飞行器操纵面嗡鸣风洞试验技术综述

闫昱; 路波; 杨兴华; 郭洪涛; 余立

doi:10.7638/kqdlxxb-2021.0303

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飞行器操纵面嗡鸣风洞试验技术综述

综述 | 更新时间：2026-05-28

- 飞行器操纵面嗡鸣风洞试验技术综述
- Review on buzz wind tunnel test technology for aircraft control surfaces
- 空气动力学学报 2022年40卷第3期页码：1-9
- 作者机构：
  
  中国空气动力研究与发展中心高速空气动力研究所,绵阳,621000
- 作者简介：
  
  闫昱（1985-），河南新郑人，硕士，副研究员，研究方向：气动弹性风洞试验技术. E-mail：aeroelastics@126.com
  余立*（1975-），安徽肥东人，硕士，研究员，研究方向：空气动力学. E-mail：yuli@cardc.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0303
  中图分类号： V211.71;V216.2+4
- 纸质出版：2022
- 稿件说明：
移动端阅览
闫昱, 路波, 杨兴华, 等. 飞行器操纵面嗡鸣风洞试验技术综述[J]. 空气动力学学报, 2022, 40(3): 1−9.

YAN Yu, LU Bo, YANG Xinghua, et al. Review on buzz wind tunnel test technology for aircraft control surfaces[J]. 2022, 40(3): 1-9.
闫昱, 路波, 杨兴华, 等. 飞行器操纵面嗡鸣风洞试验技术综述[J]. 空气动力学学报, 2022, 40(3): 1−9. DOI： 10.7638/kqdlxxb-2021.0303

YAN Yu, LU Bo, YANG Xinghua, et al. Review on buzz wind tunnel test technology for aircraft control surfaces[J]. 2022, 40(3): 1-9. DOI： 10.7638/kqdlxxb-2021.0303.

摘要

操纵面嗡鸣是飞行器跨声速飞行时发生的气动弹性动不稳定现象。嗡鸣的发生，轻则降低飞行器操纵面效率，重则导致灾难性的飞行事故，是除颤振外飞行器设计部门重点关注的气动弹性难题。操纵面嗡鸣涉及激波与边界层的相互作用，目前尚没有准确预测嗡鸣的计算方法，通常采用风洞试验来获取相关数据。操纵面嗡鸣风洞试验可以利用风洞再现嗡鸣现象，研究嗡鸣特性，是飞行器研制阶段检验操纵面防嗡鸣设计最行之有效的手段。本文回顾了国内外操纵面嗡鸣风洞试验研究现状，梳理了操纵面嗡鸣的发生机理、触发条件及分型依据，对操纵面嗡鸣试验风洞选取、模型设计、试验方法提供了建议，对颤振试验中可能出现的嗡鸣问题提供了判别方法，对后续的工作进行了展望。

Abstract

Control surface buzz of the aircraft is an aeroelastic instability phenomenon during the transonic flight. The occurrence of buzz can reduce the efficiency of aircraft control surfaces

and even cause disastrous flight accidents. Therefore

the buzz phenomenon is another difficult aeroelastic problem that the aircraft design department focuses on in addition to the flutter. Control surface buzz is related to the interaction between the shock wave and the boundary layer

and there is no accurate calculation method to obtain the buzz characteristics

thus the wind tunnel test is usually used to acquire relevant data. The buzz wind tunnel test can be used to reproduce the buzz phenomenon and study its characteristics

which is the most effective method to verify the anti-buzz design in the aircraft development stage. In the present study

we review previous studies of buzz wind tunnel tests. The occurrence mechanism

triggering conditions and control surface buzz classification are sorted out. Feasible suggestions for suitable wind tunnel selection

model design and test methods of buzz wind tunnel test are provided

and effective methods to distinguish the buzz phenomenon during the flutter test are discussed. The follow-up work is presented in the end.

关键词

Keywords

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