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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

 94
  • 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.
  • NAKAYA Koji, FUKUDA Seisuke, SAKAI Shin-ichiro, YAMAZAKI Atsushi, UEMIZU Kazunori, TORIUMI Tsuyoshi, Junko TAKAHASHI, MAEHARA Masaki, OKAHASHI Takakazu, SHUJIRO SAWAI And
    Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan (Web) 10(ists28) 2012年  
  • Peter J. Buist, Sandra Verhagen, Tatsuaki Hashimoto, Shujira Sawai, Shin-Ichiro Sakai, Nobutaka Bando, Shigehito Shimizu
    GPS World 22(9) 57-66 2011年9月  
  • K. Enya, T. Kotani, K. Haze, K. Aono, T. Nakagawa, H. Matsuhara, H. Kataza, T. Wada, M. Kawada, K. Fujiwara, M. Mita, S. Takeuchi, K. Komatsu, S. Sakai, H. Uchida, S. Mitani, T. Yamawaki, T. Miyata, S. Sako, T. Nakamura, K. Asano, T. Yamashita, N. Narita, T. Matsuo, M. Tamura, J. Nishikawa, E. Kokubo, Y. Hayano, S. Oya, M. Fukagawa, H. Shibai, N. Baba, N. Murakami, Y. Itoh, M. Honda, B. Okamoto, S. Ida, M. Takami, L. Abe, O. Guyon, P. Bierden, T. Yamamuro
    Advances in Space Research 48(2) 323-333 2011年7月15日  
  • 中邨 勉, 坂東 信尚, 坂井 真一郎, 齋藤 宏文
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 58(682) 309-315 2010年11月5日  
    A radio astronomical observatory satellite ``ASTRO-G'', which will be launched in 2012, has two characteristics: flexible appendages and high-speed and high-precision attitude maneuvering. Because of these two antithetical features, attitude control system (ACS) of ASTRO-G becomes quite challenging in comparison with those of past satellites. For such a satellite, feedforward control which is robust to model identification error is considered to be important. Nil-Mode-Exciting (NME) profiler is one of references for anti-vibration, which is designed to excite no flexible modes, and thus its robustness is considered to be of most significant. NME profiler, however, is relatively slow reference because of negligible high frequency component. In this paper, we propose Modified NME profiler which is relatively fast reference designed by convolution of NME profiler and Input Shaper. Some anti-vibration experiments are carried out to show the effectiveness of the proposed reference.
  • Shinji Mitani, Takanori Iwata, Ken Fujiwara, Shin-Ichiro Sakai, Keigo Enya, Takayuki Kotani, Hideo Matsuhara, Takao Nakagawa, Toshio Matsumoto, Woong-Seob Jeong, Dae-Hee Lee
    Proceedings of SPIE - The International Society for Optical Engineering 7731 2010年  
  • ANDO Masaki, KAWAMURA Seiji, SATO Shuichi, NAKAMURA Takashi, TSUBONO Kimio, ARAYA Akito, FUNAKI Ikkoh, IOKA Kunihito, KANDA Nobuyuki, MORIWAKI Shigenori, MUSHA Mitsuru, NAKAZAWA Kazuhiro, NUMATA Kenji, SAKAI Shin-ichiro, SETO Naoki, TAKASHIMA Takeshi, TANAKA Takahiro, DECIGO Working Group the
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 8(27) Po_4_1-Po_4_6 2010年  
    A space gravitational wave antenna, DECIGO (DECI-hertz interferometer Gravitational wave Observatory) will provide fruitful insights into the universe, particularly on dark energy, the formation mechanism of supermassive black holes, and the inflation of the universe. In the current pre-conceptual design, DECIGO will be comprised of 4 interferometer units; each interferometer unit will be realized by formation flight of three drag-free spacecraft with 1000 km separation. Since DECIGO will be an extremely challenging mission with high-precision formation flight, it is important to increase the technical feasibility before its planned launch in 2024. Thus, we are planning two milestone missions. DECIGO pathfinder (DPF) is the first milestone mission for DECIGO, and key components for DPF are being tested on ground and in orbit. In this article, we review the conceptual design and current status of DECIGO and DPF.
