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弹箭与制导学报 >

2022 , Vol. 42 >Issue 5: 98 - 101

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2022.05.018

飞行高度对头部进气固体火箭超燃冲压发动机燃烧性能的影响

  • 刘仔 ,
  • 李叙华 ,
  • 王立武 ,
  • 陈林泉
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  • 中国航天科技集团有限公司第四研究院,西安 710025

刘仔(1991—),男,四川广安人,工程师,博士研究生,研究方向:固体发动机总体设计。

收稿日期: 2022-03-31

  网络出版日期: 2025-01-16

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Effect of Flight Altitude on Combustion Performance of Nose Fuel-inlet Model Solid-fuel Rocket Scramjet

  • LIU Zai ,
  • LI Xuhua ,
  • WANG Liwu ,
  • CHEN Linquan
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  • The Fourth Academy of China Aerospace Science and Technology Corporation, Xi’an 710025, China

Received date: 2022-03-31

  Online published: 2025-01-16

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摘要

基于头部进气固体火箭超燃冲压发动机工作特点,以高度25 km、飞行速度Ma 6作为设计状态,对头部进气固体火箭超燃冲压发动机各部件进行了初步设计。采用数值模拟方法,研究了不同飞行高度下头部进气固体火箭超燃冲压发动机补燃室燃烧性能的变化规律。研究结果表明,随着飞行高度的增大,化学反应速率整体降低,燃烧效率逐渐下降,引起补燃室推力及比冲增益减小。

关键词： 头部进气; 固体火箭超燃冲压发动机; 数值模拟; 燃烧性能

本文引用格式

刘仔 , 李叙华 , 王立武 , 陈林泉 . 飞行高度对头部进气固体火箭超燃冲压发动机燃烧性能的影响[J]. 弹箭与制导学报, 2022 , 42(5) : 98 -101 . DOI: 10.15892/j.cnki.djzdxb.2022.05.018

Abstract

Based on the characteristics of nose fuel-inlet model solid-fuel rocket scramjet, various components are designed preliminarily under the condition of free stream Ma 6 and flight altitude of 25 km. Numerical simulations are performed to analyze the performance variation law of the second combustor under different flight altitude. The results show that with the flight altitude increasing, the chemical reaction rate and combustion efficiency decreases gradually, which resulted in the decrease of thrust and specific impulse gain of the secondary combustion chamber.

Key words： nose fuel-inlet model; solid-fuel rocket scramjet; numerical simulations; combustion performance

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