LHT-100自励磁霍尔推力器热特性测试和热真空实验研究

推进技术 ›› 2016, Vol. 37 ›› Issue (4): 793-800.

• 电推进和其它推进 • 上一篇

LHT-100自励磁霍尔推力器热特性测试和热真空实验研究

田立成,高俊,李兴坤,郭宁,顾左,张天平

兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000

发布日期:2021-08-15
作者简介:田立成，男，硕士，工程师，研究领域为等离子体浸没离子注入材料改性研究、离子电推进和霍尔电推进等空间特种推进理论与实验技术研究、航天器充放电理论与实验技术研究等。
基金资助:
重点实验室基金(9140C5504041001)。

Experimental Study of Thermal Characteristics and Thermal Vacuum of LHT-100 Self-Excited Hall Thruster

Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China and Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China

Published:2021-08-15

摘要/Abstract

摘要： 为了验证LHT-100自励磁霍尔推力器工作状态的热特性和空间环境适应性，对霍尔推力器进行了工作状态热特性测试和热真空实验研究，给出了LHT-100霍尔推力器在工作状态下关键部位的温度升高和自然降温规律，分析了自励磁霍尔推力器在常温下启动达到热平衡过程中的推力、比冲、放电损耗等随时间的变化规律，并在带过渡板情况下开展了霍尔推力器的热真空环境实验。实验结果表明:LHT-100自励磁霍尔推力器在工作近3.5h内达到热平衡，关机5h后霍尔推力器整体温度自然降至室温，在常温下启动达到热平衡过程中霍尔推力器的放电电流、推力、比冲、放电损耗等指标在正常范围内，霍尔推力器在热真空环境中启动和工作正常，霍尔推力器零部件及其材料对高低温变化环境的稳定性和适应性较好，能够适应高低温变化的环境影响。

关键词: LHT-100自励磁霍尔推力器；热特性；热真空；实验研究

Abstract: In order to verify the thermal characteristics and space atmosphere adaptability of LHT-100 self-excited Hall thruster，thermal test and thermal vacuum experiment were carried out. The temperature of key parts and natural cooling process of LHT-100 Hall thruster were presented. The law of thrust，specific impulse，discharge loss versus time of LHT-100 Hall thruster is analyzed when it starts up and reaches thermal equilibrium at room temperature. The thermal vacuum experiment of Hall thruster with transition plate was carried out. The experiment results show that LHT-100 self-excited Hall thruster reaches thermal equilibrium at work in near 3.5 hour，and after 5 hour when the LHT-100 Hall thruster turns off，the overall temperature can reach room temperature. The discharge current，thrust，specific impulse，discharge loss can be in appropriate range. The Hall thruster can work normally in both the high and low temperature environment. It has better stability and adaptability in both the high and low temperature environment. It also can be able to adapt to the environment impact of the high and low temperature variation.

Key words: LHT-100 self-excited Hall thruster；Thermal characteristics；Thermal vacuum；Experimental study

田立成,高俊,李兴坤,郭宁,顾左,张天平. LHT-100自励磁霍尔推力器热特性测试和热真空实验研究[J]. 推进技术, 2016, 37(4): 793-800.

TIAN Li-cheng,GAO Jun,LI Xing-kun,GUO Ning,GU Zuo,ZHANG Tian-ping. Experimental Study of Thermal Characteristics and Thermal Vacuum of LHT-100 Self-Excited Hall Thruster[J]. Journal of Propulsion Technology, 2016, 37(4): 793-800.

