Feasibility Study on Performance Enhancement Options for the ECR Ion Thruster µ10
Feasibility Study on Performance Enhancement Options for the ECR Ion Thruster µ10
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ECR 离子推进器 µ10 性能增强选项的可行性研究
DOI：
10.2322/tstj.7.pb_113
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发表时间：
2008
期刊：
影响因子：
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通讯作者：
H. Kuninaka
中科院分区：
文献类型：
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作者：
K. Nishiyama;S. Hosoda;Miyuki Usui;R. Tsukizaki;H. Hayashi;Y. Shimizu;H. Kuninaka
为了适应各种各样的空间飞行，如小型地球同步卫星和深空探测器，正在进行微波放电离子推进器µ10性能增强方案的可行性研究。作者正在考虑以下五种选择：1。较低的插入损耗DC块; 2.不使用圆形波导部分，直接将微波天线插入放电室; 3.优化了原本位于波导深处的气体注入器布局; 4.额外的磁环旨在减少放电室侧壁的离子损失; 5.新的离子光学系统包括一个更薄的屏幕网格和一个更小的加速器网格。不是所有的，但大多数已经在这篇文章中进行了测试和报告。隼鸟小行星探测器的原始模型最大产生8 mN。即使推进剂流量和微波功率增加，也不可能产生更大的推力。事实证明，通过提供更多的流速和/或更多的微波功率，利用上述选项将最大推力增加到10 - 11 mN的范围是可行的。
In order to adapt to a wide variety of the space flights, such as small geosynchronous satellites and deep space explorers, feasibility study of performance enhancement options for the microwave discharge ion thruster µ10 is underway. Authors are considering the following five options: 1. Lower insertion loss DC blocks; 2. Direct monopole antenna insertion to the discharge chamber without using a circular waveguide part; 3. Optimization of gas injector layout which was originally located deep in the waveguide; 4. Additional magnet rings aiming ion loss reduction to the side wall of the discharge chamber; 5. New ion optics consists of a thinner screen grid and a smaller-hole accelerator grid. Not all but most of them have already been tested and reported in this article. The original models for Hayabusa asteroid explorer generated 8 mN at maximum. Larger thrust generation was impossible even if propellant flow rates and microwave powers were increased. It turned out to be feasible to increase the maximum thrust to a range of 10 - 11 mN with above mentioned options by supplying more flow rates and/or more microwave powers.