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Hiroyuki Ogawa

  (小川 博之)

Profile Information

Affiliation
Professor, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
Degree
Doctor of Engineering(Mar, 1996, Nagoya University)
Contact information
ogawa.hiroyukijaxa.jp
J-GLOBAL ID
200901051344540154
researchmap Member ID
1000253790
External link

Research on advanced thermal control systems for future scientific satellites
　Based on the experience of scientific satellite projects, we analyze the current issues and future plans, and conduct research and development of advanced thermal control systems for future scientific satellites. The results of our research have been fed back to the thermal control system on board the X-ray astronomy satellite Hitomi, and are being considered for application to the next scientific satellite project.

Thermal control for scientific satellite projects
　In challenging projects that actively employ thermo-fluid devices, such as the Japan-Europe Mercury mission BepiColombo, which will be exposed to extreme environments that have never been experienced before, and the large X-ray telescope satellite Hitomi, new satellite development methods that have never been experienced before are required. In such challenging projects that actively employ thermo-fluid devices, conventional satellite development methods and their extensions cannot be applied. We are contributing to the success of the project from the viewpoint of heat by leading the new research and development with our academic knowledge of thermo-fluid mechanics, such as development of new materials that can withstand extreme environments, construction of thermal design and analysis methods, development of test facilities, and development of verification methods.

Application of thermo-fluid mechanics
　We are contributing to various space science project activities based on our academic knowledge of thermo-fluid and its related fields. In the research of reusable rockets, we are contributing to the solution of problems related to thermo-fluid such as engine flow, cryogenic tanks, and external flow. In the area of satellite propulsion, we have contributed to the improvement of thruster analysis technology by studying the chemical reaction flow inside hydrazine thrusters, and in the area of rocket propulsion, we have developed a method for analyzing the internal flow of solid rockets and contributed to the investigation of the causes of malfunctions in M-V rockets and SRB-A rockets. In the rocket propulsion system, he developed an internal flow analysis method for solid rockets and contributed to investigating the cause of the failure of the M-V rocket and SRB-A. He has also contributed to rocket research by working on rocket flight safety and radio frequency interference problems with rocket exhaust plumes. I have also conducted theoretical research on shock wave interference in high-speed electromagnetic fluids and propulsion systems using electromagnetic fluids.

Research Interests

 8

Research Areas

 4

Research History

 6
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Education

 1

Committee Memberships

 1

Awards

 1

Papers

 80
  • Xinyu Chang, Takeshi Yokouchi, Kimihide Odagiri, Hiroyuki Ogawa, Hosei Nagano, Hiroki Nagai
    International Journal of Heat and Mass Transfer, 221 125037-125037, Apr, 2024  
  • Kimihide Odagiri, Xinyu Chang, Hiroki Nagai, Hiroyuki Ogawa
    Applied Thermal Engineering, 121109-121109, Jul, 2023  
  • Hideyuki Fuke, Shun Okazaki, Akiko Kawachi, Manami Kondo, Hiroyuki Ogawa, Noboru Yamada
    Nuclear Instruments and Methods in Physics Research Section A: Accelerators, Spectrometers, Detectors and Associated Equipment, 1049 168102-168102, Apr, 2023  
  • Masaru Hirata, Kimihide Odagiri, Hiroyuki Ogawa
    Applied Thermal Engineering, 219 119573-119573, Jan, 2023  
    A capillary pumped loop (CPL) is a capillary force-driven heat transport device that uses the phase change of a working fluid. A CPL has excellent properties in terms of heat transport capability, heat transport distance, and flexibility in heat transport path arrangement. However, its startup reliability is low, and its startup characteristics have yet to be determined. This study aims to investigate the startup characteristics of a CPL and improve its startup reliability. The startup procedures are newly proposed and experimentally verified in this paper. In the proposed method, the evaporator was preheated in addition to the reservoir preheating before startup. Verification was done by switching the order of the reservoir preheating and evaporator preheating. The experimental results showed that the proposed methods enable the CPL to start up even in conditions where the CPL was unable to start up by a conventional method (reservoir temperatures ranging from 40 °C to 80 °C). It was also confirmed that the order of the evaporator preheating and reservoir preheating affects the degree of overshoot of the evaporator temperature. The maximum temperature of the evaporator at the startup was reduced by up to 91.5 °C in case the evaporator was preheated before the reservoir preheating.
  • Naoko Iwata, Masanori Saitoh, Keiichi Yanagase, Yasuhiro Iso, Yukio Inoue, Hiroyuki Ogawa, Yoshiro Miyazaki
    JOURNAL OF SPACECRAFT AND ROCKETS, Feb, 2022  
    Typically, spacecraft development is costly and time-consuming because of the many iterations usually needed to reach optimal design solutions. This paper presents an innovative approach that eliminates the need to iterate the thermal design process using a network of variable conductance oscillating heat pipes (VC-OHPs) on every structural panel. The temperatures of the panels where components are mounted would thus be maintained at constant levels by VC-OHPs, even if the instruments' locations or heat dissipation changes. A structural thermal model was built to verify the proposed thermal and structural design in a simulated deep space environment and in a launch environment. It consisted of two VC-OHPs and six aluminum honeycomb panels. A thermal vacuum test was conducted to demonstrate the temperature control by the VC-OHPs. The test results showed that temperature control by VC-OHPs could maintain the panels operating as evaporators at stable temperatures and follow the reservoir temperature. A vibration test was conducted under the launch environment of a Japanese H2A rocket. The results confirmed that the structural thermal model met requirements for resistance to mechanical launch environment. The VC-OHPs functioned after the vibration test. The structural thermal model showed that the proposed thermal control architecture is feasible in an actual spacecraft in terms of thermal and structure design.
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Misc.

