航空学报 > 2024, Vol. 45 Issue (9): 528602-528602   doi: 10.7527/S1000-6893.2023.28602

基于高阶谐波控制的倾转旋翼近场气动噪声主动控制试验

马锦超1,2, 陆洋2(), 王亮权3, 宋奎辉3   

  1. 1.无锡职业技术学院 机械工程分院,无锡 214121
    2.南京航空航天大学 直升机旋翼动力学重点实验室,南京 210016
    3.中国空气动力研究与发展中心 旋翼空气动力学重点实验室,绵阳 621000
  • 收稿日期:2023-02-24 修回日期:2023-03-13 接受日期:2023-04-07 出版日期:2024-05-15 发布日期:2023-04-14
  • 通讯作者: 陆洋 E-mail:luyang@nuaa.edu.cn
  • 基金资助:
    中国空气动力研究与发展中心旋翼空气动力学重点实验室研究开放课题资助(RAL202103-3)

Active control test of tiltrotor near-field aeroacoustics based on higher harmonic control

Jinchao MA1,2, Yang LU2(), Liangquan WANG3, Kuihui SONG3   

  1. 1.School of Mechanical Technology,Wuxi Institute of Technology,Wuxi  214121,China
    2.National Key Laboratory of Science and Technology on Rotorcraft Aero-Mechanics,Nanjing university of aeronautics and astronautics,Nanjing  210016,China
    3.Rotor Aerodynamics Key Laboratory,China Aerodynamics Research and Development Center,Mianyang  621000,China
  • Received:2023-02-24 Revised:2023-03-13 Accepted:2023-04-07 Online:2024-05-15 Published:2023-04-14
  • Contact: Yang LU E-mail:luyang@nuaa.edu.cn
  • Supported by:
    Open Research Topic of the Key Laboratory of Rotor Aerodynamics, China Aerodynamics Research and Development Center(RAL202103-3)

摘要:

倾转旋翼飞行器的桨尖靠近机身,其近场气动噪声问题严重,理论研究表明,高阶谐波控制能够调整桨盘载荷分布,从而降低倾转旋翼对机身表面的气动噪声辐射。通过试验研究验证了高阶谐波控制(HHC)对倾转旋翼飞行器近场气动噪声的抑制效果。研制了一套用于模型倾转旋翼的HHC伺服控制系统,及倾转旋翼飞行器缩比机身模型;进一步在消声室环境下搭建了倾转旋翼飞行器近场气动噪声主动控制的HHC主动控制试验系统,开展了直升机模式下的噪声主动控制试验研究;验证了HHC对倾转旋翼飞行器近场气动噪声的主动控制效果。试验结果表明2 Ω的HHC控制输入的降噪效果最好,在直升机模式下,机身顶部观测点处的近场气动噪声最多可降低4.5 dB。

关键词: 倾转旋翼, 高阶谐波控制, 近场, 气动噪声, 主动控制

Abstract:

The proximity of tiltrotor aircraft blade tips to the fuselage causes a serious near-field aeroacoustics problem. Theoretical research shows that Higher Harmonic Control (HHC) input can adjust the load distribution of the rotor disc, thereby reducing the aeroacoustics radiation on the fuselage surface. In this paper, the suppression effect of HHC on near-field aeroacoustics in tiltrotor aircraft is verified experimentally. An HHC servo control system for model tiltrotor aircraft and a scaled fuselage model for tiltrotor aircraft are developed. An HHC active control test platform for near-field aeroacoustics in tiltrotor aircraft is further built in the anechoic chamber environment, and noise active control tests are carried out in helicopter mode. The active control effects of HHC on near-field aeroacoustics in tiltrotor aircraft are verified. The test results demonstrate that the 2 Ω HHC control input yields the best noise reduction performance. In helicopter mode, the near-field aeroacoustics at the observation point on the top of the fuselage can be reduced by up to 4.5 dB.

Key words: tiltrotor, higher harmonic control, near-field, aeroacoustics, active control

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