研究者業績
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  2. 坂井 真一郎

坂井 真一郎

サカイ シンイチロウ  (Shin-ichiro Sakai)

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 宇宙機応用工学研究系 教授
学位
博士（工学)(2000年3月 東京大学)
研究者番号
10342619
J-GLOBAL ID
202101019944115931
researchmap会員ID
R000018454
外部リンク

主要な研究キーワード

 2
もっとみる

主要な受賞

 18
もっとみる

論文

 86
  • Ito Takahiro, Ueda Satoshi, Yokota Kentaro, Sakai Shin-ichiro, Sawai Shujiro
    Journal of Guidance, Control, and Dynamics 25-29 2025年3月11日  査読有り
  • Ishida Takayuki, Fukuda Seisuke, Kariya Kazuki, Kamata Hiroyuki, Takadama Keiki
    Acta Astronautica 226(P1) 772-781 2024年11月13日  査読有り
  • Shibata Takuma, Ersin Halil, Sakai Shin-ichiro
    Aerospace Science and Technology 155(P1) 2024年9月23日  査読有り
  • Nakamura Tetsuya, Akiyama Hidefumi, Kanaya Shusaku, Miyazawa Yu, Toyota Hiroyuki, Sakai Shin-ichiro
    Journal of Evolving Space Activities 2 2024年9月2日  査読有り
  • Ueda Satoshi, Ito Takahiro, Sakai Shin-ichiro
    Journal of Evolving Space Activities 2 2024年9月2日  査読有り
  • Kambayashi Masaru, Ito Takahiro, Sakai Shinichiro
    Transactions of the Japan Society for Aeronautical and Space Sciences 67(1) 23-31 2024年1月4日  査読有り
  • Toyota Hiroyuki, Miyazawa Yu, Kanaya Shusaku, Kukita Akio, Kondo Hiroatsu, Koide Kazuya, Kuhara Takahiro, Nakamura Kazuyuki, Kawano Taro, Naito Hitoshi, Sawai Shujiro, Fukuda Seisuke, Sakai Shinichiro
    Transactions of the Japan Society for Aeronautical and Space Sciences 66(6) 199-208 2023年11月4日  査読有り
  • Cetiny Mustafa Efe, Soken Halil Ersin, Sakai Shinichiro
    The Journal of the Astronautical Sciences 69 1726-1743 2022年11月11日  査読有り
  • 植田 聡史, 伊藤 琢博, 坂井 真一郎
    計測自動制御学会論文集 58(3) 194-201 2022年4月7日  査読有り
  • Shibata Takuma, Sakai Shinichiro
    JOURNAL OF SPACECRAFT AND ROCKETS 59(2) 651-659 2022年3月29日  査読有り
  • Ito Takahiro, Sakai Shinichiro
    JOURNAL OF GUIDANCE, CONTROL, AND DYNAMICS 46(4) 695-708 2022年2月1日  査読有り
  • Takahashi Yuta, Sakamoto Hiraku, Sakai Shin-ichiro
    Journal of Guidance, Control, and Dynamics 45(2) 280-295 2022年2月1日  査読有り
  • Satoshi UEDA, Takahiro ITO, Shinichiro SAKAI
    Transactions of the Society of Instrument and Control Engineers 58(3) 194-201 2022年  
  • Ueda Satoshi, Sakai Shin-ichiro
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19(3) 334-343 2021年5月4日  査読有り
  • 柴田 拓馬, 坂井 真一郎
    日本航空宇宙学会論文集 69(2) 60-67 2021年4月5日  査読有り
  • Daijiro Shiraiwa, Nobuhiko Tanaka, Kohei Kojima, Takao Kaneko, Shinichiro Sakai, Kenichi Kushiki, Shujiro Sawai, Keisuke Michigami, Taro Kawano, Kenta Goto, Katsumi Furukawa
    Proceedings of the International Astronautical Congress, IAC C4 2021年  
  • Go Fujii, Kaname Kawatsu, Yu Daimon, Keisuke Michigami, Kenichi Kushiki, Shujiro Sawai, Shinichiro Sakai
    AIAA Propulsion and Energy Forum, 2021 2021年  
  • Ito Takahiro, Sakai Shin-ichiro
    Journal of Guidance, Control, and Dynamics 44(4) 854-861 2020年12月1日  査読有り
  • Ito Takahiro, Sakai Shin-ichiro
    Acta Astronautica 176(6) 438-454 2020年11月1日  査読有り
  • 五十里 哲, 伊藤 琢博, 小栗 健士朗, 稲守 孝哉, 坂井 真一郎, 川勝 康弘, 冨木 淳史, 船瀬 龍
    日本航空宇宙学会論文集 68(2) 89-95 2020年8月1日  査読有り