  • SAITO Hirobumi, SAKAI Shin-ichiro, HIGUCHI Ken, KISHIMOTO Naoko, TAKEUCHI Hiroshi, YOSHIHARA Keisuke, ASAKI Yoshiharu, TSUBOI Masato, MURATA Yasuhiro, KOBAYASHI Hideyuki
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 8(27) To_4_33-To_4_41 2010年  査読有り
    Space VLBI (very long baseline interferometry) mission, ASTRO-G, will be launched in 2013 by Japan Aerospace Exploration Agency (JAXA). ASTRO-G is a follow-on mission of HALCA (VSOP) mission in 1990s, which was the world first space VLBI mission. ASTRO-G will consists of a huge synthetic aperture with diameter of 35,000 Km together with radio antennas in the ground. They will achieve the world highest angular resolution imaging by means of 43 GHz observation. This paper describes the advanced key technologies of ASTRO-G such as the 9 m deployable antenna with very accurate surface, the fast rest - to - rest attitude maneuver, and the precision orbit determination above NAVSTAR&#039;s orbits. These advance technologies lead ASTRO-G mission to the astronomical observation with the world highest angular resolution.
  • Peter J. Buist, Sandra Verhagen, Tatsuaki Hashimoto, Shujiro Sawai, Shin-ichiro Sakai, Nobutaka Bando, Shigehito Shimizu
    2010 IEEE-ION POSITION LOCATION AND NAVIGATION SYMPOSIUM PLANS 1287-1294 2010年  査読有り
  • Masaki Ando, Seiji Kawamura, Shuichi Sato, 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
    CLASSICAL AND QUANTUM GRAVITY 26(9) 2009年5月  
  • 橋本 樹明, 澤井 秀次郎, 坂井 真一郎, 坂東 信尚, 小林 弘明, 石川 毅彦, 稲富 裕光, 藤田 和央, 吉光 徹雄, 斎藤 芳隆, 福家 英之
    JASMA : Journal of the Japan Society of Microgravity Application 26(1) 9-14 2009年1月31日  
  • 澤井 秀次郎, 橋本 樹明, 坂井 真一郎, 坂東 信尚, 吉光 徹雄, 石川 毅彦, 稲富 裕光, 福家 英之, 鎌田 幸男, 長江 朋子, 小林 弘明, 藤田 和央, 小島 孝之, 上野 誠也, 宮路 幸二, 門岡 昇平, 平木 講儒, 鈴木 宏二郎, 上原 聡
    JASMA : Journal of the Japan Society of Microgravity Application 26(1) 21-28 2009年1月31日  
  • 福田 盛介, 水野 貴秀, 坂井 真一郎, 福島 洋介, 齋藤 宏文
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 57(660) 25-31 2009年1月5日  
    REIMEI/INDEX (INnovative-technology Demonstration EXperiment) is a 70kg class small satellite which the Institute of Space and Astronautical Science, Japan Exploration Agency, ISAS/JAXA, has developed for observation of auroral small-scale dynamics as well as demonstration of advanced satellite technologies. An important engineering mission of REIMEI is integrated satellite control using commercial RISC CPUs with a triple voting system in order to ensure fault-tolerance against radiation hazards. Software modules concerning every satellite function, such as attitude control, data handling, and mission applications, work cooperatively so that highly sophisticated satellite control can be performed. In this paper, after a concept of the integrated satellite control is introduced, the Integrated Controller Unit (ICU) is described in detail. Also unique topics in developing the integrated control system are shown.
  • Takaaki TANAKA, Takashi KIDA, Tomoyuki NAGASHIO, Takashi OHTANI, Isao YAMAGUCHI, Tokio KASAI, Yoshiro HAMADA, Shin-ichiro SAKAI, Nobutaka BANDO
    Journal of Space Engineering 2(1) 12-24 2009年  
  • Tetsuo Yoshimitsu, Shujiro Sawai, Takahide Mizuno, Seisuke Fukuda, Nobutaka Bando, Shin'ichiro Sakai, Ken Higuchi, Tatsuaki Okada, Takashi Kubota, Daisuke Kobayashi, Ryoichiro Yasumitsu, Makoto Kunugi, Shoji Yoshikawa, Katsumi Furukawa, Tetsuya Matsuo
    60th International Astronautical Congress 2009, IAC 2009 2 1096-1100 2009年  査読有り
  • Tatsuaki Hashimoto, Shujiro Sawai, Shin'ichiro Sakai, Nobutaka Bando, Hiroaki Kobayashi, Kazuhisa Fujita, Yuko Inatomi, Takehiko Ishikawa, Tetsuo Yoshimitsu, Yoshitaka Saito
    Proc. 60th International Astronautical Congress 1 IAC-09.A2.5.3-730 2009年  査読有り
  • ISHIKAWA Takehiko, HASHIMOTO Tatsuaki, SAWAI Shujiro, SAITO Yoshitaka, INATOMI Yuko, YOSHIMITSU Tetsuo, SAKAI Shin'ichiro, KOBAYASHI Hiroaki, FUJITA Kazuhisa, BANDO Nobutaka
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7(26) Ph_29-Ph_33 2009年  
    The second flight of microgravity experiment system using a free fall capsule from a high altitude balloon was conducted in May 2007. Using a drag free control, around 10-4G gravity conditions were obtained for 30 seconds. Results of a combustion experiment with Japanese sparker conducted inside the microgravity experimental unit were also reported.
