10 cm考夫曼型离子推力器放电室关键参数优化

胡竟; 耿海; 杨福全; 郭德洲; 王东升; 李建鹏

doi:10.13700/j.bh.1001-5965.2021.0631

10 cm考夫曼型离子推力器放电室关键参数优化

doi: 10.13700/j.bh.1001-5965.2021.0631

胡竟^{1, 2},
耿海^1, ,,
杨福全¹,
郭德洲¹,
王东升¹,
李建鹏¹

1.
兰州空间技术物理研究所真空技术与物理重点实验室，兰州 730000
2.
北京航空航天大学材料科学与工程学院，北京 100191

基金项目: 民用航天预先研究项目(D010509)

详细信息

通讯作者:
E-mail：marine115@126.com

中图分类号: V439+.4
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- 被引次数: 0
出版历程
- 收稿日期: 2021-10-25
- 录用日期: 2021-11-27
- 网络出版日期: 2022-01-12
- 整期出版日期: 2023-08-31

Optimization of discharge chamber key parameters for 10 cm Kaufman xenon ion thruster

1.
Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China
2.
School of Materials Science and Engineering，Beihang University，Beijing 100191，China

Funds: Civil Space Advance Research Project (D010509)

More Information

Corresponding author: E-mail：marine115@126.com

摘要

摘要:
放电室构型设计是离子推力器结构设计的基础与核心，直接影响到放电室工作能效及整机工作寿命。针对新型航天器在轨飞行任务对大推力、长寿命连续变推力离子推力器的应用需求，探究了影响10 cm离子推力器整机效能的放电室关键参数因子，揭示了发散场放电室的磁场发散度、电子通道面积及阴极位置等敏感参数对放电室性能的影响作用关系。开展了10 cm离子推力器放电室参数构型的优化与验证。结果表明：在不改变整机结构的情况下，通过优化放电室关键参数，10 cm离子推力器最大输出推力由20 mN提升至25 mN，提升近25%，推力调节范围由1～20 mN扩展至1～25 mN，全范围内推力分辨率均优于50 μN，且推力器在20 mN最佳工作点的阳极电压由43.5 V降至38.4 V，放电损耗由345 W/A降至308 W/A，预估整机寿命将由15 000 h提升至17 500 h。研究为推动10 cm离子推力器的在轨扩展应用提供了一定的技术支撑。
- 无拖曳飞行 /
- 连续变推力 /
- 离子推力器 /
- 宽范围 /
- 放电室
Abstract:
Discharge chamber configuration is the foundation and core of ion thruster structure design, which directly influences the working efficiency of the discharge chamber and in-orbit lifetime of the thruster. Aiming at the application requirement of new complex aerospace equipment for ion thruster with long-life, high thrust wide-range and continuous variable-thrust, this research explored the key factors of discharge chamber configuration parameters influencing the efficacy of 10 cm ion thruster, as well as the influence of magnetic field divergence, electron channel area and hollow cathode position and other sensitive parameters on discharge chamber performances. Then optimization of parameter configuration and verification of discharge chamber of 10 cm ion thruster were conducted. The results showed that by optimizing discharge chamber key parameters, the maximum thrust of 10 cm ion thruster increased from 20 mN to 25 mN, 25% higher without changing the mechanical structure of the thruster, which extended the thrust adjustment range from 1−20 mN to 1−25 mN, and enhanced the thrust resolution in the whole range to more than 50 μN. Moreover, the anode potential dropped to 38.4 V from 43.5 V, the discharge loss dropped to 308 W/A from 345 W/A, and the estimated lifetime of thruster will be increased from 15000 h to 17500 h. The above research will certainly provide technical support for the extended in-orbit application of 10 cm ion thruster.
- drag-free flight /
- continuous variable-thrust /
- ion thruster /
- wide-range /
- discharge chamber

HTML全文

图 1 10 cm离子推力器工作原理

Figure 1. Working process of 10 cm ion thruster

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图 2 发散场推力器电子通道示意图

Figure 2. Schematic of electronic channel in divergent magnetic field thruster

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图 3 阴极位置调节示意图

Figure 3. Schematic of orifice plate height setting

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图 4 10 cm离子推力器工程样机实物

Figure 4. Prototype of 10 cm ion thruster engineering

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图 5 不同磁场发散度下放电损耗与放电室推进剂利用率之间的关系

Figure 5. Discharge loss versus mass utilization efficiency under different magnetic field divergent

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图 6 不同电子通道面积下阳极电压和放电损耗与励磁电流之间的关系

Figure 6. Anode potential and discharge loss versus magnet current under different electronic channel areas

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图 7 不同阴极位置下励磁电流和阴极流率占比对放电损耗的影响

Figure 7. Magnet current and cathode flowrate versus discharge loss under different orifice plate heights

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图 8 25 mN工作点下连续工作3 h的推力变化

Figure 8. Thrust changes at 25 mN operating point for 3 h continues operation

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图 9 1～25 mN范围内的推力调节变化规律

Figure 9. Thrust regulation and change rule over range 1～25 mN

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图 10 优化前后加速栅工作200 h时的状态对比

Figure 10. Comparison of state of accelerator grid having worked for 200 h before and after optimization

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表 1 放电室关键参数优化前后状态对比

Table 1. Comparison of key parameters of discharge chamber before and after optimization

测试结果	K_d/(°)	S/mm²	h/mm
优化前	65	1435	0
优化后	70	1089	3

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表 2 推力器性能测试对比

Table 2. Comparison of thrust test results

优化改进	阳极电压 /V	阳极电压振荡 /V	阴极电压 /V	阴极电压振荡 /V	推力 /mN	放电损耗 / (W·A⁻¹)	推进剂利用率 /%	功率 /W
优化前	43.5	28	13.2	6	20.10	345	55.7	604
优化后	38.4	10	9.8	5	20.11	308	59.6	584

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