等离子体冰形调控改善翼型/机翼气动性能的试验研究

梁华; 谢理科; 吴云; 刘雪城; 苏志; 白成宏

doi:10.7638/kqdlxxb-2021.0234

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等离子体冰形调控改善翼型/机翼气动性能的试验研究

翼型研究新进展 | 更新时间：2026-05-28

- 等离子体冰形调控改善翼型/机翼气动性能的试验研究
- Experimental study on aerodynamic performance improvement of airfoil/wing based on plasma ice shape modulation
- 空气动力学学报 2021年39卷第6期页码：156-164
- 作者机构：
  
  1. 空军工程大学等离子体动力学重点实验室,西安,710038
  2. 中国人民解放军95889部队
- 作者简介：
  
  梁华*（1982-），男，博士后，副教授，研究方向：等离子体流动控制与防除冰. E-mail：lianghua82702@163.com
- 基金信息：
  
  国家自然科学基金（12002384）;国防科技重点实验室基金（ LK2020050044）;重庆市重点实验室基金（GATRI2020C06003）
- DOI：10.7638/kqdlxxb-2021.0234
  中图分类号： O532+.2;V211.41
- 纸质出版：2021
- 稿件说明：
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梁华, 谢理科, 吴云, 等. 等离子体冰形调控改善翼型/机翼气动性能的试验研究[J]. 空气动力学学报, 2021, 39(6): 156−164, 195.

LIANG Hua, XIE Like, WU Yun, et al. Experimental study on aerodynamic performance improvement of airfoil/wing based on plasma ice shape modulation[J]. 2021, 39(6): 156-164.
梁华, 谢理科, 吴云, 等. 等离子体冰形调控改善翼型/机翼气动性能的试验研究[J]. 空气动力学学报, 2021, 39(6): 156−164, 195. DOI： 10.7638/kqdlxxb-2021.0234

LIANG Hua, XIE Like, WU Yun, et al. Experimental study on aerodynamic performance improvement of airfoil/wing based on plasma ice shape modulation[J]. 2021, 39(6): 156-164. DOI： 10.7638/kqdlxxb-2021.0234.

摘要

飞机结冰是严重影响飞行安全的潜在危险因素之一。本文针对飞机结冰问题提出了保障结冰条件下飞行安全的等离子体冰形调控方法，开展了基于等离子防除冰冰形调控的冰风洞试验，进行了冰形调控规律的探索，并在无人机上对冰形调控方法进行了验证。结果表明，等离子体冰形调控可按照设计的布局防止结冰从而获得所预期的调制冰形；单个冰形宽度与弦长比即无量纲冰形尺寸（

）和单个冰形宽度与单个无冰间隙宽度比即无量纲调控比例（

）决定了调控效果；对于固定的无量纲调控比例，无量纲冰形尺寸比值在0.1～0.2之间时获得最佳的升力系数；无量纲调控比越低，机翼升力系数越高。在无人机飞行测试中，通过前缘冰形调制策略提高飞行气动性能的验证，结果表明：相比于机翼前缘全结冰，前缘冰形调制后，失速迎角延迟4°，在大迎角下的升力系数普遍恢复了20%～30%。本文给出了冰形调控的方法和调控规律，并指出选用合适的无量纲冰形尺寸和调制比有助于获得结冰条件下最佳的气动性能，同时通过无人机飞行试验验证了方法的有效性。

Abstract

Aircraft icing is one of the potential hazards that seriously affects flight safety. This paper proposes a plasma ice shape modulation method to ensure flight safety under aircraft icing conditions. This method was verified on an unmanned aerial vehicle (UAV). An ice wind tunnel experiment employing the plasma anti-icing ice shape modulation was carried out to explore the ice shape modulation law. Results show that the plasma ice shape modulation can prevent freezing according to the designed layout and obtain desired modulated ice shapes. The ratio of single ice shape width to chord length

namely the dimensionless ice shape size

and the ratio of single ice shape width to single ice-free gap width

namely the dimensionless modulation ratio determine the control effect. For a fixed dimensionless modulation ratio

the optimal lift coefficient can be obtained with the dimensionless ice shape size between 0.1 and 0.2. The lower the dimensionless modulation ratio

the higher the lift coefficient. The flight test indicates that the ice shape modulation strategy can improve the aerodynamic performance of UAV. Compared with the full icing on the leading edge of the wing

the stall angle is delayed by 4° after the ice shape modulation. Lift coefficient has generally recovered by 20%-30% at high angles of attack. In summary

this paper provides the method and law of ice shape modulation. Choosing appropriate dimensionless ice shape size and modulation ratio will help to obtain the best aerodynamic performance under icing conditions. As research continues

the effectiveness of this method is verified by the flight test of UAV.

关键词

Keywords

references

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