一种仿生蜻蜓式垂直起降喷管的流动特性分析及优化设计

赵海宇; 宋经远; 胡双卫; 钟锐; 王青山

doi:10.7638/kqdlxxb-2023.0063

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一种仿生蜻蜓式垂直起降喷管的流动特性分析及优化设计

研究论文 | 更新时间：2026-05-28

- 一种仿生蜻蜓式垂直起降喷管的流动特性分析及优化设计
- Flow characteristic analysis and optimization design of a bionic dragonfly vertical takeoff and landing nozzle
- 空气动力学学报 2024年42卷第5期页码：45-52
- 作者机构：
  
  1. 中南大学机电工程学院,长沙,410083
  2. 中国航发沈阳发动机研究所,沈阳,110015
- 作者简介：
  
  赵海宇（1997—），男，硕士研究生，研究方向：空气轴承、喷管等的气动研究. E-mail：zhy1997910@163.com
  王青山*（1989—），男，教授，硕士生导师，研究方向：数字孪生，主动控制，转子动力学，结构声学，计算力学，结构动力学. E-mail：qingshanwang@csu.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0063
  中图分类号： V231
- 纸质出版：2024
- 稿件说明：
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赵海宇, 宋经远, 胡双卫, 等. 一种仿生蜻蜓式垂直起降喷管的流动特性分析及优化设计[J]. 空气动力学学报, 2024, 42(5): 45−52.

ZHAO Haiyu, SONG Jingyuan, HU Shuangwei, et al. Flow characteristic analysis and optimization design of a bionic dragonfly vertical takeoff and landing nozzle[J]. 2024, 42(5): 45-52.
赵海宇, 宋经远, 胡双卫, 等. 一种仿生蜻蜓式垂直起降喷管的流动特性分析及优化设计[J]. 空气动力学学报, 2024, 42(5): 45−52. DOI： 10.7638/kqdlxxb-2023.0063

ZHAO Haiyu, SONG Jingyuan, HU Shuangwei, et al. Flow characteristic analysis and optimization design of a bionic dragonfly vertical takeoff and landing nozzle[J]. 2024, 42(5): 45-52. DOI： 10.7638/kqdlxxb-2023.0063.

摘要

为提高飞行器排气系统的隐身性及机动性，提出了一种仿生蜻蜓式垂直起降喷管，并对不同模式下喷管的流动特性及流道优化进行研究。首先运用CFD方法分别对常规巡航、S形隐身以及垂直起降模式下的蜻蜓式垂直起降喷管进行流场数值仿真，探究该喷管的流动特性；然后在此基础上，分别研究喷管各舱段间相对转角对S形隐身模式及垂直起降模式下喷管气动特性的影响规律，得出相应模式下气动性能较优的蜻蜓式垂直起降喷管。研究结果表明：相同条件下，常规巡航模式下喷管气动性能较优；各舱段相对转角对喷管气动性能有较大影响，其中转角

、

分别为−34°、12°、22°的S形隐身模式喷管以及

、

分别为35°、30°、30°的垂直起降模式喷管的综合气动性能较优。

Abstract

In order to improve the stealth performance and maneuverability of the aircraft exhaust system

this paper proposes a bionic dragonfly vertical takeoff and landing nozzle

whose flow characteristics and optimization under different modes are investigated. The Computational Fluid Dynamics approach is used to simulate the flow fields of this nozzle in the cruise

S-type stealth

and vertical takeoff and landing modes. Based on the analyses of the obtained flow fields in each mode

the effects of t

he relative angle between adjacent nozzle sections on the nozzles's aerodynamic characteristics in the S-type stealth mode and the vertical takeoff and landing mode were studied

yielding an optimized combination of the relative angles for each mode. The results show that

under the same condition

the conventional cruise-mode nozzle has a better aerodynamic performance; the relative angle of adjacent nozzle sections significantly impacts on the aerodynamic performance of the nozzle. The overall aerodynamic performance of the S-type stealth mode nozzle with an angle combination

= −34°

= 12° and

= 22° and the vertical takeoff and landing mode nozzle with

= 35°

= 30° and

= 30° are better.

关键词

Keywords

references

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