  • SAWAI Shujiro, FUJITA Kazuhisa, KOBAYASHI Hiroaki, SAKAI Shin'ichiro, BANDO Nobutaka, KADOOKA Shouhei, TSUBOI Nobuyuki, MIYAJI Koji, UCHIYAMA Taku, HASHIMOTO Tatsuaki
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7(26) Tg_27-Tg_34 2009年  
    JAXA is developing Mach 5 hypersonic turbojet engine technology that can be applied in a future hypersonic transport. Now, Jet Engine Technology Research Center of JAXA conducts the experimental study using a 1 / 10 scale-model engine. In parallel to engine development activities, a new supersonic flight-testing vehicle for the hypersonic turbojet engine is under development since 2004. In this paper, the system configuration of the flight-testing vehicle is outlined and development status is reported.
  • SAITO Hirobumi, SAWAI Syujiro, SAKAI Shin-ichiro, FUKUDA Seisuke, KITADE Kenji
    Acta Astronautica 65(9/10) 2009年  
  • 福田盛介, 澤井秀次郎, 坂井真一郎, 齋藤宏文, 遠間孝之, 高橋純子, 鳥海強, 北出賢二
    宇宙技術(Web) 8 2009年  
  • 石川 毅彦, 稲富 裕光, 橋本 樹明, 澤井 秀次郎, 斎藤 芳隆, 吉光 徹雄, 坂井 真一郎, 小林 弘明, 藤田 和央, 坂東 信尚, 後藤 雅享
    JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 25(1) 3-10 2008年1月31日  
  • Shin-Ichiro Sakai, Ryosuke Kaneda, Ken Maeda, Tetsu Saitoh, Hirobumi Saito, Tatsuaki Hashimoto
    European Space Agency, (Special Publication) ESA SP (654) 2008年  
  • 金田良介, 坂井真一郎, 橋本樹明, 齋藤宏文
    日本航空宇宙学会論文集 56(652) 203-210 (J-STAGE)-210 2008年  査読有り
    For astronomical observing missions by formation flying satellites in LEO, satellites require control force to keep the relative position, against Keplerian orbit in an inertia coordinate frame. Since satellites require propulsion systems, i.e. thrusters, but the use of thrusters limits the mission lifetime associated with the finite fuel supply. Thus the authors propose the formation flight using electromagnetic force. In this method, the electromagnetic force between super-conducting magnets are used for the relative position control. This method has the obvious advantage of no-fuel to acquire control force. Since such large magnetic moment in earth magnetism generates large disturbance torque, the magnetic moments should be sinusoidal with shorter period than that of the orbit period. Therefore, this paper proposes the relative position control by changing the phase difference between sinusoidal magnetic moments. The proposed method was evaluated with numerical simulations and the results shows the feasibility of the proposed formation flight.
