|Table of Contents|

Magnetic field design and experimental verification of magnetic shielded Hall thruster(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2019年05期
Page:
59-65
Research Field:
研究与设计
Publishing date:

Info

Title:
Magnetic field design and experimental verification of magnetic shielded Hall thruster
Author(s):
XU Yanan1;  KANG Xiaolu1; 2;  YU Shuilin1; 2;  HUANG Hao1; 2
(1.Shanghai Institute of Space Propulsion, Shanghai 201112, China; 2.Shanghai Space Engine Engineering Research Center, Shanghai 201112, China)
Keywords:
magnetic shielding;  magnetic field design;  wall corrosion
PACS:
V439
DOI:
-
Abstract:
Magnetic shielding can effectively reduce the erosion of plasma on the wall of Hall thruster discharge chamber.It is an effective way to prolong the life of the thruster, which can improve the life of Hall thruster to meet the requirements of long-life space missions.So it has great potential for development.In this paper, the principle of magnetic shielding technology was analyzed, and the magnetic field design and verification experiments were carried out for a 120 mm Hall thruster.A magnetic field configuration with the maximum bending degree of the near-wall magnetic line to the anode and the maximum disjunction with the wall was proposed, which is the configuration whose near-wall magnetic line is the highest isopotential in the experimental prototype.The erosion of the wall of the magnetic shielding configuration was compared with that of traditional configuration after 10 hours of ignition.The former is covered by deposited carbon powder, which shows that magnetic shielding can significantly reduce the ion erosion on the wall of the discharge chamber.The remarkable effect of the magnetic shielding field configuration was verified.Then the performance of the magnetic shielding Hall thruster was preliminarily studied.The optimum efficiency of the thruster is 54.23% at 62sccm anode flow and 300 V discharge voltage, which corresponds to plume state "long cylinder".

References:

[1] 康小录, 杭观荣, 朱智春.霍尔电推进技术的发展与应用[J].火箭推进, 2017, 43(1): 8-17, 37.KANG X L, HANG G R, ZHU Z C.Development and application of Hall electric propulsion technology[J].Journal of Rocket Propulsion, 2017, 43(1): 8-17, 37.
[2] MIKELLIDES I, KATZ I, HOFER R.Design of a laboratory Hall thruster with magnetically shielded channel walls, phase I: numerical simulations[C]//47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011.
[3] HOFER R R, GOEBEL D M, MIKELLIDES I G, et al.Design of a laboratory Hall thruster with magnetically shielded channel walls, phase II: experiments:AIAA 2012-3788 [R].USA: AIAA, 2012.
[4] MIKELLIDES I, KATZ I, HOFER R, et al.Design of alaboratory Hall thruster with magnetically shielded channel walls, phase III: comparison of theory with experiment[C]//48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012.
[5] HOFER R R, CUSSON S E.The H9 magnetically shielded hall thruster: IEPC 2017-232 [R].USA: IEPC, 2017.
[6] CONVERSANO R W, GOEBEL D M, HOFER R R, et al.Development and initial testing of a magnetically shielded miniature Hall thruster[J].IEEE Transactions on Plasma Science, 2015, 43(1): 103-117.
[7] CONVEFRSANO R W, HOFER R R, MIKELLIDES I G, et al.Magnetically shielded miniature Hall thruster: design improvement and performance analysis: IEPC 2015-100 [R].Japan: IEPC, 2015.
[8] CONVERSANO R W, GOEBEL D M, HOFER R R, et al.Performance analysis of a low-power magnetically shielded Hall thruster: experiments[J].Journal of Propulsion and Power, 2017, 33(4): 975-983.
[9] CONVERSANO R W, GOEBEL D M, MIKELLIDES I G, et al.Performance analysis of a low-power magnetically shielded Hall thruster: computational modeling[J].Journal of Propulsion and Power, 2017, 33(4): 992-1001.
[10] CONVEFRSANO R W, DAN M G.Magnetically shielded miniature hall thruster: performance assessment and status update:AIAA 2014-3896[R].USA: AIAA journal, 2014.
[11] HUANG W S, WILLIAMS G J, PETERSON P Y, et al.Plasma plume characterization of the HERMeS during a 1722-hr wear test campaign: IEPC 2017-307 [R].USA: IEPC, 2017.
[12] GILLAND J H, PETERSON P Y.Wear Trends of the HERMeS Thruster as a function of throttlepoint: IEPC 2017-207 [R].USA: IEPC, 2017.
[13] ORTEGA A L, MIKELLIDES I G.Numerical simulations for the assessment of erosion in the 12.5-kW Hall effect rocket with magnetic shielding(HERMeS): IEPC 2017-154 [R].USA: IEPC, 2017.
[14] POLK J E, LOBBIA R, BARRIAULT A, et al.Inner front pole cover erosion in the 12.5 kW HERMeS Hall thruster over a range of operating conditions: EPC 2017-409 [R].USA: IEPC, 2017.
[15] GIANNNETTI V, PIRAGINO A.Development of a 5 kW low-erosion Hall effect hruster: IEPC 2017-379[R].USA: IEPC, 2017.
[16] DUCCI C, MISURI T.Magnetically shielded HT100 experimental campaign: IEPC2017-372 [R].USA: IEPC, 2017.
[17] GRIMAUD L, VAUDOLON J, MAZOUFFRE S, et al.Design and characterization of a 200 W Hall thruster in “magnetic shielding” configuration[C]//52nd AIAA/SAE/ASEE Joint Propulsion Conference.Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016.
[18] 汤海滨, 张广川, 任军学, 等.一种磁场可调的带磁屏蔽效应的低功率霍尔推力器: CN201710438203.2[P].2017-09-15.
[19] 边兴宇.霍尔推力器放电通道壁面分割及磁屏蔽效应研究[D].大连: 大连海事大学, 2018.
[20] 蔡宁泊. 磁聚焦影响霍尔推力器壁面腐蚀的研究[D]. 哈尔滨: 哈尔滨工业大学, 2010.
[21] MOROZOV A I, SAVELYEV V V. Fundamentals of stationary plasma thruster theory [J]. Reviews of Plasma Physics, 2000, 21(2):203-391.
[22] 于达仁. 空间电推进原理[M]. 哈尔滨: 哈尔滨工业大学出版社, 2014.
[23] POLK J E, DUCHEMIN O B, KOEL B E, et al.The effect of carbon deposition on accelerator grid wear rates in ion engine ground testing:AIAA 2000-3662 [R].USA: AIAA journal, 2000.

Memo

Memo:
-
Last Update: 2019-10-25