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弹箭与制导学报 >

2017 , Vol. 37 >Issue 4: 98 - 100

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2017.04.023

火箭技术

某两侧进气固冲发动机二次燃烧性能提升仿真研究

  • 王希亮 ,
  • 陈志明 ,
  • 孙振华
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  • 1 中国空空导弹研究院,河南洛阳 471009
    2 航空制导武器航空科技重点实验室,河南洛阳 471009

王希亮(1975-),男,湖南益阳人,高级工程师,硕士,研究方向:固体火箭冲压发动机设计。

收稿日期: 2016-11-29

  网络出版日期: 2025-05-28

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Research on the Simulation of Two Times Combustion Performance Enhancement of a Bilateral Intake Ramjet

  • WANG Xiliang ,
  • CHEN Zhiming ,
  • SUN Zhenhua
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  • 1 China Airborne Missile Academy, Henan Luoyang 471009, China
    2 Aviation Key Laboratory of Science and Technology on Airborne Guided Weapons, Henan Luoyang 471009, China

Received date: 2016-11-29

  Online published: 2025-05-28

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摘要

为了提高采用头部两侧进气布局形式的固冲发动机的二次燃烧性能,以某地面连管试验用固冲发动机为研究对象,分别从进气道出口形式和燃气喷射方式两个方面对补燃室掺混燃烧流场的影响进行了仿真研究。结果表明:进气道出口结构形式对该种布局方案的补燃室二次燃烧性能有重大影响;在保持进气道出口结构不变的条件下通过合理配置一次燃气喷射方式可以在一定程度上提升二次燃烧性能。

关键词： 固体火箭冲压发动机; 补燃室; 掺混燃烧; 相对比冲; 数值模拟

本文引用格式

王希亮 , 陈志明 , 孙振华 . 某两侧进气固冲发动机二次燃烧性能提升仿真研究[J]. 弹箭与制导学报, 2017 , 37(4) : 98 -100 . DOI: 10.15892/j.cnki.djzdxb.2017.04.023

Abstract

In order to improve the two times combustion performance of solid rocket ramjet adopting bilateral intake layout at head, taking a solid rocket ramjet used in ground connected pipe test as the object of study, the influence of air-inlet exit form and the mode of gas injection on the mixing combustion flow field of afterburning chamber was simulated respectively. The results showed that the structural style of air-inlet exit had a significant impact on the two times combustion performance of afterburning chamber of this layout scheme. Keeping the structure of the air-inlet outlet unchanged, the two times combustion performance could be improved through reasonable configuration of primary gas injection mode.

Key words： solid rocket ramjet; afterburning chamber; mixing combustion; relative specific impulse; numerical simulation

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参考文献

[1]
王同辉, 白涛涛, 莫展,等. 特型燃气喷口对补燃室掺混燃烧的影响[J]. 弹箭与制导学报, 2015, 35(2):97-400.
[2]
单睿子, 曹军伟, 莫展,等. 基于试验设计的固体火箭冲压发动机燃烧效率规律研究[J]. 航空学报, 2015, 36(9):2859-2868.
[3]
李纲, 何国强, 孙振华,等. 固冲发动机补燃室二次燃烧实验研究[J]. 固体火箭技术, 2007, 30(5):400-403.
[4]
胡建新, 夏智勋, 方丁酉,等. 进气道位置对含硼推进剂固体火箭冲压发动机性能的影响. 推进技术, 2007, 28(1):50-54.
[5]
XIA Zhixun, HU Jianxin, FANG Dingyou, et al. Combustion study of the boron particles in the secondary chamber of ducted rocket: AIAA 2006-4445 [R]. [S.l.:s.n.], 2006.
[6]
VANKA S P, CRAIG R, STULL F D., Mixing, cheimical reaction and flow field development in ducted rockets[J]. Journal of Propulsion and Power, 1986, 2(4):331-338.
[7]
胡建新, 夏智勋, 郭健,等. 空燃比对含硼固冲发动机补燃室燃烧影响[J]. 固体火箭技术,2008,31(2):125-128.
[8]
陈林泉, 毛根旺, 霍东兴,等. 燃气喷射方式对冲压发动机补燃室掺混效果的影响[J]. 固体火箭技术, 2005,28(1):40-43.
[9]
赵春宇, 李斌, 鞠玉涛. 环向进气固体火箭冲压发动机补燃室流场数值模拟[J]. 弹箭与制导学报,2008,28(2):136-138.
[10]
王希亮, 孙振华, 马高建,等. 头部两侧进气固冲发动机补燃室内流场研究[J]. 航空兵器,2011(5):51-55.
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