Profile Information
- Affiliation
- Research and Development Staff, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
- Researcher number
- 90935107
- ORCID ID
https://orcid.org/0000-0002-1056-4841
- J-GLOBAL ID
- 202101017728385182
- researchmap Member ID
- R000026820
Research Areas
3Research History
2Education
3Papers
10-
JAXA-RR-23-003 77-104, Feb, 2024 Peer-reviewed
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Journal of Evolving Space Activities, 1 n/a, 2023 Peer-reviewedLead authorThis 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, May 16, 2022
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JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 70(6) 234-241, 2022The drifting trajectory analysis of the reentry recovery module RATS with inflatable deployable aeroshell is validated with the drifting trajectory based on the flight experiment data. The RTOFS sea surface current forecast data and the GFS ocean wind forecast data, released from NCEP, are employed in the drifting trajectory analysis. It is shown that the RATS can float for a long time, although the inflatable ring is filled with CO2 gas, which has large gas permeability of the gas-tight layer. The leeway coefficient for drifting trajectory analysis is estimated to be 0.038 based on the floating design of the RATS. The drifting trajectory analysis was performed using the RATS landing point as the initial position. It was confirmed that the predicted drift direction agrees with the RATS drifting trajectory. However, the difference between the predicted result and the drifting trajectory increases with time in the ocean wind direction. The difference is approximately 0.8 km after 100 minutes from splashdown.
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 65(1) 1-10, 2022 Peer-reviewedLead author<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.
32-
Proceedings of Sounding Rocket Symposium 2023, Feb, 2024
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Balloon Symposium: 2023, Oct 1, 2023
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宇宙科学技術連合講演会講演集(CD-ROM), 67th, 2023
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宇宙科学技術連合講演会講演集(CD-ROM), 67th, 2023
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宇宙科学技術連合講演会講演集(CD-ROM), 67th, 2023
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大気球シンポジウム: 2022年度 = Balloon Symposium: 2022, Nov, 2022大気球シンポジウム 2022年度(2022年11月7-8日. ハイブリッド開催(JAXA相模原キャンパス& オンライン)) Balloon Symposium 2022 (November 7-8, 2022. Hybrid(in-person & online) Conference (Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan 著者人数: 11名 資料番号: SA6000177011 レポート番号: isas22-sbs-011
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観測ロケットシンポジウム2021 講演集 = Proceedings of Sounding Rocket Symposium 2021, Mar, 2022第4回観測ロケットシンポジウム(2022年3月14-15日. ハイブリッド開催(JAXA相模原キャンパス& オンライン)) 4th Sounding Rocket Symposium(March 14-15, 2022. Hybrid(in-person & online) Conference (Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan 著者人数: 15名 資料番号: SA6000175002 レポート番号: Ⅰ-2
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宇宙科学技術連合講演会講演集(CD-ROM), 66th, 2022
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宇宙科学技術連合講演会講演集(CD-ROM), 66th, 2022
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宇宙科学技術連合講演会講演集(CD-ROM), 65th, 2021
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宇宙科学技術連合講演会講演集(CD-ROM), 65th, 2021
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宇宙科学技術連合講演会講演集(CD-ROM), 64th, 2020
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宇宙科学技術連合講演会講演集(CD-ROM), 64th, 2020
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プラズマプロセシング研究会プロシーディングス(CD-ROM), 37th, 2019
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宇宙科学技術連合講演会講演集(CD-ROM), 63rd, 2019
Presentations
24-
16th International Symposium on Materials in the Space Environment and 14th International Conference on Protection of Materials, Oct 9, 2024
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International Electric Propulsion Conference 2024, Jun 26, 2024
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International Symposium on Space Technology and Science, Jun 6, 2023
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International Electric Propulsion Conference 2022, Jun 20, 2022
Professional Memberships
2-
Nov, 2021 - Present
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Aug, 2021 - Present