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  

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

作　　者：刘仔 李叙华 王立武 陈林泉 LIU Zai;LI Xuhua;WANG Liwu;CHEN Linquan(The Fourth Academy of China Aerospace Science and Technology Corporation,Xi’an 710025,China)

机构地区：[1]中国航天科技集团有限公司第四研究院,西安710025

出　　处：《弹箭与制导学报》2022年第5期98-101,共4页Journal of Projectiles,Rockets,Missiles and Guidance

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。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.

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 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]