研究者業績

久保 勇貴

クボ ユウキ  (Yuki KUBO)

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 宇宙飛翔工学研究系 宇宙航空プロジェクト研究員
学位
博士(工学)(2022年3月 東京大学)
修士(工学)(2019年3月 東京大学)
学士(工学)(2017年3月 東京大学)

ORCID ID
 https://orcid.org/0000-0001-7710-9504
J-GLOBAL ID
202101001156242209
researchmap会員ID
R000015398

久保 勇貴 (KUBO Yuki),工学博士

宇宙航空研究開発機構 宇宙科学研究所 宇宙飛翔工学研究系 宇宙航空プロジェクト研究員

東京大学大学院 工学系研究科博士課程修了.工学博士.2022年4月より,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 宇宙航空プロジェクト研究員.専門は宇宙機の軌道・姿勢制御と宇宙ロボティクス,宇宙機システム工学.特に変形する宇宙機・宇宙ロボットによる非ホロノミック性を利用した姿勢制御手法の研究に従事し,宇宙機構造を大きく変える構造可変性と迅速な姿勢変更能力を両立する革新的な宇宙機システムを提案している.

 


学歴

 3

論文

 13
  • 久保勇貴, 中条俊大
    Astrodynamics 8(1) 47-60 2024年2月8日  査読有り筆頭著者
  • 深井 稜汰, 菊地 翔太, 久保 勇貴, 坂谷 尚哉, 嶌生 有理, 木村 駿太, 尾崎 直哉, 村上 豪
    日本惑星科学会誌遊星人 32(4) 288-295 2023年12月  査読有り
  • Toshihiro CHUJO, Yuki KUBO, Tetsuya KUSUMOTO
    Journal of Evolving Space Activities 1 69 2023年  査読有り
  • 久保勇貴
    東京大学大学院 博士論文 2022年3月  筆頭著者
  • Yuki Kubo, Junichiro Kawaguhi
    Aerospace Technology Japan 20 35-40 2022年  査読有り筆頭著者
  • Yuki Kubo, Junichiro Kawaguchi
    Journal of Guidance, Control, and Dynamics 45(7) 1299-1309 2022年  査読有り筆頭著者
  • David D. Fan, Kyohei Otsu, Yuki Kubo, Anushri Dixit, Joel Burdick, Ali-Akbar Agha-Mohammadi
    Proceedings of Robotics: Science and Systems 2021年7月  査読有り
  • Masanori Matsushita, Toshihiro Chujo, Jun Matsumoto, Osamu Mori, Rikio Yokota, Hiroyuki Toyota, Yasutaka Satou, Nobukatsu Okuizumi, Hideki Kato, Tetsuya Nakamura, Yuichi Shibata, Tatsuro Nakao, Kazuyuki Mori, Sanae Fujii, Yuki Takao, Yuki Kubo, Yuya Miyamoto, Yuichiro Nada, Risa Motegi, Genki Ohira, Yudai Kimishima
    Advances in Space Research 67(9) 2899-2911 2021年5月  査読有り
    This paper reports on the manufacturing and evaluation of a solar power sail membrane prototype for the OKEANOS project. The in-house prototype was built by the Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency. Mechanical and electrical evaluation tests were conducted. The membrane, thin-film solar cells, reflectivity control devices were good condition after the manufacturing and handling. The improvements in the manufacturing process and design were found. The manufacturing process and design were fundamentally established. After the prototype, improvement plans for the manufacturing process and design were tried. We have a prospect of manufacturing the flight model sail and continue to the development.
  • 久保勇貴, 梅田啓右, 茂木倫紗, 佐伯孝尚, 川口淳一郎
    日本航空宇宙学会論文集 69(2) 68-71 2021年  査読有り筆頭著者
  • Motoo ITO, Tatsuaki OKADA, Yoko KEBUKAWA, Jun AOKI, Yosuke KAWAI, Jun MATSUMOTO, Toshihiro CHUJO, Ryosuke NAKAMURA, Hajime YANO, Sho-ichiro YOKOTA, Michisato TOYODA, Hisayoshi YURIMOTO, Motoki WATANABE, Ryota IKEDA, Yuki KUBO, Noel GRAND, Herve COTTIN, Arnaud BUCH, Cyril SZOPA, Osamu MORI
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19(4) 477-484 2021年  査読有り
  • Osamu Mori, Jun Matsumoto, Toshihiro Chujo, Masanori Matsushita, Hideki Kato, Takanao Saiki, Yuichi Tsuda, Jun’ichiro Kawaguchi, Fuyuto Terui, Yuya Mimasu, Go Ono, Naoko Ogawa, Yuki Takao, Yuki Kubo, Kaoru Ohashi, Ahmed Kiyoshi Sugihara, Tatsuaki Okada, Takahiro Iwata, Hajime Yano
    Astrodynamics 4(3) 233-248 2020年9月  査読有り
    The solar power sail is an original Japanese concept in which electric power is generated by thin-film solar cells attached on the solar sail membrane. Japan Aerospace Exploration Agency (JAXA) successfully demonstrated the world’s first solar power sail technology through IKAROS (Interplanetary Kite-craft Accelerated by Radiation of the Sun) mission in 2010. IKAROS demonstrated photon propulsion and power generation using thin-film solar cells during its interplanetary cruise. Scaled up, solar power sails can generate enough power to drive high specific impulse ion thrusters in the outer planetary region. With this concept, we propose a landing or sample return mission to directly explore a Jupiter Trojan asteroid using solar power sail-craft OKEANOS (Oversize Kite-craft for Exploration and AstroNautics in the Outer Solar System). After rendezvousing with a Trojan asteroid, a lander separates from OKEANOS to collect samples, and perform in-situ analyses in three proposed mission sequences, including sending samples back to Earth. This paper proposes a system design for OKEANOS and includes analyses of the latest mission.
