研究者業績
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 助教
- 研究者番号
- 30872444
- ORCID ID
https://orcid.org/0000-0003-1491-1940- J-GLOBAL ID
- 202001000326595612
- researchmap会員ID
- R000000445
研究キーワード
6経歴
4-
2023年8月 - 現在
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2022年12月 - 現在
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2015年10月 - 2022年11月
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2014年4月 - 2015年9月
学歴
3-
2018年9月 - 2021年9月
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2012年4月 - 2014年3月
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2008年4月 - 2012年3月
主要な委員歴
4主要な受賞
17主要な論文
31-
Publications of the Astronomical Society of Japan 77(5) 1080-1089 2025年10月 査読有りAbstract We propose a mission concept, called the space interferometer laboratory voyaging towards innovative applications (SILVIA), designed to demonstrate ultra-precision formation flying between three spacecraft separated by 100 m. SILVIA aims to achieve submicrometer precision in relative distance control by integrating spacecraft sensors, laser interferometry, low-thrust, and low-noise micro-propulsion for real-time measurement and control of distances and relative orientations between spacecraft. A 100 m scale mission in a near-circular low Earth orbit has been identified as an ideal, cost-effective setting for demonstrating SILVIA, as this configuration maintains a good balance between small relative perturbations and low risk of collision. This mission will fill the current technology gap towards future missions, including gravitational wave observatories such as the decihertz interferometer gravitational wave observatory (DECIGO), designed to detect the primordial gravitational-wave background, and high-contrast nulling infrared interferometers such as the large interferometer for exoplanets (LIFE), designed for direct imaging of thermal emissions from nearby terrestrial planet candidates. The mission concept and its key technologies are outlined, paving the way for the next generation of high-precision space-based observatories.
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Acta Astronautica 235 130-140 2025年10月 査読有り筆頭著者責任著者Precise satellite formation flying is a promising technology that enables unprecedented astronomical observations. For comprehensive astronomical missions, preliminary small satellite missions in low Earth orbit (LEO) have been proposed. However, various perturbation sources in LEO can disturb rigid and precise formation control. This study proposes an approach that combines feedforward and feedback controls to attain precise formation flying in LEO. The developed feedforward control can compensate for major gravitational perturbations, predicted from the absolute position and velocity of spacecraft. In addition, the feedback control can address uncertain and unmodeled perturbations. Consequently, the hybrid approach can yield a smaller tracking error than feedback control alone. This novel approach is reliable and robust against environmental uncertainties—including atmospheric density, high-order Earth gravitational potentials, and third-body gravity—and systematic uncertainties—including atmospheric and solar radiation coefficients and thrust errors of spacecraft. Indeed, closed-loop control simulations of a linear astronomical interferometer under such uncertainties reveal a significant reduction in tracking error and feedback controller load using feedforward control, potentially making precise and reliable formation flying in LEO much achievable.
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Journal of Guidance, Control, and Dynamics 48(6) 1298-1313 2025年6月 査読有り筆頭著者責任著者
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Astronomy & Astrophysics 682(A38) 2024年2月 査読有り筆頭著者責任著者
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Journal of Guidance, Control, and Dynamics 46(4) 695-708 2023年4月 査読有り筆頭著者責任著者
主要なMISC
80-
Report prepared for the W. M. Keck Institute for Space Studies (KISS), California Institute of Technology 2025年8月 招待有り
講演・口頭発表等
38-
76th International Atronautical Congress, Sydney, Australia 2025年10月
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76th International Atronautical Congress, Sydney, Australia 2025年9月
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The 11th European Conference for Aerospace Sciences 2025年7月
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The 35th Workshop on JAXA Astrodynamics and Flight Mechanics 2025年7月
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2025 AIAA SciTech Forum, Orlando, The United States 2025年1月
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12th International Workshop on Satellite Constellations and Formation Flying, Kaohsiung, Taiwan 2024年12月
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In the class of "Dynamics and Control of Spacecraft," Politecnico di Torino, Online 2024年12月 招待有りHosted by Prof. Elisa Capello
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12th International Workshop on Satellite Constellations and Formation Flying, Kaohsiung, Taiwan 2024年12月
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16th International Space Conference of Pacific-basin Societies 2024年11月
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16th International Space Conference of Pacific-basin Societies 2024年11月
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Aerospace Engineering Department Seminar, San Diego State University, The United States 2024年11月 招待有りHosted by Prof. Ping Lu
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Seminar, NASA Jet Propulsion Laboratory, Pasadena, The United States 2024年11月 招待有りHosted by Dr. Andrew E. Johnson
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The 75th International Astronautical Congress, Milan, Italy 2024年10月
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The 75th International Astronautical Congress, Milan, Italy 2024年10月
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The 75th International Astronautical Congress, Milan, Italy 2024年10月
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Joint research seminar (among Osaka University, Politecnico di Torino, and ISAS/JAXA), Osaka University 2024年9月
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Optical and Infrared Interferometry and Imaging IX 2024年8月28日 SPIE