  • 澤井秀次郎, 橋本樹明, 坂井真一郎, 坂東信尚, 小林弘明, 藤田和央, 吉光徹雄, 石川毅彦, 稲富裕光, 福家英之, 鎌田幸男, 星野慎二, 田島賢一, 門岡昇平, 上原聡, 小島孝之, 上野誠也, 宮路幸二, 坪井伸幸, 平木講儒, 鈴木宏二郎, 松嶋清穂, 中田孝
    日本航空宇宙学会論文集 56(654) 2008年  
  • Inatomi Yuko, Ishikawa Takehiko, Hashimoto Tatsuaki, SAWAI Shujiro, SAITO Yoshitaka, YOSHIMITSU Tetsuo, SAKAI Shin-ichiro, KOBAYASHI Hiroaki, FUJITA Kazuo, BANDO Nobutaka, GOTO Masayuki, JIMBO Itaru, YAMAKAWA Hiroshi
    JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 24(3) 296-300 2007年7月30日  
  • Hirobumi Saito, Takahide Mizuno, Koji Tanaka, Yoshitsugu Sone, Seisuke Fukuda, Shin-Ichiro Sakai, Nobukatsu Okuizumi, Makoto Mita, Yosuke Fukushima, Masatoshi Uno, Yoshimitsu Yanagawa, Takuya Takahara, Ryosuke Kaneda, Takashi Honma, Masafumi Hirahara, Kazushi Asamura, Takeshi Sakanoi, Akira Miura, Toshinori Ikenaga, Horiyuki Nagamatsu, Keita Ogawa, Yasunari Masumoto
    International Astronautical Federation - 58th International Astronautical Congress 2007 6 3668-3678 2007年  
  • Nobutaka Bando, Ken-Ichi Tajima, Shin-Ichiro Sakai, Yuko Inatomi, Takehiko Ishikawa, Hiroaki Kobayashi, Kazuhisa Fujita, Hideyuki Fuke, Shujiro Sawai, Tatsuaki Hashimoto
    International Astronautical Federation - 58th International Astronautical Congress 2007 1 495-500 2007年  
  • Maeda K, Tohma T, Saitoh T, Hara Y, Mitsuda K, Dotani T, Maeda Y, Ishida M, Kokubun M, Kunieda H, Hashimoto T, Sakai S
    Proceedings of the SICE Annual Conference 3019-3024 2007年  査読有り
  • 稲富 裕光, 石川 毅彦, 橋本 樹明, 澤井 秀次郎, 斉藤 芳隆, 吉光 徹雄, 坂井 真一郎, 小林 弘明, 藤田 和央, 坂東 信尚, 後藤 雅享, 神保 至, 山川 宏
    JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 23(4) 197-203 2006年11月30日  
  • 稲富 裕光, 神保 至, 石川 毅彦, 橋本 樹明, 澤井 秀次郎, 斉藤 芳隆, 吉光 徹雄, 坂井 真一郎, 小林 弘明, 藤田 和央, 坂東 信尚, 後藤 雅享, 山川 宏
    JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 23(4) 280-280 2006年11月30日  
  • Seisuke Fukuda, Shin-ichiro Sakai, Yousuke Fukushima, Kazushi Asamura, Takahide Mizuno, Hirobumi Saito, Takuya Takahara, Ryosuke Kaneda, Yoshimitsu Yanagawa
    SpaceOps 2006 Conference 2006年  
  • Ryosuke Kanada, Shin-Ichiro Sakai, Tatsuaki Hashimoto, Hirobumi Saito
    Advances in the Astronautical Sciences 124 381-394 2006年  
  • Toshio Kamiya, Ken Maeda, Naoto Ogura, Tatsuaki Hashimoto, Shin-Ichiro Sakai, Yasuhiro Murata, Nanako Mochizuki
    Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2006 2 948-956 2006年  
  • 稲富 裕光, 坂東 信尚, 澤井 秀次郎, 石川 毅彦, 坂井 真一郎, 吉光 徹雄, 斎藤 芳隆, 山川 宏, 橋本 樹明
    JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 22(4) 317-317 2005年11月28日  
  • Hirobumi Saito, Takahide Mizuno, Koji Tanaka, Yoshitsugu Sone, Seisuke Fukuda, Shin-Ichiro Sakai, Nobukatsu Okuizumi, Makoto Mita, Yosuke Fukushima, Masafumi Hirahara, Kazushi Asamura, Takeshi Sakanoi, Akira Miura, Toshinori Ikenaga, Yasunari Masumoto
    International Astronautical Federation - 56th International Astronautical Congress 2005 4 2379-2394 2005年  
  • 坂井 真一郎, 福島 洋介, 本間 貴之, 金田 良介, 長尾 剛司
    電子情報通信学会論文誌. B, 通信 = The transactions of the Institute of Electronics, Information and Communication Engineers. B 88(1) 69-78 2005年1月1日  
    2004年打上げ予定の小型科学衛星"INDEX"は,60[kg]の小型衛星でありながら高精度の姿勢制御を行ってオーロラ観測を行う科学衛星である.重量及びコストの点でハードウェアの制約を受ける中で,高精度な姿勢制御性能を実現するために様々な工夫を施している.本論文ではこのうち,センサ性能を十分に考慮した姿勢制御系の設計手法,また光学センサの触を避けるための衛星運用方式とその評価などについて述べる.更に,効率的に試験・開発を進めるための柔軟なテレメトリコマンドシステムについても紹介する.
  • 橋本 樹明, 斎藤 芳隆, 稲富 裕光, 石川 毅彦, 澤井 秀次郎, 山川 宏, 吉光 徹雄, 坂井 真一郎
    JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 21 66-66 2004年11月4日  

MISC

 46
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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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