Research, Test and Operation Technology Grp.
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
11-
Journal of Electric Propulsion, 5(1), Feb 10, 2026
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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.
Misc.
33-
Proceedings of Sounding Rocket Symposium 2024, Mar, 2025
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Proceedings of Sounding Rocket Symposium 2023, Feb, 2024
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Balloon Symposium: 2023, Oct 1, 2023
Presentations
26-
39th International Electric Propulsion Conference, Sep 18, 2025
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35th International Symposium on Space Technology and Science, Jul 16, 2025
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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
Professional Memberships
2-
Nov, 2021 - Present
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Aug, 2021 - Present