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SICE Festival with Annual Conference 2024, Kochi 2024年8月
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The 34th Workshop on JAXA Astrodynamics and Flight Mechanics 2024年7月
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The 2024 European Control Conference, Stockholm 2024年6月
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29th International Symposium on Space Flight Dynamics, Darmstadt, Germany 2024年4月
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In the class of "Applied Control in Astronautics," Purdue University, Online 2024年4月 招待有りHosted by Prof. Ken Oguri
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Seminar, Exoplanets and Habitability Group, ETH Zurich, Switzerland 2024年4月 招待有りHosted by Prof. Sascha P. Quanz
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33rd International Symposium on Space Technology and Science 2022年3月
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11th International ESA Conference on Guidance, Navigation & Control Systems 2021年6月
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Advances in the Astronautical Sciences 2020年
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Proceedings of the International Astronautical Congress, IAC 2019年
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PROMOTE THE PROGRESS OF THE PACIFIC-BASIN REGION THROUGH SPACE INNOVATION 2019年 UNIVELT INCOn February 3, 2018 at the JAXA Uchinoura Space Center, JAXA experimented SS-520 No. 5 launch with a 3U sized cube sat called TRICOM-1R aboard. After liftoff, flight of SS-520 No. 5 proceeded normally. Around 7 minutes 30 seconds into flight, TRICOM-1R separated and was inserted into its target orbit. And the launcher became the world's smallest class satellite launcher. SS-520 launch vehicle is one of sounding rockets operated in JAXA/ISAS, and originally two stage rocket. In this experiment, to make this vehicle put a satellite into orbit, the third stage motor is added. And this sounding rocket has four tail fins for spin stabilization, but usually don't have an attitude control system during the flight. But in this mission, it is needed to control its attitude to ignite second and third motor toward horizontal after first stage bum-out. The gas jet system is installed into between the first stage and the second stage of the vehicle as a unique active attitude control system. The gas jet system can control the spin axis direction and the spin rate of the vehicle during the coasting fight. Because of this constraint, the apogee altitude after the burn out of the first stage motor almost correspond with the perigee altitude of the elliptical orbit. In this mission, the sounding rocket-based Nano launcher is planned to put TRICOM-1R into the elliptical orbit. Its targeted apogee altitude is about 1,800 km and its perigee altitude is about 180 km. Because the perigee altitude is relatively low, the orbit life is very short. One of the mission requirements is to make the vehicle an orbit insertion with more than 30 days orbital lifetime. The vehicle error or the environment error deeply affect the achieved trajectory. These errors must be small enough to put TRICOM-1R into orbit. This paper discusses about the trajectory design on how to manage the sounding rocket into a satellite launching vehicle, the effect of the orbital distribution depending on the various errors, the flight safety analysis, and finally flight performance evaluation.
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SPACEFLIGHT MECHANICS 2019, VOL 168, PTS I-IV 2019年 UNIVELT INCIn order to deeply understand orbital disturbances, the flight data of the PROCYON, which is the 50kg-class interplanetary micro-spacecraft was analyzed. In the telemetry data, we found two unexpected behaviors of angular momentum in Z-axis as compared with the accurate solar radiation pressure model. In order to clarify the causes of the angular momentum anomalies, several small disturbances like thermal radiation pressure, deformation of the structure, and interplanetary magnetic field effect, which are usually ignored are discussed in this study. The thermal radiation and deformation of the structure can explain the over-large Z-axis anomaly. The interplanetary magnetic field effect is correlated with the sudden change of Z-axis torque anomaly in several cases, but the cause of the anomaly is not completely revealed yet.
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Proceedings of the International Astronautical Congress, IAC 2018年
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Advances in the Astronautical Sciences 2018年
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Proceedings of the International Astronautical Congress, IAC 2018年
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Proceedings of the International Astronautical Congress, IAC 2017年
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Proceedings of the International Astronautical Congress, IAC 2017年
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The 25th International Symposium on Space Flight Dynamics, 2015年
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The International Symposium on Antennas and Propagation 2013年
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Tsinghua University IAF-SUAC International Student Workshop 2013年
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UN/Japan Nano-Satellite Symposium 2012年
担当経験のある科目(授業)
2-
2025年 - 現在航空宇宙工学特殊講義C：宇宙プロジェクト実践とその基礎学理 (大阪公立大学)
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2024年 - 2025年サステイナブル工学先端特論：月惑星着陸探査の最前線 (東京工科大学大学院)
主要なWorks(作品等)
7共同研究・競争的資金等の研究課題
2-
宇宙科学研究所 宇宙科学の技術フロントローディング 2021年4月 - 2027年3月
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日本学術振興会 科学研究費助成事業 若手研究 2023年4月 - 2026年3月
主要な学術貢献活動
7主要な社会貢献活動
24主要なメディア報道
4-
Universe Today 2025年4月16日 インターネットメディアInterferometry connects multiple telescopes into a single large telescope with higher resolution. It works on Earth, but an interferometer space telescope has always been a dream, with NASA's Terrestrial Planet Finder getting canceled decades ago. There's too much technical risk. A new research paper proposes a scaled-down, ultraprecision formation flying mission called SILVIA, which would test the key technology to enable future interferometer space telescopes.
