PDF(544 KB)
Study on High Power All-Electric Propulsion System for Spacecraft Orbit Transfer
- TANG Zhangyang1,2, ZHOU Cheng1,2, HAN Dong1,2, MA Xue1,2, CHEN Tao1,2
Author information
+
1. BeijingInstitute of Control Engineering，Beijing 100190，China;
2. Beijing Engineering Center of Green High-efficience Space Propulsion，Beijing 100190，China
Show less
History
+
| Received |
Revised |
| 01 Feb 2018 |
03 Jun 2018 |
| Issue Date |
|
| 20 May 2022 |
|
Compared with chemical propulsion，the application electric propulsion system in spacecraft can save the amount of propellant，which is able to significantly reduce the launch mass or allow more payloads to the target. In this paper，the research on high power electric thrusters in the world is investigated. An electric propulsion systemis designed for the near-earth spacecraft orbit transfer. Several schemes are compared with different thruster performances. At last，the suggestions are proposed for developing high power electric thruster and propulsion system in China.
{{custom_sec.title}}
{{custom_sec.title}}
{{custom_sec.content}}
This is a preview of subscription content, contact
us for subscripton.
References
[1] HERMAN D A. Performance evaluation of the prototype-model next ion thruster[C]//43rdAIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Cincinnati，OH：AIAA，2007.
[2] POLK J，DAN G，SYNDER J，et al. Performance and wear test results for a 20 kW-class ion engine with Carbon-Carbon grids[C]//41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Tucson，AZ，USA：AIAA，2005.
[3] COLETTI M，STEPHEN B G. Numerical investigate of a dual stage variable isp ion engine[C]//32nd International Electric Propulsion Conference.Wiesbaden，Germany：IEPC，2011.
[4] 张天平,张雪儿. 空间电推进技术及应用新进展[J]. 真空与低温,2013,19(4):187-194
ZHANG T P,ZHANG X E. Electric propulsion progress in technologies and applications[J]. Vacuum and Cryogenics,2013,19(4):187-194
[5] TESTOEDOV N A，YAKIMOV E N，ERMOSHKIN Y M，et al. Overview of electric propulsion activity in Russia[C]//30th International Electric Propulsion Conference.Florence，Italy：[s. n.]，2007.
[6] JOHN B M，EDWARD J. Characteristics of the T-220 HT Hall effect thruster[C]//47thAIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Huntsville Alabama：AIAA，2003.
[7] ZURBACH S，CORNU N，LASGORCEIX P. Performance evaluation of a 20 kW Hall effect thruster[C]//The 32nd International Electric Propulsion Conferece.Wiesbaden，Germany：IEPC，2011.
[8] LEPORINI A，GIANNETTI V，ANDREUSSI T，et al. Development of a 20 kW-class Hall effect thruster[C]// Space Pripulsion 2016.ROME，ITALY：[s. n.]，2016.
[9] LAPOINTE M，STRZEMPKOWSKI E，PENCIL E. High power MPD thruster performance measurements[R]. [S. l.]：AIAA，2004.
[10] KODYS A D，CHOUEIRI E Y. A Critical review of the state-of-the-art in the performance of applied-field magnetoplasmadynamic thrusters[R]. [S. l.]：AIAA，2005.
[11] HERDRICH G,BAUDER U,BOXBERGE A,et al. Advanced plasma(propulsion)concepts at IRS[J]. Vacuum,2013,88:36-41
[12] HERDRICH G，BOXBERGER A，PETKOW D，et al. Advanced scaling law for AF MPD thrusters[C]//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.[S. l.]：AIAA，2010.
[13] LONGMIER B，SQUIRE J，GLOVER T，et al. Performance measurements and technology demonstration of the VASIMR VX-200[C]// AIAA SPACE 2010 Conference & Exposition（AIAA-2010-8669）.[S. l.]：AIAA，2010.
[14] SQUIRE J P，CARTER M，DIAZ F C，et al. Development toward a spaceflight capable VASIMR engine and SEP applications[C]//AIAA SPACE 2014 Conference and Exposition（AIAA 2014-4173）.[S. l.]：AIAA，2014.
[15] ELLIOTT F W，FOSTER J E，PATTERSON M J. An overview of the high power electric propulsion（HiPEP）project[C]//40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Fort lauderdale，FL，USA：AIAA，2004.
[16] BROWN D L，BEAL B E，HAAS J M. Air force research laboratory high power electric propulsion technology development[C]//2010 IEEE Aerospace Conference. Big Sky，MT：IEEE，2010.
AI Summary
