Numerical research on jet tab thrust vector nozzle aerodynamic characteristic

CONG Rongfei; WU Junqiang; ZHANG Changfeng; YE Youda

doi:10.7638/kqdlxxb-2016.0115

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Numerical research on jet tab thrust vector nozzle aerodynamic characteristic

更新时间：2026-05-28

- Numerical research on jet tab thrust vector nozzle aerodynamic characteristic
- Vol. 37, Issue 2, Pages: 234-241(2019)
- 作者机构：
  
  1. 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
  2. 中国空气动力研究与发展中心空气动力学国家重点实验室,绵阳,621000
  3. 国家计算流体力学实验室,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2016.0115
  CLC： V211.3
- Published：2019
- 稿件说明：
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丛戎飞, 吴军强, 张长丰, 叶友达. 扰流片式推力矢量喷管气动特性数值模拟研究[J]. 空气动力学学报, 2019, 37(2): 234-241.

CONG Rongfei, WU Junqiang, ZHANG Changfeng, et al. Numerical research on jet tab thrust vector nozzle aerodynamic characteristic[J]. 2019, 37(2): 234-241.
丛戎飞, 吴军强, 张长丰, 叶友达. 扰流片式推力矢量喷管气动特性数值模拟研究[J]. 空气动力学学报, 2019, 37(2): 234-241. DOI： 10.7638/kqdlxxb-2016.0115.

CONG Rongfei, WU Junqiang, ZHANG Changfeng, et al. Numerical research on jet tab thrust vector nozzle aerodynamic characteristic[J]. 2019, 37(2): 234-241. DOI： 10.7638/kqdlxxb-2016.0115.

摘要

为了满足工程应用中扰流片式推力矢量喷管控制率建模以及优化设计的需求，本文选取了三种几何外形的扰流片，并通过数值模拟手段，研究了扰流片几何形状对于轴对称喷管推力矢量气动特性的影响规律，提出了减小扰流片推力损失的设计方法。数值模拟结果表明，推力矢量角与推力损失系数都随着扰流片插入高度的增加而增加；对于矩形扰流片，可以通过增加扰流片宽度的方式减小推力损失，对于扇形扰流片，可以通过减小上圆弧圆心与扇形顶点距离的方式减小推力损失；在插入高度及面积一定时，对比不同形状的扰流片，弧顶矩形扰流片的推力矢量角及推力损失系数均为最大，圆形扰流片均为最小。

Abstract

The jet tab thrust vector control technology discussed in this paper has outstanding advantages in less thrust loss

faster response

stronger control forces

compared with jet vane technology

which meet the needs of future air combat for advanced air-to-air missile. In order to meet the requirements of control rate modeling and optimization of jet tab thrust vector control system

conical nozzle with spoilers in three different shapes

which are round

rectangle and sector

are numerically simulated. The effects of spoiler geometry parameters on the thrust vector performance are analyzed. The design method of reducing thrust loss of spoiler is presented. The results indicate that thrust vector angle and thrust loss ratio increases with increas

ing insertion depth of the spoiler. For the rectangular spoiler

thrust loss ratio decreases with the increase of spoiler width; and for the sector spoiler

thrust loss ratio decreases with the increase of the design parameter

. When the spoiler inserted depth and inserted area is constant

rectangle spoiler has the maximum thrust vector angle and thrust loss ratio

while round spoiler has the minimum.

关键词

Keywords

references

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HAN W C. Research on jet tab thrust vector control system[D]. Nanjing: Nanjing University of Science and Technology, 2011. (in Chinese)

CUI Y B, CHEN X, ZHOU C S, et al. Research on spoiler dynamic characteristic for thrust vector control[J]. Journal of Propulsion Technology, 2013, 34(8):1030-1034. (in Chinese)

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JIA H Y, WU X J, ZHOU N C, et al. Numerical investigation on coupling effects of multiple spouts and lateral jet interaction over missile missile configuration[J]. Acta Aerodynamica Sinica, 2017, 35(6):857-840. (in Chinese)

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BACK L H, CUFFEL R F. Detection of oblique shocks in a conical nozzle with a circular-arc throat[J]. AIAA Journal, 1966, 12(4):2219-2221.

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