 380
  • 高橋克征, 岡崎峻, 福家英之, 山田昇, 小川博之
    日本伝熱シンポジウム講演論文集(CD-ROM), 54th, 2017  
  • 高橋克征, 岡崎峻, 近藤愛実, 福家英之, 山田昇, 河内明子, 小川博之
    太陽/風力エネルギー講演論文集, 2017 439-442, 2017  
  • 石村 康生, 仙場 淳彦, 秋田 剛, 鳥阪 綾子, 田中 宏明, 山川 宏, 宮下 朋之, 河野 太郎, 馬場 満久, 小川 博之, 岡崎 峻, 後藤 健, 嶋田 岳史, 旗持 天, 村田 泰宏, 前田 良知, 石田 学, 岩田 直子, 柴野 靖子, 高精度伸展式光学架台の研究開発メンバー, Ishimura Kosei, Senba Atsuko, Akita Tsuyoshi, Torisaka Ayako, Tanaka. Hiroaki, Yamakawa Hiroshi, Miyashita Tomoyuki, Kawano Taro, Baba Mitsuhisa, Ogawa Hiroyuki, Okazaki Shun, Goto Ken, Shimada Takeshi, Murata Yasuhiro, Maeda Yoshitomo, Ishida Manabu, Iwata Naoko, Shibano Yasuko, R&D member of Precise Extensible Optical Bench
    第32回宇宙構造・材料シンポジウム：講演集録 = Proceedings of 32nd Symposium on Aerospace Structure and Materials, Dec, 2016  
    第32回宇宙構造・材料シンポジウム（2016年12月9日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)), 相模原市, 神奈川県資料番号: SA6000087012レポート番号: A11
  • 嶋田 岳史, 石村 康生, 小川 博之, 岡崎 駿, Shimada Takeshi, Ishimura Kosei, Ogawa Hiroyuki, Okazaki Shun
    第32回宇宙構造・材料シンポジウム：講演集録 = Proceedings of 32nd Symposium on Aerospace Structure and Materials, Dec, 2016  
    第32回宇宙構造・材料シンポジウム（2016年12月9日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)), 相模原市, 神奈川県資料番号: SA6000087016レポート番号: A15
  • Kozai Masayoshi, Asao Yoshito, Inoue Takayoshi, Inoue Takuya, Okazaki Shun, Ogawa Hiroyuki, Kato Chihiro, Kawachi Akiko, Koike T., Sakimoto Kazuhiro, Shimizu Yuki, Takahashi Katsumasa, Takahashi Shun, Daimaru Takuro, Nagai Hiroki, Hashimoto Takeshi, Fuke Hideyuki, Munakata Kazuoki, Yamada Noboru, Yoshida Atsumasa, Yoshida Tetsuya, Wada Takuya, Aramaki T., Boggs S., Craig W. W., Doetinch P.v., Fabris R., Gahbauer F., Hailey C.J., Madden N., Mognet S.A.I, Mori K., Ong R., Perez K., Ziock K.P., Zweerink J.
    Nov, 2016  
    Balloon Symposium 2016 (November 1-2, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
  • 60 6p, Sep 6, 2016  
  • Hiroyuki Ogawa, Keisuke Shinozaki, Takao Nakagawa
    46th International Conference on Environmental Systems, Jul, 2016  
  • Naoko Iwata, Takashi Usui, Akihiko Miki, Mizuho Ikeda, Yoh Takei, Atsushi Okamoto, Hiroyuki Ogawa, Tadayuki Takahashi
    46th International Conference on Environmental Systems, Jul, 2016  
  • 柴野 靖子, 浅村 和史, 小川 博之, Shibano Yasuko, Asamura Kazushi, Ogawa Hiroyuki
    平成27年度宇宙科学に関する室内実験シンポジウム 講演集 = Proceedings of 2016 Symposium on Laboratory Experiment for Space Science, Feb, 2016  
    平成27年度宇宙科学に関する室内実験シンポジウム (2016年2月23日-24日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県資料番号: SA6000055019
