旋翼悬停状态形变特性及其对噪声的影响

李志彬; 曹亚雄; 林永峰; 孙伟; 袁明川

doi:10.7638/kqdlxxb-2021.0047

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旋翼悬停状态形变特性及其对噪声的影响

研究论文 | 更新时间：2026-05-28

- 旋翼悬停状态形变特性及其对噪声的影响
- Deformation characteristics of a hovering rotor and its influence on the aerodynamic noise
- 空气动力学学报 2022年40卷第5期页码：71-78
- 作者机构：
  
  中国直升机设计研究所直升机旋翼动力学重点实验室,景德镇,333001
- 作者简介：
  
  李志彬*（1993-），男，天津人，工程师，研究方向：直升机空气动力学、旋翼气动噪声. E-mail：lizb001@avic.com
- 基金信息：
  
  国防基础科研计划（JCKY2019205D002）;航空科学基金项目（20200057002001）
- DOI：10.7638/kqdlxxb-2021.0047
  中图分类号： V211.52
- 纸质出版：2022
- 稿件说明：
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李志彬, 曹亚雄, 林永峰, 等. 旋翼悬停状态形变特性及其对噪声的影响[J]. 空气动力学学报, 2022, 40(5): 71−78.

LI Zhibin, CAO Yaxiong, LIN Yongfeng, et al. Deformation characteristics of a hovering rotor and its influence on the aerodynamic noise[J]. 2022, 40(5): 71-78.
李志彬, 曹亚雄, 林永峰, 等. 旋翼悬停状态形变特性及其对噪声的影响[J]. 空气动力学学报, 2022, 40(5): 71−78. DOI： 10.7638/kqdlxxb-2021.0047

LI Zhibin, CAO Yaxiong, LIN Yongfeng, et al. Deformation characteristics of a hovering rotor and its influence on the aerodynamic noise[J]. 2022, 40(5): 71-78. DOI： 10.7638/kqdlxxb-2021.0047.

摘要

为研究桨叶弹性形变对旋翼气动噪声的影响，基于Camrad Ⅱ软件和FW-H方程，建立了考虑桨叶弹性形变的旋翼悬停气动噪声计算模型。其中，桨叶弹性形变量采用Camrad Ⅱ的弹性桨叶模型计算，形变桨叶外形采用三维网格精确描述，结合Camrad Ⅱ计算得到的旋翼非定常气动载荷，最后基于FW-H方程进行了形变旋翼悬停噪声的计算分析。同时，在风洞中采用双目立体视觉方法对模型旋翼进行形变测量试验，通过Camrad Ⅱ的仿真数据与试验数据的对比分析，发现仿真数据与试验数据基本吻合，验证了Camrad Ⅱ具有较好的可靠性，能够准确预估悬停状态下桨叶的弹性形变量。全尺寸旋翼的悬停噪声计算结果表明：在典型工作状态下，旋翼桨叶会发生明显的弹性形变，尤其在挥舞方向；桨叶形变不会改变旋翼悬停气动噪声的方向特性；在噪声的主要传播方向上，桨叶形变对厚度噪声和载荷噪声均会产生作用，进而导致总噪声的最大变化量约1.0 dB。通过本文研究表明，在对旋翼气动噪声，尤其是载荷噪声成分进行精确计算时，考虑桨叶的弹性形变是非常必要的。

Abstract

In order to study the influence of blade elastic deformation on rotor aerodynamic noise

based on Camrad Ⅱ and the FW-H equation

an aerodynamic noise calculation model that takes the blade elastic deformation into account has been established for a rotor in hover. The elastic blade model in Camrad Ⅱ is used to calculate the elastic shape variation of the blade. A three-dimensional grid is used to accurately describe the deformed blade. Combined with the unsteady aerodynamic load of the rotor obtained by Camrad Ⅱ

the hovering noise of the deformed blade is calculated and analyzed based on the FW-H equation. The binocular stereo vision method is used to measure the deformation of the model rotor in a wind tunnel. It is found that the numerical results are agree reasonably well with the experimental data

which verifies that Camrad Ⅱ has a good reliability and can accurately predict the elastic shape variation of the blade in hover. The hover noise characteristics of the full scale rotor are further calculated and analyzed. The results show that under typical working conditions

the rotor blade has obvious elastic deformation

especially in the flap direction. The blade deformation does not change the directivity of the noise in hover. However

it affects the thickness and loading noise in the main propagation direction

resulting in a maximum variation of about 1.0 dB in the total noise. Consequently

the influence of the blade elastic deformation should be considered for obtaining more accurate aerodynamic noise.

