摘要
针对双模式离子液体推进剂在真空环境下的化学推进模式展开实验研究。制作了可光学观测模型发动机,搭建了真空舱实验平台,然后采用高速相机、热电偶结合压力传感器以及烟气分析仪等测量方法,研究了1~4 mL/min流量工况下推进剂在模型发动机中的催化点火特性,对其着火和燃烧过程有了直观深入的认识,分析了过程中催化床不同深度位置的温度变化和真空舱内的压强变化,同时得到了主要生成气体产物的组分及其相应的浓度值变化情况,这对于深化双模式离子液体推进剂化学推进工作模式下物理机理的理解具有重要意义。
An experimental study on the chemical propulsion mode of dual-mode ionic liquid propellant in vacuum environment was carried out.An optically observable model thruster was produced,and a vacuum chamber experimental platform was built.Then,by using the measurement methods such as the high-speed camera,the thermocouple combined with pressure sensor,the gas analyzer and so on,the catalytic ignition characteristics of the propellant in the model thruster at the flow rates from 1 mL/min to 4 mL/min were studied.It has an intuitive and in-depth understanding on the propellant’s ignition and combustion process.During the process,the temperature changes at different depths of the catalytic bed and the pressure changes in the vacuum chamber were analyzed,and the components of the main gaseous products and their corresponding concentration changes were obtained.These are of great significance for figuring out the physical mechanism under the chemical propulsion working mode of dual-mode ionic liquid propellants.
作者
方杰
王尊
严浩
高鹤
姚兆普
李水清
FANG Jie;WANG Zun;YAN Hao;GAO He;YAO Zhaopu;LI Shuiqing(Beijing Institute of Control Engineering,Beijing 100190,China;Beijing Engineering Research Center of Efficient and Green Aerospace Propulsion Technology,Beijing 100190,China;Department of Energy and Power Engineering,Tsinghua University,Beijing 100084,China)
出处
《火箭推进》
CAS
2022年第5期1-8,共8页
Journal of Rocket Propulsion
基金
国家特殊支持计划青年拔尖人才项目。
关键词
双模式推进
离子液体
推进剂
催化点火
化学推进
dual mode propulsion
ionic liquid
propellant
catalytic ignition
chemical propulsion