  • Maeda Yoshitomo, Ishida Manabu, Iizuka Ryo, Iwata Naoko, Minesugi Kenji, Ishimura Kosei, Kawano Taro, Ogawa Hiroyuki, Taniguchi Shohei, Kawamoto Masamitsu, Shionome Yu, Someya Kentaro, Sato Takuro, Ichihara Kou, Tomikawa Kazuki, Sato Toshiki, Kikuchi Naomichi, Serlemitsos Peter, Soong Yang, Okajima Takashi, Olsen Larry, Robinson David, McGuinness Dan, Szymkiewicz Richard, Hahne Devin, Sytwu Joseph, Kearney John, Toomey Emory, Lozipone Larry, Brown Clif, Numata Ai, Galassi Nick, Thorpe Rosemary, Contino Dominic, Pless Paul, Schofield Mark, Chang Bill, Rice Brian, Henry Chris, Glenn Kevin, Koenecke Richard, Cottingham Christine, Mori Hideyuki, Hayashi Takayuki, Tawara Yuzuru, Tachibana Kenji, Torii Tatsuharu, Tamura Keisuke, Ishibashi Kazunori, Kunieda Hideyo, Ogasaka Yasushi, Sakurai Ikuya, Mochida Masayuki, Kawabata Eiji, Ito Toshihiro, Iwase Toshihiro, Kurebayashi Yuuki, Watanabe Tsuyoshi, Awaki Hisamitsu, Ogi Keiji, Itoh Keitaro, Izumiya Takanori, Awaya Takashi, Okada Gohta, Minami Sari, Sugita Satoshi, Miyazawa Takuya, Furuzawa Akihiro
    Meeting Abstracts of the Physical Society of Japan, 71 369-369, 2016  
  • 芝井広, 小川博之, 中川貴雄, 松原英雄, 尾中敬, 河野孝太郎, 金田英宏, 山田亨
    日本天文学会年会講演予稿集, 2016, 2016  
  • 高橋克征, 岡崎峻, 福家英之, 山田昇, 小川博之
    混相流シンポジウム講演論文集(CD-ROM), 2016, 2016  
  • 岡崎峻, 福家英之, 高橋克征, 山田昇, 小川博之
    混相流シンポジウム講演論文集(CD-ROM), 2016, 2016  
  • 芝井広, 小川博之, 中川貴雄, 松原英雄, 山田亨, 尾中敬, 河野孝太郎, 金田英宏
    日本天文学会年会講演予稿集, 2016, 2016  
  • 柴野靖子, 小川博之
    Thermophysical Properties, 37th, 2016  
  • 宮田喜久子, 長野方星, 岡崎峻, 太刀川純孝, 小川博之
    計測自動制御学会システムインテグレーション部門講演会(CD-ROM), 17th, 2016  
  • 筒井雄樹, 岡崎峻, 小川博之
    数値流体力学シンポジウム講演論文集(CD-ROM), 30th, 2016  
  • 小川博之, 伊藤隆, 中村昌道
    宇宙航空研究開発機構特別資料 JAXA-SP-(Web), (16-003), 2016  
  • Kazunori Mochizuki, Yuta Habaguchi, Mitsutoshi Tsujioka, Satoshi Nonaka, Hiroyuki Ogawa, Takashi Ito, Sakamoto Noboru
    Proceedings of the International Astronautical Congress, IAC, 2016  
    Copyright © 2016 by the International Astronautical Federation (IAF). All rights reserved. Mitsubishi Heavy Industries, LTD. (MHI) has been contributed to the development and manufacture of liquid fuelled launch vehicles from early phase in Japan. MHI began providing launch services with H-IIA launch vehicle for both commercial and government missions in 2007. In 2013 the H-IIB was added in the line-up of service launcher family. The latest success rate of H-IIA/B has reached to 97 percent. In addition, the development of new expendable launcher H3 has started, and it's first flight is planned in FY2020. In parallel, aiming for the drastic reduction of space transportation cost, RD for the reusable space transportation systems are in progress. The fundamental technologies for reusable engine, landing gear, and propellant management devices needed during way back