关键词

Keywords

references

BRENTNER K S. Prediction of helicopter rotor discrete frequency noise-a computer program incorporating realistic motions and advanced acoustic formulation: NASA-TM-87721[R]. Hampton, Virginia: National Aeronautics and Space Administration,, 1986.

RICHARD S. Modeling helicopter near-horizon harmonic noise due to transient maneuvers[D]. Maryland: University of Maryland College Park, 2012.

ALLEN C B. An unsteady multiblock multigrid scheme for lifting forward flight rotor simulation[J]. International Journal for Numerical Methods in Fluids, 2004, 45(9): 973-984. DOI: 10.1002/fld.711.

EDWARDS B, COX C. Revolutionary concepts for helicopter noise reduction: SILENT program: NASA/CR-2002-211650[R]. Hampton, Virginia: National Aeronautics and Space Administration, 2002.

FFOWCS-WILLIAMS J E, HAWKINGS D L. Sound generated by turbulence and surfaces in arbitrary motion[J]. Philosophical Transactions of the Royal Society, Series A, Mathematical and Physical Sciences, 1969, 264(1151): 321-342. https://doi.org/10.1098/rsta.1969.0031.

BRENTNER K. Modeling aerodynamically generated sound - Recent advances in rotor noise prediction[C ] // 38th Aerospace Sciences Meeting and Exhibit, Reno, NV. Reston, Virginia: AIAA, 2000. doi: 10.2514/6.2000-345

PASSE B J, SRIDHARAN A, BAEDER J D. Computational investigation of coaxial rotor interactional aerodynamics in steady forward flight[C ] // 33rd AIAA Applied Aerodynamics Conference, Dallas, TX. Reston, Virginia: AIAA, 2015. doi: 10.2514/6.2015-2883

SHARMA K, CORLE E, BRENTNER K, et al. Robust and automated coupling of RCAS and PSUWOPWOP[J]. AHS Aeromechanics Design for Transformative Vertical Flight, 2018.

WANG B, ZHAO Q J, FAN F, et al. Investigations on acoustic characteristics of rotor with improved CLOR blade-tip in hover based on experimental and prediction method[J]. Acta Aerodynamica Sinica, 2013, 31(4): 454-461. (in Chinese)

AOYAMA T, YANG C, KONDO N, et al. Comparison of noise reduction effect between AFC and conventional IBC by moving overlapped grid method[C ] // 12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference), Cambridge, Massachusetts. Reston, Virginia: AIAA, 2006. doi: 10.2514/6.2006-2609

AOYAMA T, YANG C, SAITO S. Numerical analysis of active flap for noise reduction using moving overlapped grid method[J]. Journal of the American Helicopter Society, 2007, 52(3): 189-200. DOI: 10.4050/jahs.52.189.

FARASSAT F. Linear acoustic formulas for calculation of rotating blade noise[J]. AIAA Journal, 1981, 19(9): 1122-1130. DOI: 10.2514/3.60051.

Misiorowski M, Gandhi F. Comparison of acoustic predictions using distributed and compact airloads[C]// 75th Annual Forum and Technology Display, May 13–16, Philadelphia, Pennsylvania, U.S.A, 2019.

BRENTNER K, JONES H. Noise prediction for maneuvering rotorcraft[C ] // 6th Aeroacoustics Conference and Exhibit, Lahaina, HI. Reston, Virginia: AIAA, 2000. doi: 10.2514/6.2000-2031

LI Z B, SUN W, YUAN M C. Research on the rapid calculation method of rotor aerodynamic noise[J]. Helicopter Technique, 2021(1): 1-7. (in Chinese)

FAN F. Research and application of computational methods for unsteady flow field and sound field of helicopter[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2013 (in Chinese).

LIU T, LIU P A, FAN F.. Influence of lift offset on coaxial rigid rotor blade loads and deformation[J]. Aeronautical Science Technology, 2020, 31(4): 42-49. (in Chinese) DOI: 10.19452/j.issn1007-5453.2020.04.007.

XIONG B S, XIONG K, LI X M, et al. Flapping angle measurement of helicopter rotor blade based on binocular vision[J]. Measurement Control Technology, 2016, 35(1): 34-37. (in Chinese)

XIONG B S, LUO Y H, HUANG J P, et al. Measurement method of torsion of helicopter rotor blades based on stereo vision[J]. Journal of Applied Sciences, 2018, 36(6): 950-957. (in Chinese)

ZUO C L, MA J, YUE T R, et al. Displacement and deformation measurements of helicopter rotor blades based on binocular stereo vision[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(1): 87-95. (in Chinese)

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