Performance improvement of the μ10 microwave discharge ion thruster by expansion of the plasma production volume
Performance improvement of the μ10 microwave discharge ion thruster by expansion of the plasma production volume
复制标题
通过扩大等离子体产生量提高μ10微波放电离子推进器的性能
DOI：
10.1016/j.actaastro.2018.12.023
复制
发表时间：
2019
影响因子：
3.5
通讯作者：
谷義隆，月崎竜童，神田大樹，西山和孝，國中均
中科院分区：
文献类型：
--
作者：
安宅未央子;小南裕志;佐藤開;吉村謙一;谷義隆，月崎竜童，神田大樹，西山和孝，國中均
为了提高日本宇宙航空研究开发机构（JAXA）计划用于未来深空探测任务的10 cm级微波放电离子推力器μ10的性能，设计了一种新的放电室，并对其性能进行了测试。在相同的放电功率下，新放电室的最大束流比隼鸟2号探测器原放电室的最大束流高16%。为了研究这种性能改善的原因，多电荷离子的比例在羽流，束流密度分布，和在放电室中的离子电流进行了测量探针。结果发现，在重新设计的配置中的多电荷离子效率和束发散效率没有显着不同的隼鸟2配置。这表明离子束电流的增加增强了推力。此外，还证实了新放电室内的总离子电流高于Hayabusa 2配置。然而，离子提取效率低于Hayabusa 2配置。这表明每单位入射微波功率的总离子电流的增加是性能改善的原因。在重新设计的布局中，推力为12.0 mN，比冲为3122 s，放电损失为162 W/A，在峰值性能点推进效率为39.6%。
To improve the performance of the 10-cm-class microwave discharge ion thruster μ10 for use in future deep space exploration missions planned by the Japan Aerospace Exploration Agency (JAXA), a new discharge chamber was designed, and its performance was tested. The maximum beam current in the new discharge chamber geometry was 16% higher than that in the original geometry, which was used in the Hayabusa 2 space explorer, under the same discharge power. To investigate the reason for this performance improvement, the multi-charged ion ratio in the plume, the beam current density profiles, and the ion current in the discharge chamber were measured by probes. It was found that the multi-charged ion efficiency and the beam divergence efficiency in the redesigned configuration were not significantly different from those in the Hayabusa 2 configuration. This shows that the increase in the ion beam current enhances the thrust. In addition, it was confirmed that the total ion current inside the new discharge chamber is higher than that in the Hayabusa 2 configuration. The ion extraction efficiency, however, was lower than that in the Hayabusa 2 configuration. This suggests that the increase in the total ion current per unit of incident microwave power is the cause of the performance improvement. In the redesigned configuration, the thrust is 12.0 mN, the specific impulse is 3122 s, the discharge loss is 162 W/A, and the propulsion efficiency is 39.6% at the peak performance point.