flight, has been developed with JAXA. Especially, reusable 40 kN thrust liquid hydrogen/oxygen engine has been developed and demonstrated successful firing worth 100 flights duration in 2014. Additionally, MHI has studied guidance, navigation and control technology for vertical landing rocket, and demonstrated the control law in the flight test by a subscale experimented vehicle. This paper describes the current RD status of reusable rocket and approach to future reusable space transportation system which MHI considers.
  • H. Ogawa, T. Nakagawa, H. Matsuhara, K. Shinozaki, K. Goto, N. Isobe, M. Kawada, T. Mizutani, Y. Sato, H. Sugita, S. Takeuchi, T. Yamawaki, H. Shibai
    Proceedings of SPIE - The International Society for Optical Engineering, 9904, 2016  
    © 2016 SPIE. We present the new design of the cryogenic system of the next-generation infrared astronomy mission SPICA under the new framework. The new design employs the V-groove design for radiators, making the best use of the Planck heritage. The new design is based on the ESA-JAXA CDF study (NG-CryoIRTel, CDF-152(A)) with a 2 m telescope, and we modified the CDF design to accommodate the 2.5 m telescope to meet the science requirements of SPICA. The basic design concept of the SPICA cryogenic system is to cool the Science Instrument Assembly (SIA, which is the combination of the telescope and focal-plane instruments) below 8K by the combination of the radiative cooling system and mechanical cryocoolers without any cryogen.
  • Shibai Hiroshi, Ogawa Hiroyuki, Onaka Takashi, Kaneda Hidehiro, Kohno Kotaro, Nakagawa Takao, Matsuhara Hideo, Yamada Toru, SPICA team
    Jan, 2016  
    16th Space Science Symposium (January 6-7, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan
  • 小川 博之, 再使用観測ロケットチーム, Ogawa Hiroyuki
    第16回宇宙科学シンポジウム 講演集 = Proceedings of the 16th Space Science Symposium, Jan, 2016  
    第16回宇宙科学シンポジウム (2016年1月6日-7日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県資料番号: SA6000046247レポート番号: S4-010
  • 47th 3p, 2016  
  • 岡崎峻, 西山和孝, 小川博之, 長野方星, 川勝康弘
    宇宙科学技術連合講演会講演集(CD-ROM), 60th 5p, 2016  
  • 60th 6p, 2016  
  • 60th 4p, 2016  
  • 60th 4p, 2016  
  • 60th 6p, 2016  
  • 60th 6p, 2016  
  • 60th 5p, 2016  
  • Keisuke Shinozaki, Hiroyuki Ogawa, Takao Nakagawa, Yoichi Sato, Hiroyuki Sugita, Toshihiro Yamawaki, Tadahito Mizutani, Hideo Matsuhara, Mitsunobu Kawada, Akinobu Okabayashi, Shoji Tsunematsu, Katsuhiro Narasaki, Hiroshi Shibai
    SPACE TELESCOPES AND INSTRUMENTATION 2016: OPTICAL, INFRARED, AND MILLIMETER WAVE, 9904, 2016  
