[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

一种小型全轴摆动喷管流场计算和性能分析

  • 尚永腾 ,
  • 白涛涛
展开
  • 中国空空导弹研究院,河南洛阳 471009

尚永腾(1987-),男,山东德州人,工程师,研究方向:固体火箭发动机喷管设计与研究。

收稿日期: 2019-01-17

  网络出版日期: 2025-05-19

基金资助

航空基金(20180112001);中国空空导弹研究院科技创新基金(201604S06)

Flow Field Calculation and Performance Analysis of a Small Axisymmetric Swing Nozzle

  • SHANG Yongteng ,
  • BAI Taotao
Expand
  • China Airborne Missile Academy, Henan Luoyang 471009, China

Received date: 2019-01-17

  Online published: 2025-05-19

摘要

对一种长尾管式的小型全轴摆动喷管进行流场和性能分析,采用CFD三维流场仿真方法,完成了一系列不同工况的数值计算。结果表明:摆动喷管整体流场均匀,基本不受摆动的影响,分离线附近存在局部高压和低速涡流,其与压强、通喉比和工作介质相关;摆动喷管推力损失小、致偏效率高、线性度好,摆动时的内流场负载不高而摩擦力较大。验证了摆动喷管具有良好的流场均匀性和明显的性能优势,并提出了降低摆动力矩的措施。

本文引用格式

尚永腾 , 白涛涛 . 一种小型全轴摆动喷管流场计算和性能分析[J]. 弹箭与制导学报, 2019 , 39(4) : 1 -4 . DOI: 10.15892/j.cnki.djzdxb.2019.04.001

Abstract

In order to analyze the flow field and performance of a small long-tail axisymmetric swing nozzle, A series of different conditions were calculated by 3-D CFD simulation method. The results show that the swing nozzle has a uniform flow field that nearly invariable with different angle. There are high local pressure and low velocity vortex near the split line which are related to pressure, channel-throat ratio and working medium. The swing nozzle has low thrust lost, high deflecting efficiency and good linearity and the swing brings small inner flow load and great fiction force. The good flow field uniformity and better performance of the swing nozzle is verified and measures to reduce shaking moment are proposed.

[an error occurred while processing this directive]
[1]
王永寿. 导弹的推力矢量控制技术[J]. 飞航导弹, 2005 (1): 54- 60.

[2]
段冬冬, 沈小林. 推力矢量技术在空空导弹上的应用与分析[J]. 飞航导弹, 2012 (4): 84- 87.

[3]
杨敬贤. 小型固体火箭发动机摆动喷管设计技术研究[D]. 上海: 上海交通大学, 2015.

[4]
LARA M.R. ATK space propulsion products catalog[M]. [S. l.]: Alliant Techsystems Inc., 2008: 16- 24.

[5]
ORBEKK E. Supersonic split line TVC technology and tes-ting at Nammo Raufoss AS: AIAA 2006-4940 [R]. Red-stone: AIAA, 2006.

[6]
ORBEKK E. Novel TVC system utilizing guide vanes withjet flap's into a high efficiency compact nozzle: AIAA 2005-4499 R. Redstone: AIAA, 2005.

[7]
杨玉新, 胡春波, 甘晓松,等. 喷管摆动对固体火箭发动机内两相流动的影响[J]. 弹箭与制导学报, 2006, 26 (1): 104- 107.

[8]
刘君, 黄琳, 夏智勋. 潜入式摆动喷管两相内流场数值模拟. 固体火箭技术, 2003, 26 (4): 18- 21.

[9]
周红梅, 黄志勇, 李季颖. 具有摆动喷管发动机三维内流场数值分析. 导弹与航天运载技术, 2011 (6): 15- 18.

[10]
刘宇涛, 田小涛, 邓恒,等. 一种摆动喷管的流场和传热特性研究. 弹箭与制导学报, 2017, 37 (1): 77– 80.

[11]
杜长宝, 李军. 固体火箭发动机燃气舵推力损失的数值分析与测试 弹箭与制导学报, 2010, 30 (2): 155- 157.

[12]
房雷, 莫展, 杜长宝,等. 发动机燃气舵气动特性研究[]. 航空兵器, 2013 (4): 34- 36.

文章导航

/

[an error occurred while processing this directive]