    <p>A Fault Detection, Isolation, and Recovery (FDIR) algorithm for attitude control systems is a key technology to increasing the reliability and survivability of spacecraft. Micro/nano interplanetary spacecraft, which are rapidly evolving in recent years, also require robust FDIR algorithms. However, the implementation of FDIR algorithms to these micro/nano spacecraft is difficult because of the limitations of their resources (power, mass, cost, and so on). This paper shows a strategy of how to construct a FDIR algorithm in the limited resources, taking examples from micro deep space probe PROCYON. The strategy focuses on function redundancies and multi-layer FDIR. These ideas are integrated to suit the situation of micro/nano interplanetary spacecraft and demonstrated in orbit by the PROCYON mission. The in-orbit results are discussed in detail to emphasize the effectiveness of the FDIR algorithm. </p>
  • Soken Halil Ersin, Sakai Shin-ichiro, Asamura Kazushi, Nakamura Yosuke, Takashima Takeshi, Shinohara Iku
    Aerospace 7(97) 97-97 2020年7月1日  査読有り
    JAXA’s ERG (Exploration of Energization and Radiation in Geospace) Spacecraft, which is nicknamed Arase, was launched on 20 December 2016. Arase is a spin-stabilized and Sun-oriented spacecraft. Its mission is to explore how relativistic electrons in the radiation belts are generated during space storms. Two different on-ground attitude determination algorithms are designed for the mission: A TRIAD-based algorithm that inherits from old missions and a filtering-based new algorithm. This paper, first, discusses the design of the filtering-based attitude determination algorithm, which is mainly based on an Unscented Kalman Filter (UKF), specifically designed for spinning spacecraft (SpinUKF). The SpinUKF uses a newly introduced set of attitude parameters (i.e., spin-parameters) to represent the three-axis attitude of the spacecraft and runs UKF for attitude estimation. The paper then presents the preliminary attitude estimation results for the spacecraft that are obtained after the launch. The results are presented along with the encountered challenges and suggested solutions for them. These preliminary attitude estimation results show that the expected accuracy of the fine attitude estimation for the spacecraft is less than 0.5°.
  • Soken Halil Ersin, Sakai Shin-ichiro
    ISA Transactions 2019年9月1日  最終著者
  • 柴田 拓馬, 坂井 真一郎
    日本航空宇宙学会論文集 67(4) 126-135 2019年8月1日  最終著者
  • Mitani Shinji, Mizutani Tadahito, Sakai Shin-ichiro
    DESIGN AND DEVELOPMENT OF FIBER OPTIC ROTATION SENSORS 113-124 2019年7月1日  
  • 新井 久旺, 坂井 真一郎
    日本航空宇宙学会論文集 67(3) 81-92 2019年6月1日  最終著者
  • Takahiro Ito, Shinichiro Sakai
    Proceedings of the International Astronautical Congress, IAC 2019- 2019年  
  • Nakamura Yosuke, Fukuda Seisuke, Shibano Yasuko, Ogawa Hiroyuki, Sakai Shin-ichiro, Shimizu Shigehito, Soken Halil Ersin, Miyazawa Yu, Toyota Hiroyuki, Kukita Akio, Maru Yusuke, Nakatsuka Junichi, Sakai Tomohiko, Takeuchi Shinsuke, Maki Kenichiro, Mita Makoto, Ogawa Emiko, Kakehashi Yuya, Nitta Kumi, Asamura Kazushi, Takashima Takeshi, Shinohara Iku
    Earth, Planets and Space 70(1) 102 2018年12月1日  
  • Ito Takahiro, .Ikari Satoshi, Funase Ryu, Sakai Shin-ichiro, Kawakatsu Yasuhiro, Tomiki Atsushi, Inamori Takaya
    Acta Astronautica 152 299-309 2018年11月1日  
  • 石井 晴之, 村田 暁紀, 上野 史, 辰巳 嵩豊, 梅内 祐太, 高玉 圭樹, 原田 智広, 鎌田 弘之, 石田 貴行, 福田 盛介, 澤井 秀次郎, 坂井 真一郎
    航空宇宙技術 17 69-78 2018年5月1日  
  • 植田 聡史, 坂井 真一郎, 福田 盛介, 澤井 秀次郎
    計測と制御 57(4) 222-228 2018年4月1日  
  • 植田 聡史, 伊藤 琢博, 樋口 丈浩, 上野 誠也, 坂井 真一郎
    航空宇宙技術 17 45-54 2018年3月1日  
  • 澤井 秀次郎, 福田 盛介, 坂井 真一郎, 櫛木 賢一, 荒川 哲人, 佐藤 英一, 冨木 淳史, 道上 啓亮, 河野 太郎, 岡崎 峻, 久木田 明夫, 宮澤 優, 植田 聡史, 戸部 裕史, 丸 祐介, 下地 治彦, 清水 康弘, 芝崎 裕介, 島田 貞則, 横井 貴弘, 藪下 剛, 佐藤 賢一郎, 中村 和行, 久原 隆博, 高見 剛史, 田中 伸彦, 古川 克己
    航空宇宙技術 17 35-43 2018年3月1日  
