宇宙飛翔工学研究系

澤井 秀次郎

サワイ シュウジロウ  (SAWAI SHUJIRO)

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

J-GLOBAL ID
200901034091305402
researchmap会員ID
5000019340

研究キーワード

 2

論文

 379
  • Mitsuhisa Baba, Shinpei Okita, Kentaro Watanabe, Yusuke Maru, Shujiro Sawai, Osamu Mori, Kazuhisa Fujita
    AIAA SCITECH 2023 Forum 2023年1月19日  
  • Hiroyuki TOYOTA, Yu MIYAZAWA, Shusaku KANAYA, Akio KUKITA, Hiroatsu KONDO, Kazuya KOIDE, Takahiro KUHARA, Kazuyuki NAKAMURA, Taro KAWANO, Hitoshi NAITO, Shujiro SAWAI, Seisuke FUKUDA, Shin-ichiro SAKAI
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 66(6) 199-208 2023年  
  • Kaoru Namiki, Yuki Takao, Naoki Morishita, Shota Kikuchi, Yusuke Maru, Osamu Mori, Yuichi Tsuda, Shujiro Sawai
    AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 22 51-61 2023年  
  • Maiko YAMAKAWA, Yusuke MARU, Mitsuhisa BABA, Yu DAIMON, Kazuhisa FUJITA, Shujiro SAWAI, Osamu MORI, Yuichi TSUDA
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 21 29-35 2023年  
  • Osamu Mori, Kenichi Kushiki, Shujiro Sawai, Maki Shida, Yusuke Maru, Keisuke Michigami, Hideshi Kagawa, Taiichi Nagata, Junichi Nakatsuka, Daisuke Goto, Katsumi Furukawa, Tsuyoshi Takami, Hikaru Uramachi, Yuya Mimasu, Fuyuto Terui, Naoko Ogawa, Go Ono, Kent Yoshikawa
    Hayabusa2 Asteroid Sample Return Mission: Technological Innovation and Advances 433-452 2022年1月1日  
    In this chapter, the development procedure and the operation of Hayabusa2 bipropellant chemical propulsion system are described in detail. Lessons learned from the original Hayabusa (sample return mission from the asteroid Itokawa) and Akatsuki (Venus climate orbiter mission) are described, and the countermeasures incorporated into the design of Hayabusa2 chemical propulsion system are detailed. On-orbit data is used to assess the impulse provided by each thruster. In particular, the cause of thrust variability under pulsed operation is investigated, and approaches to ensure stable and reliable thruster operation are proposed. Furthermore, the relation between thrust duration and generated impulse is modeled to enable reliable reproduction of the required ΔV.

MISC

 53

共同研究・競争的資金等の研究課題

 6