Control mechanism of the thickness noise based on sound pressure cancellation

HE Xiang; SHI Yongjie; XU Guohua

doi:10.7638/kqdlxxb-2018.0049

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Control mechanism of the thickness noise based on sound pressure cancellation

更新时间：2026-05-28

- Control mechanism of the thickness noise based on sound pressure cancellation
- Vol. 37, Issue 6, Pages: 893-900(2019)
- 作者机构：
  
  南京航空航天大学直升机旋翼动力学国家级重点实验室,江苏,南京,210016
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0049
  CLC： TB533+.2;V275+.1
- Published：2019
- 稿件说明：
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贺祥, 史勇杰, 徐国华. 基于声压相消的旋翼厚度噪声控制机理[J]. 空气动力学学报, 2019, 37(6): 893-900.

HE Xiang, SHI Yongjie, XU Guohua. Control mechanism of the thickness noise based on sound pressure cancellation[J]. 2019, 37(6): 893-900.
贺祥, 史勇杰, 徐国华. 基于声压相消的旋翼厚度噪声控制机理[J]. 空气动力学学报, 2019, 37(6): 893-900. DOI： 10.7638/kqdlxxb-2018.0049.

HE Xiang, SHI Yongjie, XU Guohua. Control mechanism of the thickness noise based on sound pressure cancellation[J]. 2019, 37(6): 893-900. DOI： 10.7638/kqdlxxb-2018.0049.

摘要

低频、面内传播的旋翼厚度噪声对于直升机适航及声隐身特性具有重要影响。本文基于声压相消原理，建立一种通过在桨叶外端布置阻力激励器来进行旋翼厚度噪声降噪的控制方案，并开展了其控制机理的数值模拟研究。以AH-1/OLS旋翼为研究对象，分析了厚度噪声的组成以及展弦比等参数对噪声特性的影响；进行了控制力噪声形成特性以及控制力幅值、频率等参数的影响规律研究；并分析了不同飞行状态下阻力激励控制方法对旋翼厚度噪声降噪特性的影响。结果表明：当桨尖阻力激励器产生的非定常阻力在桨盘平面90°方位角处变化率最大时，阻力产生的抑制声波可以有效降低旋翼前方区域的噪声；相比于高阶谐波控制力，采用低阶谐波控制力进行厚度噪声降噪时，降噪区域范围大，但所需的控制力幅值较大；相同的桨尖阻力，前飞状态下的降噪效果更好。

Abstract

The low harmonic in-plane thickness noise has an important influence on the airworthiness and inaudibility characteristics of helicopter. A new numerical simulation by using the cancellation of opposite sound pressure waves from on-blade active actuator is developed to study the control mechanism of rotor thickness noise. Firstly

the composition of the thickness noise and parametric study to examine the effects of aspect ratio and so on are respectively performed for AH-1/OLS rotor. The characteristics of sound waves formation and the influence of the amplitude and harmonic of active tip force on the cancellation of rotor thickness noise are then deeply assessed. The influence of on-blade active actuator on the thickness noise reduction characteristics is analyzed in different flight conditions. The results show that

the sound waves from the change rate of tip force

opposite to thickness pressure waves

which is the largest in the advance side of rotor

can reduce the peak thickness noise levels in the front of rotor. Compared with low harmonic tip force

high harmonic tip force is found to need small amplitude to cancel the noise at the target observer location

which means that the performance penalty of the additional force is slight. But

the cancellation effectiveness occurred over a narrow region.

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references

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