    <p>SLIM (Smart Lander for Investigating Moon) is the Lunar Landing Demonstrator which is under development at ISAS/JAXA. SLIM demonstrates not only so-called Pin-Point Landing Technique to the lunar surface, but also demonstrates the design to make the explorer small and lightweight. Realizing the compact explorer is one of the key points to achieve the frequent lunar and planetary explorations. This paper summarizes the preliminary system design of SLIM, especially the way to reduce the size.</p>
  • 岡田 怜史, 中浜 優佳, 森部 美沙子, 鎌田 弘之, 狩谷 和季, 高玉 圭樹, 石田 貴行, 福田 盛介, 澤井 秀次郎, 坂井 真一郎
    航空宇宙技術 17 61-67 2018年3月1日  
  • Halil Ersin Soken, Shin-Ichiro Sakai, Kazushi Asamura, Yosuke Nakamura, Takeshi Takashima
    Advances in the Astronautical Sciences 162 1175-1193 2018年  
  • 平澤 遼, 池永 敏憲, 植田 聡史, 坂井 真一郎
    航空宇宙技術 17 1-9 2018年1月1日  最終著者
  • Shuichi Sato, Seiji Kawamura, Masaki Ando, Takashi Nakamura, Kimio Tsubono, Akito Araya, Ikkoh Funaki, Kunihito Ioka, Nobuyuki Kanda, Shigenori Moriwaki, Mitsuru Musha, Kazuhiro Nakazawa, Kenji Numata, Shin-ichiro Sakai, Naoki Seto, Takeshi Takashima, Takahiro Tanaka, Kazuhiro Agatsuma, Koh-suke Aoyanagi, Koji Arai, Hideki Asada, Yoichi Aso, Takeshi Chiba, Toshikazu Ebisuzaki, Yumiko Ejiri, Motohiro Enoki, Yoshiharu Eriguchi, Masa-Katsu Fujimoto, Ryuichi Fujita, Mitsuhiro Fukushima, Toshifumi Futamase, Katsuhiko Ganzu, Tomohiro Harada, Tatsuaki Hashimoto, Kazuhiro Hayama, Wataru Hikida, Yoshiaki Himemoto, Hisashi Hirabayashi, Takashi Hiramatsu, Feng-Lei Hong, Hideyuki Horisawa, Mizuhiko Hosokawa, Kiyotomo Ichiki, Takeshi Ikegami, Kaiki T. Inoue, Koji Ishidoshiro, Hideki Ishihara, Takehiko Ishikawa, Hideharu Ishizaki, Hiroyuki Ito, Yousuke Itoh, Nobuki Kawashima, Fumiko Kawazoe, Naoko Kishimoto, Kenta Kiuchi, Shiho Kobayashi, Kazunori Kohri, Hiroyuki Koizumi, Yasufumi Kojima, Keiko Kokeyama, Wataru Kokuyama, Kei Kotake, Yoshihide Kozai, Hideaki Kudoh, Hiroo Kunimori, Hitoshi Kuninaka, Kazuaki Kuroda, Kei-ichi Maeda, Hideo Matsuhara, Yasushi Mino, Osamu Miyakawa, Shinji Miyoki, Mutsuko Y. Morimoto, Tomoko Morioka, Toshiyuki Morisawa, Shinji Mukohyama, Shigeo Nagano, Isao Naito, Kouji Nakamura, Hiroyuki Nakano, Kenichi Nakao, Shinichi Nakasuka, Yoshinori Nakayama, Erina Nishida, Kazutaka Nishiyama, Atsushi Nishizawa, Yoshito Niwa, Taiga Noumi, Yoshiyuki Obuchi, Masatake Ohashi, Naoko Ohishi, Masashi Ohkawa, Norio Okada, Kouji Onozato, Kenichi Oohara, Norichika Sago, Motoyuki Saijo, Masaaki Sakagami, Shihori Sakata, Misao Sasaki, Takashi Sato, Masaru Shibata, Hisaaki Shinkai, Kentaro Somiya, Hajime Sotani, Naoshi Sugiyama, Yudai Suwa, Rieko Suzuki, Hideyuki Tagoshi, Fuminobu Takahashi, Kakeru Takahashi, Keitaro Takahashi, Ryutaro Takahashi, Ryuichi Takahashi, Tadayuki Takahashi, Hirotaka Takahashi, Takamori Akiteru, Tadashi Takano, Keisuke Taniguchi, Atsushi Taruya, Hiroyuki Tashiro, Yasuo Torii, Morio Toyoshima, Shinji Tsujikawa, Yoshiki Tsunesada, Akitoshi Ueda, Ken-ichi Ueda, Masayoshi Utashima, Yaka Wakabayashi, Hiroshi Yamakawa, Kazuhiro Yamamoto, Toshitaka Yamazaki, Jun’ichi Yokoyama, Chul-Moon Yoo, Shijun Yoshida, Taizoh Yoshino
    Journal of Physics: Conference Series 840(1) 012010-012010 2017年5月  査読有り
  • Takahiro Ito, Satoshi Ueda, Shin-Ichiro Sakai, Shujiro Sawai, Seisuke Fukuda, Kenichi Kushiki, Seiya Ueno, Takehiro Higuchi, Yusuke Shibasaki, Takeshi Kuroda
    Proceedings of the International Astronautical Congress, IAC 2 856-866 2017年  
  • Halil Ersin Soken, Shin-Ichiro Sakai, Kazushi Asamura, Yosuke Nakamura, Takeshi Takashima
