火箭推进

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.

引言
1 实验系统与方法
2 结果与讨论
3 结论

图1 实验系统示意图
Fig.1 Experimental setup

图2 可光学观测模型发动机<br/>Fig.2 Optically observable model thruster

图2 可光学观测模型发动机
Fig.2 Optically observable model thruster

图3 各个流量下的点火燃烧过程<br/>Fig.3 Combustion process at various flow rates

图3 各个流量下的点火燃烧过程
Fig.3 Combustion process at various flow rates

图4 各个流量下的温度压强曲线图<br/>Fig.4 Temperature and pressure curves at various flow rates

图4 各个流量下的温度压强曲线图
Fig.4 Temperature and pressure curves at various flow rates

图5 各个流量下烟气分析结果<br/>Fig.5 Gas analysis results at various flow rates

图5 各个流量下烟气分析结果
Fig.5 Gas analysis results at various flow rates

[1] ROVEY J L,LYNE C T,MUNDAHL A J,et al.Review of multimode space propulsion[J].Progress in Aerospace Sciences,2020,118:100627.
[2] ZHANG Q H,SHREEVE J M.Energetic ionic liquids as explosives and propellant fuels:A new journey of ionic liquid chemistry[J].Chemical Reviews,2014,114(20):10527-10574.
[3] 邓友全.离子液体:性质、制备与应用[M].北京:中国石化出版社,2006.
[4] DONIUS B,ROVEY J.Analysis and prediction of dual-mode chemical and electric ionic liquid propulsion performance[C]//48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.Reston,Virginia:AIAA,2010.
[5] SUTTON G P,BIBLARZ O.Rocket propulsion elements[M].New York:John Wiley & Sons,Inc,2016.
[6] LARRIBA C,GAROZ D,BUENO C,et al.Taylor cones of ionic liquids as ion sources：The role of electrical conductivity and surface tension[EB/OL].https://www.researchgate.net/publication/235978373_Taylor_Cones_of_Ionic_Liquids_as_Ion_Sources_The_Role_of_Electrical_Conductivity_and_Surface_Tension,2007.
[7] BERG S,ROVEY J.Dual-mode propellant properties and performance analysis of energetic ionic liquids[C]//50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition.Reston,Virginia:AIAA,2012.
[8] BERG S P,ROVEY J.Ignition evaluation of monopropellant blends of HAN and imidazole-based ionic liquid fuels[C]//50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition.Reston,Virginia:AIAA,2012.
[9] BERG S P,ROVEY J,PRINCE B,et al.Electrospray of an energetic ionic liquid monopropellant for multi-mode micropropulsion applications[C]//51st AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2015.
[10] BERG S P,ROVEY J.Decomposition of a double salt ionic liquid monopropellant on heated metallic surfaces[C]//52nd AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2016.
[11] MUNDAHL A,BERG S P,ROVEY J.Linear burn rates of monopropellants for multi-mode micropropulsion[C]//52nd AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2016.
[12] BERG S P,ROVEY J.Decomposition of a double salt ionic liquid monopropellant in a microtube for multi-mode micropropulsion applications[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2017.
[13] BERG S P,GLASCOCK M S,COOPER M,et al.Multimode integrated monopropellant electrospray thruster testing results:Chemical mode[C]//NASA In-Space Chemical Propulsion Technical Interchange Meeting.Washington D C:NASA,2020.
[14] LYNE C T,ROVEY J,BERG S P.Monopropellant-electrospray multimode thruster testing results:Electrospray mode[C]//AIAA Propulsion and Energy 2021 Forum.Reston,Virginia:AIAA,2021.
[15] SHARMA A,ADDUCCI A C,ROVEY J,et al.Green ionic liquid multimode monopropellant based chemical micro-thruster[C]//AIAA SCITECH 2022 Forum.Reston,Virginia:AIAA,2022.
[16] 王文涛,马智勇,丛伟民,等.一种多任务模式离子液体推进剂的制备、表征及催化分解研究[J].推进技术,2020,41(2):455-460.
[17] 韩泉东,洪鑫,周海清.空间推进技术需求与发展分析[J].火箭推进,2012,38(2):9-15.
[18] 高鹤,李少龙,严浩,等.双模式离子液体推进剂的分解特性与热试车实验研究[J].空间控制技术与应用,2021,47(4):41-47.
[19] LI S L,YAN H,WANG Z,et al.Catalytic decomposition and burning of a dual-mode ionic liquid propellant[J].Energy & Fuels,2021,35(22):18716-18725.
[20] 高鹤.离子液体推进剂燃烧特性与催化效率提升研究[D].北京:中国空间技术研究院,2021.

备注

引言

1 实验系统与方法

2 结果与讨论

3 结论

期刊信息