  • Yuji Sato, Shinya Fujita, Toshinori Kuwahara, Yoshihiko Shibuya, Koh Kamachi, Junichiro Kawaguchi, Yuki Kubo, Yuichiro Nada, Kaoru Ohashi
    2020 IEEE/SICE INTERNATIONAL SYMPOSIUM ON SYSTEM INTEGRATION (SII) 477-482 2020年  査読有り
    This paper provides the thruster control approach for micro-satellites to realize autonomous orbit and attitude control. The Space Robotics Laboratory (SRL) of Tohoku University and ALE Co. Ltd. are currently developing a micro-satellite called "ALE-2" to generate artificial meteors. This satellite is required to keep the sun-synchronous orbit at the altitude of 375-400 km due to operational safety and mission constraints. ALE-2 is equipped with the High Density Cold Gas Jet System (HDCGJ) developed by Patchedconics, LLC for orbit and attitude control. Although a variety of thruster control methods have been proposed, this research focuses on a design of a reliable, uncomplicated and robust algorithm using the low-thrust, 4 nozzle propulsion system. A precomputed thruster selection table is utilized to reduce the processing power and to optimize the thrust force and torque distribution. The evaluation result from the full-software closed-loop simulation demonstrated that the proposed approach was valid for the orbit control of ALE-2 while high attitude control stability could be maintained in the long term.
  • Toshihiro Chujo, Osamu Mori, Yuki Kubo
    Acta Astronautica 140 133-139 2017年11月  査読有り
    A phase equilibrium propulsion system is a kind of cold-gas jet in which the phase equilibrium state of the fuel is maintained in a tank and its vapor is ejected when a valve is opened. One such example is a gas-liquid equilibrium propulsion system that uses liquefied gas as fuel. This system was mounted on the IKAROS solar sail and has been demonstrated in orbit. The system has a higher storage efficiency and a lighter configuration than a high-pressure cold-gas jet because the vapor pressure is lower, and is suitable for small spacecraft. However, the system requires a gas-liquid separation device in order to avoid leakage of the liquid, which makes the system complex. As another example of a phase equilibrium propulsion system, we introduce a solid-gas equilibrium propulsion system, which uses a sublimable substance as fuel and ejects its vapor. This system has an even lower vapor pressure and does not require such a separation device, instead requiring only a filter to keep the solid inside the tank. Moreover, the system is much simpler and lighter, making it more suitable for small spacecraft, especially CubeSat-class spacecraft, and the low thrust of the system allows spacecraft motion to be controlled precisely. In addition, the thrust level can be controlled by controlling the temperature of the fuel, which changes the vapor pressure. The present paper introduces the concept of the proposed system, and describes ejection experiments and its evaluation. The basic function of the proposed system is demonstrated in order to verify its usefulness.

MISC

 5

書籍等出版物

 2
  • 安達茉莉子, 岡田悠, 小原晩, 小山田浩子, 久保勇貴, JUNERAY, 瀬尾夏美, pha, パリッコ, 吉川浩満, 藤岡みなみ (担当:共著, 範囲:土星の輪をくぐる)
    2024年
  • 久保勇貴
    太田出版 2023年3月24日 (ISBN: 9784778318567)

所属学協会

 1

共同研究・競争的資金等の研究課題

 2

産業財産権

 1

学術貢献活動

 2

社会貢献活動

 21

メディア報道

 15