    Advances in the Astronautical Sciences 160 2615-2629 2017年  
  • Halil Ersin Soken, Shin-ichiro Sakai, Kazushi Asamura, Yosuke Nakamura, Takeshi Takashima
    SPACEFLIGHT MECHANICS 2017, PTS I - IV 160 2615-2629 2017年  
  • Satoshi Ikari, Takaya Inamori, Takahiro Ito, Kaito Ariu, Kenshiro Oguri, Masataka Fujimoto, Shinichiro Sakai, Yasuhiro Kawakatsu, Ryu Funase
    Transactions of the Japan Society for Aeronautical and Space Sciences 60(3) 181-191 2017年  
  • Satoshi Ikari, Takaya Inamori, Takahiro Ito, Kaito Ariu, Kenshiro Oguri, Masataka Fujimoto, Shinichiro Sakai, Yasuhiro Kawakatsu, Ryu Funase
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 60(3) 181-191 2017年  
  • Halil Ersin Soken, Shin-Ichiro Sakai, Kazushi Asamura, Yosuke Nakamura, Takeshi Takashima
    2016 AIAA Guidance, Navigation, and Control Conference 2016年  
  • TAKINO Tatsuya, NOMURA Izuru, MORIBE Misako, KAMATA Hiroyuki, TAKADAMA Keiki, FUKUDA Seisuke, SAWAI Shujiro, SAKAI Shin-ichiro
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 14(30) Pt_7-Pt_14 2016年  
    <p>In this study, a crater detection method for a moon-landing system with low computational resources is proposed. The proposed method is applied to the Smart Lander for Investigating Moon (SLIM), which aims for a pin-point landing on the moon. According to this plan, surface images of the moon will be captured by a camera mounted on the space probe, and the craters are to be detected from the images. Based on the positional relationship between detected craters, the method estimates the exact flight position of the space probe. Because the computational resources of SLIM are limited, rapid and accurate crater detection must be performed using fixed-point arithmetic on a field-programmable gate array (FPGA). This study proposes a crater detection method that uses principal component analysis (PCA). The computational processing for crater detection by PCA is performed by product-sum operations, which are suitable for fixed-point arithmetic. Moreover, this method is capable of parallel processing; hence high-speed processing is expected. This study not only introduces a crater detection method using PCA but also evaluates the properties of this method.</p>
  • 丸 祐介, 山本 信, 福山 誠二郎, 岡田 純平, 菅 勇志, 梯 友哉, 福家 英之, 伊藤 琢博, 水島 隆成, 江口 光, 石川 毅彦, 坂東 信尚, 澤井 秀次郎, 清水 成人, 坂井 真一郎, 吉光 徹雄, 小林 弘明, 菊池 政雄
    日本航空宇宙学会論文集 63(6) 257-264 2015年  査読有り
    In this paper is presented a microgravity experiment system utilizing a high altitude balloon. The feature is a double shell structure of a vehicle that is dropped off from the balloon and a microgravity experiment section that is attached to the inside of the vehicle with a liner slider. Control with cold gas jet thrusters of relative position of the experiment section to the vehicle and attitude of the vehicle maintains fine microgravity environment. The design strategy of the vehicle is explained, mainly referring to differences from the authors' previous design. The result of the flight experiment is also shown to evaluate the characteristics of the presented system.
  • Kikuchi Masao, Ishikawa Takehiko, Yamamoto Shin, Sawai Shujiro, Maru Yusuke, Sakai Shinichiro, Bando Nobutaka, Shimizu Shigehito, Kobayashi Hiroaki, Yoshimitsu Tetsuo, Kan Yuji, Mizushima Takanari, Fukuyama Seijiro, Okada Junpei, Yoda Shinichi, Fuke Hideyuki, Kakehashi Yuya, Hashimoto Tatsuaki
    INTERNATIONAL JOURNAL OF MICROGRAVITY SCIENCE AND APPLICATION 32(2) 2015年  査読有り
