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弹箭与制导学报 >

2014 , Vol. 34 >Issue 4: 122 - 124,161

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2014.04.013

火箭技术

固体冲压发动机补燃室结构参数对掺混燃烧效率的影响

  • 田凌寒 ,
  • 田维平 ,
  • 董新刚 ,
  • 杨玉新
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  • 西安航天动力技术研究所,西安 710025

田凌寒(1988-),男,湖北十堰人,助理工程师,硕士研究生,研究方向:航空宇航推进理论与工程。

收稿日期: 2013-11-12

  网络出版日期: 2025-05-30

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Effect of Structural Parameters of Afterburning Chamber on Mixing and Combustion Efficiency for Solid Rocket Ramjet

  • TIAN Linghan ,
  • TIAN Weiping ,
  • DONG Xingang ,
  • YANG Yuxin
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  • Xi'an Institute of Aerospace Propulsion Technology, Xi'an 710025, China

Received date: 2013-11-12

  Online published: 2025-05-30

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摘要

以双下侧进气道式固体火箭冲压发动机为研究对象,建立三维补燃室内流场数值模型,采用正交试验设计,计算分析3个补燃室结构参数对二次燃烧效率的影响,并结合地面试验验证了数值仿真的可行性。通过极差分析,得到了各结构参数对燃烧效率的影响趋势以及最优水平搭配。经过方差分析,得出各个结构参数对燃烧效率影响的显著性,其中补燃室长度的影响是高度显著的。

关键词： 固冲发动机; 正交试验设计; 结构参数; 燃烧效率

本文引用格式

田凌寒 , 田维平 , 董新刚 , 杨玉新 . 固体冲压发动机补燃室结构参数对掺混燃烧效率的影响[J]. 弹箭与制导学报, 2014 , 34(4) : 122 -124,161 . DOI: 10.15892/j.cnki.djzdxb.2014.04.013

Abstract

Solid propellant ramjet with dual underside inlet was selected for study. By using orthogonal design, a three-dimensional flow field model of afterburning chamber was build to study the effect trends of three structural parameters on the mixing and combustion efficiency. The feasibility of numerical simulation was also verified by ground tests. The results got from range analysis indicate the effect trends and optimal levels of each structural parameter, while the variance analysis indicates the influence significance of various structural parameters on combustion efficiency. As a result, the length of the afterburning chamber is highly significant.

Key words： solid rocket ramjet; orthogonal design; structural parameters; combustion efficiency

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