格尼襟翼对旋转导弹气动特性的影响

寇少博; 冯立好; 李晓; 杨欣; 刘松彬; 徐华松

doi:10.7638/kqdlxxb-2021.0401

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格尼襟翼对旋转导弹气动特性的影响

研究论文 | 更新时间：2026-05-28

- 格尼襟翼对旋转导弹气动特性的影响
- Effect of Gurney flaps on aerodynamic characteristics of a spinning missile
- 空气动力学学报 2023年41卷第1期页码：77-85
- 作者机构：
  
  1. 北京航空航天大学流体力学研究所,北京,100191
  2. 上海机电工程研究所,上海,201109
- 作者简介：
  
  寇少博（1997-），男，陕西人，硕士研究生，研究方向：流体力学. E-mail：zy2005308@buaa.edu.cn
  冯立好*，教授，研究方向：流动控制，空气动力学. E-mail：lhfeng@buaa.edu.cn
- 基金信息：
  
  上海航天科技创新基金
- DOI：10.7638/kqdlxxb-2021.0401
  中图分类号： TJ013
- 纸质出版：2023
- 稿件说明：
移动端阅览
寇少博, 冯立好, 李晓, 等. 格尼襟翼对旋转导弹气动特性的影响[J]. 空气动力学学报, 2023, 41(1): 77−85.

KOU Shaobo, FENG Lihao, LI Xiao, et al. Effect of Gurney flaps on aerodynamic characteristics of a spinning missile[J]. 2023, 41(1): 77-85.
寇少博, 冯立好, 李晓, 等. 格尼襟翼对旋转导弹气动特性的影响[J]. 空气动力学学报, 2023, 41(1): 77−85. DOI： 10.7638/kqdlxxb-2021.0401

KOU Shaobo, FENG Lihao, LI Xiao, et al. Effect of Gurney flaps on aerodynamic characteristics of a spinning missile[J]. 2023, 41(1): 77-85. DOI： 10.7638/kqdlxxb-2021.0401.

摘要

旋转导弹多采用斜置尾翼产生滚转力矩，但存在转速稳定性差等问题，影响了命中精度。为改善旋转导弹气动特性，本文采用在导弹尾翼后缘放置格尼襟翼的方式代替传统斜置尾翼产生滚转力矩。通过数值模拟方法，研究了不同高度格尼襟翼对导弹气动特性的影响规律，并与斜置尾翼模型进行对比。结果表明：格尼襟翼能够产生保持导弹旋转的滚转力矩，且格尼襟翼高度增加，滚转力矩增大；相比斜置尾翼，格尼襟翼能够为导弹提供更大的滚转力矩，对导弹侧向力的影响相对更小。不同来流马赫数下格尼襟翼的操纵效率略有差异，亚声速来流时，格尼襟翼产生的滚转力矩随着导弹迎角增加而减小；超声速来流时，格尼襟翼产生的滚转力矩几乎不随迎角变化而改变，与亚声速来流相比，格尼襟翼的操纵效率降低。进一步通过分析流场揭示了格尼襟翼产生滚转力矩的流动机理：格尼襟翼使得导弹尾翼后缘附近产生非对称流动，以致各尾翼出现非对称的压力差，从而产生保持导弹旋转的滚转力矩。

Abstract

The spinning missiles usually adopt oblique tails to generate the rolling moment. However

such a configuration suffers from the problem of poor stability of rotating speed

which affects the hitting accuracy. To improve the aerodynamic performance of spinning missiles

the traditional oblique tails are substituted with Gurney flaps on the trailing edge of the tails to generate rolling moment in the present study. Effect of the Gurney flap height on the aerodynamic characteristics of the missile is studied by performing numerical simulations

and also compared with the oblique tail model. The results show that the Gurney flaps can generate the rolling moment for the missile

which increases with the Gurney flap height. Compared to the oblique tail model

the Gurney flaps can provide a larger rolling moment for the missile with a relatively small impact on side force. The maneuvering efficiency of the Gurney flaps is slightly different at different Mach numbers. The rolling moment decreases with the increase of the angle of attack in the subsonic regime

while it remains nearly unchanged with the angle of attack variation in the supersonic regime. Meanwhile

the maneuvering efficiency of the Gurney flaps is lower in the supersonic regime compared to that in the subsonic regime. It is found that

the Gurney flaps induce asymmetric flow near the trailing edge of the missile tail

resulting in the occurrence of asymmetric pressure difference among the tails

thus leading to the rolling moment generation.

关键词

Keywords

references

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