  • 坂東 信尚, 福家 英之, 莊司 泰弘, Doetinchem Philip v., Hailey Charles J., 坂井 真一郎, 橋本 樹明
    航空宇宙技術 14 59-65 2015年  
    In this paper, direction control of balloon gondola with only untwisting motor is proposed. Typically a reaction wheel and another actuator for unloading the reaction wheel are in use to control the attitude (or direction) of the gondola. Although this method can get high accuracy control performance, two actuators spend many resources of the gondola. The proposed method uses only untwisting motor installed above the gondola to rotate. This method can not realize such high accuracy control performance but realize direction control with the most simple configuration. The proposed method is applied to prototype GAPS (General Anti-Particle Spectrometer) balloon experiment in 2012. This paper shows control design for this experiment and the results of the proposed method.
  • A. Yamazaki, F. Tsuchiya, T. Sakanoi, K. Uemizu, K. Yoshioka, G. Murakami, M. Kagitani, Y. Kasaba, I. Yoshikawa, N. Terada, T. Kimura, S. Sakai, K. Nakaya, S. Fukuda, S. Sawai
    SPACE SCIENCE REVIEWS 184(1-4) 259-274 2014年11月  査読有り
  • Shinji Mitani, Yasuhiro Kawakatsu, Shin-ichiro Sakai, Naomi Murakami, Toshihiko Yamawaki, Tadahito Mizutani, Keiji Komatsu, Hirokazu Kataza, Keigo Enya, Takao Nakagawa
    SPACE TELESCOPES AND INSTRUMENTATION 2014: OPTICAL, INFRARED, AND MILLIMETER WAVE 9143 2014年  
  • T. Kotani, K. Enya, T. Nakagawa, H. Matsuhara, H. Kataza, M. Kawada, M. Mita, K. Komatsu, H. Uchida, K. Fujiwara, S. Mitani, S. Sakai, K. Haze, H. Kaneda, S. Oyabu, D. Ishihara, T. Miyata, S. Sako, T. Nakamura, K. Asano, M. Tamura, J. Nishikawa, T. Yamashita, N. Narita, H. Hayano, S. Oya, E. Kokubo, Y. Itoh, T. Matsuo, M. Fukagawa, H. Shibai, M. Honda, N. Baba, N. Murakami, Y. K. Okamoto, S. Ida, M. Takami, L. Abe, O. Guyon, T. Yamamuro
    SPACE TELESCOPES AND INSTRUMENTATION 2012: OPTICAL, INFRARED, AND MILLIMETER WAVE 8442 2012年  
  • NAGAMATSU Hiroyuki, ASAMURA Kazushi, YAMAZAKI Atsushi, SAKAI Shin-ichiro, FUKUDA Seisuke, SAITO Hirobumi
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 10(28) Pf_15-Pf_19 2012年  
    We are in progress to develop a system for automatic operation of a satellite in order to reduce human load at satellite steady operation phase. The ground station for small satellite REIMEI (INDEX : INnovative-technology Demonstration EXperiment) is used as a test bench for verification of the proposed method. In our new automatic operation system, a scheduler software as a substitutive operator manages all the operations through a unified procedure, including sending command, receiving telemetry, and driving antenna in accordance with an operation time line which is prepared before the operation pass. The scheduler also performs diagnostics of satellite anomaly based upon the received telemetry data and status of the ground station. In case that some anomaly of the satellite is detected, the scheduler initiates an emergency schedule that was prepared depending on the emergency level. The automatic operation system is nearly completed for downlink operations of the data recorder that account for 75% of REIMEI steady operation. This approach is very effective to reduce psychological and physical load of operators.

MISC

 42
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主要な講演・口頭発表等

 281
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共同研究・競争的資金等の研究課題

 5

産業財産権

 4

社会貢献活動

 18
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