参考文献

[1] Manzella D, Jankovsky R, Elliott F, et al. Hall Thruster Plume Measurements on-Board the Russian Express Satellites[R]. NASA/TM-2001-211217.
[2] Sitnikova N, Volkov D, Maximov I, et al. Hall Effect Thruster Interactions Data from the Russian Express-A2 and Express-A3 Satellites[R]. NASA/CR-2003-212005.
[3] 张天平, 唐福俊, 田华兵, 等. 电推进航天器的特殊环境及其影响[J]. 航天器环境工程, 2007, 24(2):88-94.
[4] 张郁. 电推进技术的研究应用现状及其发展趋势[J]. 火箭推进, 2005, 31(2): 27-36.
[5] Colbert TS, Day M, Fischer G, et al. Plan and Status of the Development and Qualification Program for Stationary Plasma Thruster[C]. Monterey: Joint Propulsion Conference and Exhibit, 1993.
[6] 田立成, 龙建飞, 郭宁, 等. 卫星敏感区域霍尔推力器束流沉积污染模型[J]. 真空科学与技术学报, 2013, 33(9): 883-887.
[7] 田立成, 郭宁, 龙建飞, 等. LHT-100霍尔推力器宽功率范围工作实验研究[J]. 推进技术, 2014, 35(9): 1283-1289. (TIAN Li-cheng, GUO Ning, LONG Jian-fei, et al. Experimental Study of LHT-100 Hall Thruster Operation in the Wide Power Range[J]. Journal of Propulsion Technology, 2014, 35(9): 1283-1289.)
[8] Walker R M L, Gallimore A D. Hall Thruster Cluster Operation with a Shared Cathode[J]. Journal of Propulsion and Power, 2007, 23(3): 528-536.
[9] Linnell J A, Gallimore A D. Efficiency Analysis of a Hall Thruster Operating with Krypton and Xenon[J]. Journal of Propulsion and Power, 2006, 22(6): 1402-1418.
[10] Book C F, Walker R M L. Effect of Anode Temperature on Hall Thruster Performance[J]. Journal of Propulsion and Power, 2010, 26(5): 1036-1044.
[11] Ross J L, Sommerville J D, King L B. Energy-Loss Mechanisms of a Low-Discharge-Voltage Hall Thruster[J]. Journal of Propulsion and Power, 2010, 26(6): 1312-1317.
[12] 韩轲, 江滨浩, 纪延超. 霍尔效应推力器放电双稳态机理研究[J]. 物理学报, 2012, 61(7).
[13] Morozov A I, Savelyev V V. Fundamentals of Stationary Plasma Thruster Theory[M]. Springer US: Reviews of Plasma Physics, 2000.
[14] Hruby V, Pote B, Gamero-[Castano] M, et al. Hall Thrusters Operating in Pulsed Mode[C]. Pasadena California: 27th International Electric Propulsion Conference, 2001.
[15] Gray H, Provost S, Glogowski M, et al. Inmarsat 4F1 Plasma Propulsion System Initial Flight Operations[C]. Princeton: 29th International Electric Propulsion Conference, 2005.
[16] Arhipov B A , Krochak L Z, Kudriavcev S S, et al. Investigation of the Stationary Plasma Thruster (SPT-100) - Characteristics and Thermal Maps at the Raised Discharge Power[R]. AIAA 98-3791.
[17] Day M, Maslennikov N, Randolph T, et al. SPT-100 Subsystem Qualification Status[R]. AIAA 96-2713.
[18] Lyszyk M, Klinger E, Secheresse O, et al. PPS 1350 Plasma Thruster Qualification Status[C]. Amsterdam Netherlands: 50th International Astronautical Congress, 1999.
[19] Garner C E, Brophy J R, Polk J E, et al. Experimental Evaluation of Russian Anode Layer Thrusters[R]. AIAA 94-3010.
[20] Brophy J R, Barnett J W, Sankovic J M, et al. Performance of the Stationary Plasma Thruster: SPT-100[R]. AIAA 92-3155.
[21] Sang-Wook Kim, Alcc D Gallimorc. Plume Study of a 1.35kW SPT-100 Using an E×B Probe[R]. AIAA 99-2423.
[22] King L B, Gallimore A D. Mass Spectral Measurements in the Plume of a SPT-100 Hall Thruster[J]. Journal of Propulsion and Power, 2000, 16(6): 1086-1092.
[23] Kim V. Main Physical Features and Processes Determining the Performance of Stationary Plasma Thrusters[J]. Journal of Propulsion and Power, 1998, 14(5): 736-743.
[24] Morozov A I, Savelyev V V. Fundamentals of Stationary Plasma Thruster Theory[M]. Springer US: Reviews of Plasma Physics, 2000.　　　　　　　　　　　　　*　收稿日期:2014-11-16；修订日期:2015-01-07。基金项目:重点实验室基金(9140C5504041001)。作者简介:田立成,男,硕士,工程师,研究领域为等离子体浸没离子注入材料改性研究、离子电推进和霍尔电推进等空间特种推进理论与实验技术研究、航天器充放电理论与实验技术研究等。E-mail: tlc1676@163.com(编辑:梅瑛)

LHT-100自励磁霍尔推力器热特性测试和热真空实验研究

Experimental Study of Thermal Characteristics and Thermal Vacuum of LHT-100 Self-Excited Hall Thruster

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