専門・基盤技術グループ
基本情報
- 所属
- 国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 研究開発員
- 研究者番号
- 90935107
- ORCID ID
https://orcid.org/0000-0002-1056-4841
- J-GLOBAL ID
- 202101017728385182
- researchmap会員ID
- R000026820
経歴
2-
2019年4月 - 現在
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2015年3月 - 2019年3月
学歴
3-
2016年4月 - 2019年3月
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2014年4月 - 2016年3月
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2010年4月 - 2014年3月
論文
10-
宇宙航空研究開発機構研究開発報告: 大気球研究報告 JAXA-RR-23-003 77-104 2024年2月 査読有り
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Journal of Evolving Space Activities 1 n/a 2023年 査読有り筆頭著者This paper reports on our study to develop a magnetic circuit with a discrete outer coil and test its performance in a Hall thruster. The results were compared to those of a Hall thruster on board the Engineering Test Satellite-9 (ETS-9), which used a cylindrical outer coil. At the normalized magnetic field strength of 0.58 for the 6 kW operation using a six poles discrete outer coil, the thrust, discharge current, Isp, thrust-to-power ratio, thrust efficiency, and discharge oscillation were 386.7 mN, 19.0 A, 1890 s, 66.9%, 62.0%, and 13.5% respectively. The Hall thruster with the new magnetic circuit achieved equivalent performance (including discharge stability) to the Hall thruster on board the ETS-9. Further, the study investigated the effect of the number of poles on the performance of the Hall thruster: the performance with the three pole coil was lower than that with the six poles coil. This paper also reports on the effect of pole numbers on utilization efficiency. Mass and current utilization efficiency were more affected by the magnetic field generated by the three poles outer coil.
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26th AIAA Aerodynamic Decelerator Systems Technology Conference 2022年5月16日
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 65(1) 1-10 2022年 査読有り筆頭著者<p>The ion energy angle distribution and its relationship to plasma parameters for spot and plume modes are elucidated for a LaB6 hollow cathode with a radiative heater. Measurements were conducted using a retarding potential analyzer (RPA) and a single Langmuir probe. The ion energy distribution function (IEDF) characteristics showed different tendencies in the current density and mass flow-rate dependence under different plasma modes. The IEDF peak potential for the spot mode varied from 16 to 23 V with increasing current density, and the IEDF peak potential for the plume mode varied from 16 to 32 V with decreasing mass flow rate. Considering angle dependency of ion energy, when the observation angle was changed from the radial direction to the axial direction, the IEDF peak potential increased from 29 to 40 V for the plume mode (10 A, 10 sccm) and increased slightly from 16 to 18 V for the spot mode (20 A, 30 sccm). The probe measurement analysis revealed that the IEDF peak energies are the same as, or exceed, the plasma potential and have a qualitative correlation with the electron temperature spatial distribution.</p>
MISC
33講演・口頭発表等
26-
39th International Electric Propulsion Conference 2025年9月18日
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35th International Symposium on Space Technology and Science 2025年7月16日
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16th International Symposium on Materials in the Space Environment and 14th International Conference on Protection of Materials 2024年10月9日
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International Electric Propulsion Conference 2024 2024年6月26日
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International Symposium on Space Technology and Science 2023年6月6日