阻力舵机翼颤振特性仿真与风洞试验

李永昌; 汉怿哲; 戴玉婷; 杨超

doi:10.7638/kqdlxxb-2024.0022

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阻力舵机翼颤振特性仿真与风洞试验

研究论文 | 更新时间：2026-05-28

- 阻力舵机翼颤振特性仿真与风洞试验
- Numerical and experimental study on flutter characteristics of a wing with drag rudder
- 空气动力学学报 2025年43卷第12期页码：135-143
- 作者机构：
  
  1. 北京航空航天大学航空科学与工程学院,北京,100191
  2. 天目山实验室,杭州,310023
  3. 杭州市北京航空航天大学国际创新研究院（北京航空航天大学国际创新学院）,杭州,311115
- 作者简介：
  
  李永昌（1995—），男，山东德州人，工程师，研究方向：气动弹性力学. E-mail：liyongchang@buaa.edu.cn
  戴玉婷*，女，博士，教授，研究方向：气动弹性力学. E-mail：yutingdai@buaa.edu.cn
- 基金信息：
  
  国家自然科学基金（12472332）
- DOI：10.7638/kqdlxxb-2024.0022
  中图分类号： V215.3
- 纸质出版：2025
- 稿件说明：
移动端阅览
李永昌, 汉怿哲, 戴玉婷, 等. 阻力舵机翼颤振特性仿真与风洞试验[J]. 空气动力学学报, 2025, 43(12): 135−143.

LI Yongchang, HAN Yizhe, DAI Yuting, et al. Numerical and experimental study on flutter characteristics of a wing with drag rudder[J]. 2025, 43(12): 135-143.
李永昌, 汉怿哲, 戴玉婷, 等. 阻力舵机翼颤振特性仿真与风洞试验[J]. 空气动力学学报, 2025, 43(12): 135−143. DOI： 10.7638/kqdlxxb-2024.0022

LI Yongchang, HAN Yizhe, DAI Yuting, et al. Numerical and experimental study on flutter characteristics of a wing with drag rudder[J]. 2025, 43(12): 135-143. DOI： 10.7638/kqdlxxb-2024.0022.

摘要

阻力舵是一种用于飞翼布局飞行器的非常规操纵面，阻力舵开裂产生偏航力矩实现航向操纵，其气动力具有较强非线性。针对低速大展弦比三维阻力舵机翼模型，提出了一种基于颤振频率处高精度非定常气动力修正的阻力舵机翼频域颤振分析方法，并开展该阻力舵机翼低速颤振风洞试验研究。将考虑非定常气动力修正的颤振结果与风洞试验结果进行对比，得到了不同开裂角下的阻力舵机翼颤振规律。仿真与风洞试验结果均表明，随着开裂角增大，阻力舵机翼颤振速度提高。相比于无开裂状态，单侧20°开裂角下该阻力舵机翼颤振速度提高约8.5%。

Abstract

The drag rudder serves as an unconventional control surface specifically designed for flying wing aircraft. Positioned near the wingtips

the drag rudder splits to generate drag force and yawing moments

which exhibits significant nonlinear characteristics. This paper introduces a flutter analysis method for drag rudder equipped wing model

which is based on high-precision unsteady aerodynamic force corrections at the flutter frequency domain. Subsequently

a low-speed wind tunnel test for the drag-rudder wing flutter is conducted. The study reveals the flutter patterns of the drag-rudder wing under various split angles by comparing the simulation and wind tunnel test results. Both sets of results indicate that an increase in the split angle leads to a higher flutter speed of the drag-rudder wing. Specificially

a unilateral 20° split angle results in an approximately 8.5% increase in flutter speed compared to the non-split state.

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references

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