Work characteristics of low power water propellant pulsed plasma thruster

ZHU Ping; HOU Li-ya; ZHANG Wei-yi

doi:10.3788/OPE.20111910.2402

您当前的位置：

首页 >

文章列表页 >

Work characteristics of low power water propellant pulsed plasma thruster

Article | 更新时间：2020-08-12

- Work characteristics of low power water propellant pulsed plasma thruster
- Optics and Precision Engineering Vol. 19, Issue 10, Pages: 2402-2408(2011)
- 作者机构：
  
  1. 南京理工大学机械工程学院, 江苏南京 210094
  2. 中北大学电子测试技术国防重点实验室, 山西太原 030051
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20111910.2402
  CLC： V228
- Received：27 January 2011，
  
  Revised：18 March 2011，
  
  Published Online：27 October 2011，
  
  Published：25 October 2011
- 稿件说明：
移动端阅览
朱平, 侯丽雅, 章维一. 低功率水工质脉冲等离子体推进器的工作特性[J]. 光学精密工程, 2011,19(10): 2402-2408

ZHU Ping, HOU Li-ya, ZHANG Wei-yi . Work characteristics of low power water propellant pulsed plasma thruster[J]. Editorial Office of Optics and Precision Engineering, 2011,19(10): 2402-2408
朱平, 侯丽雅, 章维一. 低功率水工质脉冲等离子体推进器的工作特性[J]. 光学精密工程, 2011,19(10): 2402-2408 DOI： 10.3788/OPE.20111910.2402.

ZHU Ping, HOU Li-ya, ZHANG Wei-yi . Work characteristics of low power water propellant pulsed plasma thruster[J]. Editorial Office of Optics and Precision Engineering, 2011,19(10): 2402-2408 DOI： 10.3788/OPE.20111910.2402.

摘要

为了解决Teflon脉冲等离子体推进器存在的性能低、有污染等问题

设计了以水为工质的脉冲等离子体推进器系统

并研究了它的主要工作指标的能量阈值。分析了水工质脉冲等离子体推进器系统的放电类型形成条件及原因

通过放电电压和电流测试实验

对工作能量阈值进行了实验研究

得到了稳定运行能量对应的储能电容值。实验结果表明:在足够高的电场强度和足够大的触发电流下

才能产生保证稳定工作触发概率的初始等离子体;而水工质脉冲等离子体推进器的正常工作能量范围由储能决定

与储能电容的容值不相关。研究结果为发展无污染、性能高、具有广适性的低功率水工质脉冲等离子体推进器打下了一定的基础。

Abstract

The paper designs a pulsed plasma thruster system based on water propellant and studies energetic threshold of its main working characteristics to solve the problems of low performance and high pollution of Teflon pulsed plasma thrusters. Based on an analysis of the forming condition and cause of electric discharge types

working energetic threshold is studied experimentally by the discharge voltage and current measurement.The study shows that the initial plasma that can provide trigger probability for steady operation and energy storage capacity are obtained only by enough electric-field intensity and trigger current

and the normal working energy range of the water propellant pulsed plasma thruster is decided by stored energies but not related to capacity values. The study provides a possibility for developing low power water propellant pulsed plasma thrusters of free pollution

high performance and wide applications.

关键词

Keywords

references

尤政, 张高飞, 林杨等. MEMS固体化学推进器设计与建模研究[J]. 光学精密工程, 2005,13(2):117-126. YOU ZH, ZHANG G F, LIN Y,et al.. Design and modeling of MEMS-based solid propellant propulsion[J]. Opt. Precision Eng., 2005, 13(2):117-126.(in Chinese)[2] 戴路, 金光, 陈涛. 基于VSCMG的卫星姿态控制仿真系统研究[J]. 光学精密工程, 2008, 16(8):1546-1553. DAI L, JIN G, CHEN T. Satellite attitude control simulation test bed based on VSCMG[J]. Opt. Precision Eng., 2008,16(8):1546-1553.(in Chinese)[3] CHRISTOPHER D R, MARK E C, MATTICK A T. Pulsed plasma thruster system for microsatellites[J]. J Spac Rock, 2005, 42(1):161-170.[4] 尹乐, 周进, 缪万波,等. 脉冲等离子体推力器放电波形设计评估仿真研究[J]. 推进技术, 2010, 31(4):490-495. YIN L, ZHOU J, MIAO W B. Design and simulation of the discharge current wave for pulsed plasma thruster[J]. J Propul Tech, 2010, 31(4):490-495.(in Chinese)[5] JUNJI U, JUNPEI I, YUKIYA K, et al.. Study on pulsed plasma thruster configuration to expand impulse bit range . 29th International Electric Propulsion Conference, IEPC,2005:234.[6] SCHONHERR T, KOMURASAKI K. Evaluation of discharge behavior of the pulsed plasma thruster SIMP-LEX . AIAA,2010:6530.[7] SPANJERS G G, LOTSPEICH J S, MCFALL K A, et al.. Propellant losses because of particulate emission in a pulsed plasma thruster[J]. J Propul P,1998,14(4):554-559.[8] MARKUSIC T E, KURT A P, CHOUEIRI E Y, et al.. Ablative z-pinch pulsed plasma thruster[J]. J Propul P, 2005, 21(3):392-405.[9] DE ALESSANDRO R O, BRITO H, GALIAN E S. P4S-1 solid propellant pulsed plasma thruster development phase . AIAA,2009:5281.[10] ARRINGTON L A, HAAG T W, PENCIL E J, et al.. A performance comparison of pulsed plasma thruster electrode configurations . 25th International Electric Propulsion Conference, IEPC,1997:127.[11] KUANG Y Z. Effects of propellant geometry on PPT performance . 17th International Electric Propulsion Conference. IEPC,1984:685-690.[12] HIROYUKI K, KAKAMI A, FURUTA Y, et al.. Liquid propellant pulsed plasma thruster . 28th International Electric Propulsion Conference, IEPC, 2003:087.[13] ZHU P, HOU L Y, ZHANG W Y. The effect of easily ionized elements Na and K on the performance of pulsed plasma thruster using water propellant[J]. Science China Tech. Sci., 2010, 53(10):2878-2882.[14] ZHU P, HOU L Y, ZHANG W Y. The measurement on micro-jet impulse based on laser interferometer[J]. 2009 ASME Fluids Engineering Division Summer Meeting and Exhibition, FEDSM,2009,78030(1):1707-1714.

Views

632

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

No data

Related Author

No data

Related Institution

No data

AI问答

Address：No.3888 Dong Nanhu Road, Changchun, Jilin, China Postal code：130033
Tel：0431-86176855 Email：gxjmgc@ciomp.ac.cn
Technical support is provided by Beijing Founder electronics co., LTD 吉ICP备11002662号-17 京公网安备11010802024621
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