Study on Vibration Reduction Technology of Coaxial Rigid Rotor Based on High‑Order Harmonic Control

WEI Wulei; YU Zhihao; FAN Feng; ZHAO Jinrui

doi:10.16356/j.2097-6771.2026.02.006

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Study on Vibration Reduction Technology of Coaxial Rigid Rotor Based on High‑Order Harmonic Control

更新时间：2026-04-30

- Study on Vibration Reduction Technology of Coaxial Rigid Rotor Based on High‑Order Harmonic Control
- Journal of Nanjing University of Aeronautics & Astronautics（Natural Science Edition） Vol. 58, Issue 2, Pages: 305-312(2026)
- 作者机构：
  
  中国直升机设计研究所旋翼动力学全国重点实验室，景德镇 333001
- 作者简介：
- 基金信息：
- DOI：10.16356/j.2097-6771.2026.02.006
  CLC： V212.4
- Received：12 November 2025，
  
  Revised：2026-03-01，
  
  Published：28 April 2026
- 稿件说明：
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魏武雷，余智豪，樊枫，等. 基于高阶谐波控制的共轴刚性旋翼减振技术研究［J］. 南京航空航天大学学报（自然科学版），2026，58（2）：305⁃312.

WEI Wulei， YU Zhihao， FAN Feng， et al. Study on vibration reduction technology of coaxial rigid rotor based on high‑order harmonic control［J］. Journal of Nanjing University of Aeronautics & Astronautics（Natural Science Edition），2026， 58（2）：305⁃312.
魏武雷，余智豪，樊枫，等. 基于高阶谐波控制的共轴刚性旋翼减振技术研究［J］. 南京航空航天大学学报（自然科学版），2026，58（2）：305⁃312. DOI： 10.16356/j.2097-6771.2026.02.006.

WEI Wulei， YU Zhihao， FAN Feng， et al. Study on vibration reduction technology of coaxial rigid rotor based on high‑order harmonic control［J］. Journal of Nanjing University of Aeronautics & Astronautics（Natural Science Edition），2026， 58（2）：305⁃312. DOI： 10.16356/j.2097-6771.2026.02.006.

摘要

针对共轴直升机高速前飞时振动载荷较大的问题，本文研究了对共轴双旋翼施加高阶谐波控制（High⁃order harmonic control， HHC）进行减振主动控制。文中创新性地将经典中等变形梁桨叶结构动力学模型、含自由尾迹的旋翼非定常气动模型以及HHC主动控制模型深度耦合，建立了适用于共轴双旋翼的高阶谐波主动控制气弹综合分析模型。以XH‑59A共轴双旋翼为分析对象，在模型验证有效的基础上，开展了上、下旋翼总距高阶谐波控制的幅值、相位等参数对桨毂垂向振动载荷的影响性分析。研究表明：共轴双旋翼桨毂减振效果随高阶谐波控制幅值增加呈先增大后减小规律，即在合适的幅值或相位下，高阶谐波控制能有效抑制桨毂垂向振动载荷；3阶和6阶谐波均可大幅降低相同阶次的桨毂垂向振动，最大降幅能达到90%，但对其他阶次的桨毂垂向振动影响有限。

Abstract

Aiming at the issue of large vibration loads during high-speed forward flight of coaxial helicopters， the implementation of high-order harmonic control（HHC） on the coaxial rotors system is considered for active vibration suppression control. In this paper， the classical moderate deflection beam structural dynamics model of rotor blades， the unsteady aerodynamic model of rotor with free wake， and the HHC active control model are innovatively and deeply coupled. A comprehensive aeroelastic analysis model for high-harmonic active control suitable for coaxial dual rotors is established. Based on the validated model， the XH-59A coaxial dual-rotor system is selected as the research object， and a systematic parametric analysis of the effects of HHC parameters， such as amplitude and phase， of collective pitch on the vertical hub vibration loads of the upper and lower rotors is conducted. The study shows that the hub vibration reduction effect of coaxial twin rotors first increases and then decreases with the increase of HHC amplitude. That is， HHC can effectively suppress the vertical vibration load of the hub under appropriate amplitude or phase conditions. Both 3/rev and 6/rev harmonics can significantly reduce the corresponding-order vertical hub vibrations， achieving a maximum reduction of up to 90%， although their influence on vibrations of different orders is limited.

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references

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Related Institution

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics & Astronautics

（南京航空航天大学直升机旋翼动力学国家级重点实验室，，）

Science and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute

National Key Laboratory of Science and Technology on Rotorcaft Aeromechanics, Nanjing University of Aeronautics & Astronautics

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