance peak value compared to the passive state. Wind tunnel control tests results demonstrate the effectiveness of the MHL-FC, where the attenuation of acceleration RMS and resonance peak in the aircraft centroid are 33.4% and 34.8% compared to the passive state, respectively.</p>

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Characterization and vibration control of a magnetorheological damper-based tail support for wind tunnel tests

  • 期刊论文

  • 发表日期：

    2025年5月5日

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  • Wang Li,
  • Jie Fu,
  • Can Zhong,
  • Miao Yu,
  • Hak-Keung Lam

摘要

The stochastic vibration of the aircraft with tail support degrades the sensor’s data accuracy seriously in wind tunnel test, a magnetic-controlled magnetorheological damper (MRD) based tail support (MRTS) can suppress the vibration adaptively. Nevertheless, system distributed features and the nonlinearity of MRTS pose challenges for controller design. This paper proposes an indirect measurement approach for characterization of MRD on distributed structure, and bases on this, deduces maximum hysteresis loop criterion based fuzzy controller (MHL-FC) for vibration control. Initially, the dynamic response of MRD, was obtained by subtracting the real-time force–displacement response of the original support from that of the MRTS. Subsequently, aiming at increase the area (energy dissipation) of the MRD’s force–displacement hysteresis loop, MHL-FC with strategy describes by ‘apply current when velocity and displacement are in the same direction, and withhold it otherwise’ was designed, and its effectiveness was then evaluated. Impulse excitation tests demonstrate 3 times increase in damping ratio and 12.8 dB attenuation of the resonance peak value compared to the passive state. Wind tunnel control tests results demonstrate the effectiveness of the MHL-FC, where the attenuation of acceleration RMS and resonance peak in the aircraft centroid are 33.4% and 34.8% compared to the passive state, respectively.