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弹箭与制导学报 >

2011 , Vol. 31 >Issue 2: 120 - 122

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2011.02.032

火箭技术

带燃气舵的固体火箭发动机尾流仿真

  • 莫展 ,
  • 白涛涛 ,
  • 郭颜红
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  • 中国空空导弹研究院,河南洛阳 471009

莫展(1982-),男,河南洛阳人,硕士研究生,研究方向:导弹推进系统。

收稿日期: 2010-05-29

  网络出版日期: 2025-05-30

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Numerical Analysis of Plume Field for SRM with Gas Vane

  • MO Zhan ,
  • BAI Taotao ,
  • GUO Yanhong
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  • China Airborne Missile Academy, Henan Luoyang 471009, China

Received date: 2010-05-29

  Online published: 2025-05-30

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摘要

燃气舵的扰动使得固体火箭发动机高度欠膨胀的尾流场显得更加复杂。文中采用数值仿真计算的方法对比研究了不同高度下相同自由来流马赫数时的带燃气舵发动机尾流场的特性。得到存在燃气舵扰动时固体火箭发动机高度欠膨胀尾流场的轴向截面呈十字状;并且随着高度的增加尾流场膨胀程度增加,温度边界向外扩展;同时得到尾流场的长度约为200倍的发动机喷管出口直径。

关键词： 固体火箭发动机; 燃气舵; 尾流场; 数值仿真

本文引用格式

莫展 , 白涛涛 , 郭颜红 . 带燃气舵的固体火箭发动机尾流仿真[J]. 弹箭与制导学报, 2011 , 31(2) : 120 -122 . DOI: 10.15892/j.cnki.djzdxb.2011.02.032

Abstract

The plume field of solid rocket motor (SRM) with gas vane is much more complex than the one without the gas vane. The plume fields at the different altitude with the same free stream Mach number were compared by numerical simulation. The axis section of the SRM's plume field with gas vane is cross-shaped. The plume field and temperature boundary expands with the altitude increase. The length of the plume field is about 200 fold of nozzle's outlet diameter.

Key words： SRM; gas vane; plume field; numerical simulation

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参考文献

[1]
李军, 曹从咏, 徐强. 固体火箭发动机羽流场特性的数值研究[J]. 弹箭与制导学报, 2003, 23(2): 307-312.
[2]
张福祥. 火箭燃气射流动力学[M]. 北京: 国防工业出版社, 1988.
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赵承庆. 气体射流动力学[M]. 北京: 北京理工大学出版社, 1998.
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李军, 李献伟. 推力矢量发动机射流流场的数值分析[J]. 弹箭与制导学报, 2005, 25(4): 80-82.
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