10微克级液体脉冲等离子体推力器供给系统研究

推进技术 ›› 2017, Vol. 38 ›› Issue (7): 1648-1653.

10微克级液体脉冲等离子体推力器供给系统研究

王司宇,刘向阳,谢侃,武志文,成跃,王宁飞

北京理工大学宇航学院，北京 100081,北京理工大学宇航学院，北京 100081,北京理工大学宇航学院，北京 100081,北京理工大学宇航学院，北京 100081,北京理工大学宇航学院，北京 100081,北京理工大学宇航学院，北京 100081

发布日期:2021-08-15
作者简介:王司宇，男，博士生，研究领域为脉冲等离子体推力器仿真与实验。E-mail: liuxy@bit.edu.cn 通讯作者:刘向阳，男，博士，研究领域为固体火箭发动机测试技术，电推进技术。
基金资助:
中国国家留学基金委基金(201406035042)；国家自然科学基金(51576018)。

10 Micrograms Supply System for Liquid Propellant Pulsed Plasma Thruster

School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China,School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China,School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China,School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China,School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China and School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China

Published:2021-08-15

摘要/Abstract

摘要： 用水作为脉冲等离子体推力器(PPT)的推进剂是改进其性能的新思路，可以有效提高比冲、防止滞后烧蚀以及降低污染。但微量推进剂供给系统是实现液体脉冲等离子体推力器(LP-PPT)的前提条件，也是LP-PPT的难点。为此，先介绍了现有的LP-PPT供给方式，并分析各种供给方式的优缺点；以有机材料软木为渗透介质，研制了多段渗透式水推进剂供给系统；在理论分析供给原理的基础上，设计了两套供给量测量方案，并开展了相应的测量实验；将供给系统安装于PPT样机本体，开展了性能测试实验。结果表明三段结构供给系统供给量为21.76μg/s，满足LP-PPT样机的供给量需求。最终获得LP-PPT实验样机元冲量82.998μN·s，比冲194.6s，效率2.47%。

关键词: 电推进；液体脉冲等离子体推力器；供给系统；渗透材料；质量流率

Abstract: Using water as propellant，which could effectively increase the specific impulse，prevent late-time ablation and reduce pollution，was a new technology to improve the performance of pulsed plasma thruster(PPT). As the prerequisite of pushing the liquid propellant pulsed plasma thruster(LP-PPT) into engineering application，the trace propellant supply system was difficult to satisfy the needs of LP-PPT. Therefore，first of all，the existing LP-PPT supply systems were introduced. And their strengths and weaknesses were analyzed. Secondly，the cork，organic material，was used as osmotic media. Subsequently a multi-section infiltration water supply system was developed. Thirdly，based on the theoretical analysis of the supply principle，two sets of measurement plans were designed. And the related experiments were carried out. Finally，combined with the PPT，the performances of LP-PPT were tested. It is found that the mass flow rate of three-section supply system is 21.76μg/s，which is able to meet the requirement of LP-PPT prototype. The performances of LP-PPT is acquired. The impulse bit，specific impulse and efficiency are 82.998μN·s，194.6s and 2.47%，respectively.

Key words: Electric propulsion；Liquid propellant pulsed plasma thruster；Supply system；Penetrant meterial；Mass flow rate

王司宇,刘向阳,谢侃,武志文,成跃,王宁飞. 10微克级液体脉冲等离子体推力器供给系统研究[J]. 推进技术, 2017, 38(7): 1648-1653.

WANG Si-yu,LIU Xiang-yang,XIE Kan,WU Zhi-wen,CHENG Yue,WANG Ning-fei. 10 Micrograms Supply System for Liquid Propellant Pulsed Plasma Thruster[J]. Journal of Propulsion Technology, 2017, 38(7): 1648-1653.

