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In this work, the vibration acceleration caused by the rigid rotor of compound variable speed helicopter in hover is measured and investigated via vibration analyzer instrumentations. The experiments are carried out on two scale-model rigid rotors with the same geometry. The fuselage accelerations in the \(x, y\) and \(z\) directions caused by the rigid rotor are measured when the blade pitch is \(\theta =5\sim 12^\circ \) and the rotor speed is \(\Omega =500\sim 1200r/min\) . The 1 ~ 8th order acceleration in different states is analyzed by the vibration analyzer software to investigate the helicopter vibration. When increasing the rotor speed and increasing the blade pitch can increase the same lift, adjusting the blade pitch is a priority. The first-order and multiple-blade order acceleration are more prominent at the stable rotor speed. Some results from this experiment maybe useful in designing variable speed compound helicopters in the future.

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Experimental Study on Compound Helicopter Vibration of Scale-Model Rigid Rotor Under Variable Speeds in Hover

  • 会议论文

  • 发表日期：

    2025年

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  • Liang Li,
  • Peizhi Liu,
  • Xiongwen Hu,
  • Yuguo Xu,
  • Anan Xu,
  • Yonghui Liu,
  • Nian Ding

摘要

In this work, the vibration acceleration caused by the rigid rotor of compound variable speed helicopter in hover is measured and investigated via vibration analyzer instrumentations. The experiments are carried out on two scale-model rigid rotors with the same geometry. The fuselage accelerations in the \(x, y\) and \(z\) directions caused by the rigid rotor are measured when the blade pitch is \(\theta =5\sim 12^\circ \) and the rotor speed is \(\Omega =500\sim 1200r/min\) . The 1 ~ 8th order acceleration in different states is analyzed by the vibration analyzer software to investigate the helicopter vibration. When increasing the rotor speed and increasing the blade pitch can increase the same lift, adjusting the blade pitch is a priority. The first-order and multiple-blade order acceleration are more prominent at the stable rotor speed. Some results from this experiment maybe useful in designing variable speed compound helicopters in the future.