参考文献

[1] 张更新. 现代小卫星及其应用[M]. 北京:人民邮电出版社, 2008.
[2] 余金培, 杨根庆, 梁旭文. 现代小卫星技术与应用[M]. 上海:上海科学普及出版社, 2004.
[3] Burton R L, Turchi P J. Pulsed Plasma Thruster[J]. Journal of Propulsion and Power, 1998, 14(5): 716-735.
[4] Hoskins W A, Rayburn C, Sarmiento C. Pulsed Plasma Thruster Electromagnetic Compatibility: History, Theory, and the Flight Validation on EO-1[R]. AIAA 2013-5016.
[5] Junquan Li. A Highly Miniaturized uPPT Thruster for Attitude Orbit Control[C]. Switzerland: 6th European Cubesat Symposium, 2014.
[6] Mikellides P G. Theoretical Modeling and Optimization of Ablation-Fed Pulsed Plasma Thruster [D]. Columbus: The Ohio State University, 1999.
[7] Abdolrahim R, Tony S. Review of Worldwide Activities in Liquid-Fed Pulsed Plasma Thruster[J]. Journal of Propulsion and Power, 2014, 30(2): 253-264.
[8] 朱平. 水工质脉冲等离子体低功率推进器的设计与研究[D]. 南京:南京理工大学, 2011.
[9] Ziemer J K, Petr R A. Performance of Gas Fed Pulsed Plasma Thrusters Using Water Vapor Propellant[R]. AIAA 2002-4273.
[10] Koizumi H, Furuta Y, Komurasaki K, et al. A Pulsed Plasma Thruster Using Water as the Propellant[R]. AIAA 2004-3460.
[11] Kakami A, Koizumi H, Komurasaki K, et al. Design and Performance of Liquid Propellant Pulsed Plasma Thruster[J]. Vacuum, 2004, 73(3): 419-425.
[12] Koizumi H, Kakami A, Furuta Y, et al. Liquid Propellant Pulsed Plasma Thruster[R]. IEPC-2003-087.
[13] Miyagi K, Kuroki S, Tagawa T, et al. Influence of Electrode Configuration of a Liquid Propellant PPT on its Performance[R]. IEPC-2015-138.
[14] Scharlemann C A, York T M. Pulsed Plasma Thruster Using Water Propellant, Part I: Investigation of Thrust Behavior and Mechanisms[R]. AIAA 2003-5022.
[15] Carsten A S, Thomas M Y. Pulsed Plasma Thruster Using Water Propellant, Part II: Thruster Operation and Performance Evaluation[R]. AIAA 2003-5023.
[16] Simon D H, Land H B, Emhoff J. Micro Pulsed Plasma Thruster Technology Development[R]. AIAA 2004-3622.
[17] Simon D H, Land H B, Emhoff J. Experimental Evaluation of a Micro Liquid Pulsed Plasma Thruster Concept[R]. AIAA 2006-4330.
[18] William Y L Ling, Hiroyuki K, Tony S. Use of Liquid Propellants in Pulsed Plasma Thrusters for Small Satellites[R]. IEPC-2015-139.
[19] 王司宇, 刘向阳, 杨磊, 等. 基于水推进剂的脉冲等离子体推力器数值模拟[J]. 高电压技术, 2013, 39(7): 1680-1686.
[20] 柯林斯, Colins R E, 钟祥, 等. 流体通过多孔材料的流动[M]. 北京:石油工业出版社, 1984.
[21] 肖利杰, 刘向阳, 杨磊, 等. 脉冲等离子体推力器烧蚀建模与仿真[J]. 推进技术, 2011, 32(6):788-793. (XIAO Li-jie, LIU Xiang-yang, YANG Lei, et al. Ablation Modeling and Simulation for Pulsed Plasma Thruster[J]. Journal of Propulsion Technology, 2011, 32(6): 788-793.)
[22] 杨磊, 刘向阳, 陈成权, 等. 脉冲等离子体推力器宏观特性数值研究[J]. 推进技术, 2011, 32(6): 776-780. (YANG Lei, LIU Xiang-yang, CHENG Cheng-quan, et al. Numerical Analysis on Macro-Characteristics of Pulsed Plasma Thruster[J]. Journal of Propulsion Technology, 2011, 32(6): 776-780.)(编辑:张荣莉)　　　　　　　　　　　　　　收稿日期:2016-03-10；修订日期:2016-06-04。基金项目:中国国家留学基金委基金(201406035042)；国家自然科学基金(51576018)。作者简介:王司宇,男,博士生,研究领域为脉冲等离子体推力器仿真与实验。E-mail: liuxy@bit.edu.cn通讯作者:刘向阳,男,博士,研究领域为固体火箭发动机测试技术,电推进技术。E-mail: liuxy@bit.edu.cn