    The Space Infrared Telescope for Cosmology and Astrophysics (SPICA) is a pre-project of JAXA in collaboration with ESA to be launched in the 2020s. The SPICA mission is to be launched into a halo orbit around the second Lagrangian point in the Sun-Earth system, which allows us to use effective radiant cooling in combination with a mechanical cooling system in order to cool a 2.5m-class large IR telescope below 8K. Recently, a new system design in particular thermal structure of the payload module has been studied by considering the technical feasibility of a cryogenic cooled telescope within current constraints of the mission in the CDF (Concurrent Design Facility) study of ESA/ESTEC. Then, the thermal design of the mechanical cooler system, for which the Japanese side is responsible, has been examined based on the CDF study and the feasible solution giving a proper margin has been obtained. As a baseline, 4K / 1K-class Joule-Thomson coolers are used to cool the telescope and thermal interface for Focal Plane Instruments (FPIs). Additionally, two sets of double stirling coolers (2STs) are used to cool the Telescope shield. In this design, nominal operation of FPIs can be kept when one mechanical cooler is in failure.
  • 飯野 晶, 岡崎 峻, 秋田 剛, 石村 康生, 山川 宏, 小川 博之, Iino Akira, Okazaki Shun, Akita Takeshi, Ishimura Kosei, Yamakawa Hiroshi, Ogawa Hiroyuki
    第31回宇宙構造・材料シンポジウム：講演集録 = Proceedings of the 31st Symposium on Aerospace Structure and Materials, Dec, 2015  
    第31回宇宙構造・材料シンポジウム（2015年12月8日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)), 相模原市, 神奈川県資料番号: SA6000047027レポート番号: B13
  • Hiroyuki Ogawa, Tsutomu Yamazaki, Akira Okamoto
    45th International Conference on Environmental Systems, Jul, 2015  Lead author
  • 辻本拓司, 郷田直輝, 小林行泰, 矢野太平, 白旗麻衣, 山口正輝, 宇都宮真, 鹿島伸悟, 亀谷收, 浅利一善, 山田良透, 原拓自, 吉岡諭, 穂積俊輔, 梅村雅之, 西亮一, 浅田秀樹, 長島雅裕, 對木淳夫, 野田篤司, 歌島昌由, 安田進, 石村康生, 坂井真一郎, 小川博之, 福田盛介, 中須賀真一, 酒匂信匡
    日本天文学会年会講演予稿集, 2015, 2015  
  • 郷田直輝, 小林行泰, 辻本拓司, 矢野太平, 白旗麻衣, 山口正輝, 宇都宮真, 鹿島伸悟, 亀谷收, 浅利一善, 山田良透, 原拓自, 吉岡諭, 穂積俊輔, 梅村雅之, 西亮一, 浅田秀樹, 長島雅裕, 對木淳夫, 野田篤司, 歌島昌由, 安田進, 石村康生, 坂井真一郎, 小川博之, 福田盛介, 中須賀真一, 酒匂信匡
    日本天文学会年会講演予稿集, 2015, 2015  
  • 宮崎芳郎, 小川博之, 岩田直子
    日本伝熱シンポジウム講演論文集(CD-ROM), 52nd, 2015  
  • 岡崎峻, 福家英之, 清水憲政, 増山陽介, 河内明子, 宮崎芳郎, 小川博之
    日本伝熱シンポジウム講演論文集(CD-ROM), 52nd, 2015  
  • 芝井広, 小川博之, 中川貴雄, 松原英雄, 尾中敬, 河野孝太郎, 金田英宏
    日本天文学会年会講演予稿集, 2015, 2015  
  • 中川貴雄, 芝井広, 小川博之, 松原英雄, 川田光伸, 片ざ宏一, 山村一誠, 塩谷圭吾, 和田武彦, 村田泰宏, 磯部直樹, 浅野健太朗, 船木一幸, 後藤健, 竹内伸介, 上野宗孝, 杉田寛之, 篠崎慶亮, 佐藤洋一, 山脇敏彦, 水谷忠均, 巳谷真司, 尾中敬, 河野孝太郎, 土井靖生, 左近樹, 金田英宏, 大藪進喜, 石原大助, 津村耕司, 松浦周二
    日本天文学会年会講演予稿集, 2015, 2015  
  • 郷田直輝, 小林行泰, 辻本拓司, 矢野太平, 白旗麻衣, 山口正輝, 宇都宮真, 鹿島伸悟, 亀谷收, 浅利一善, 山田良透, 原拓自, 吉岡諭, 穂積俊輔, 梅村雅之, 西亮一, 浅田秀樹, 長島雅裕, 對木淳夫, 野田篤司, 歌島昌由, 安田進, 石村康生, 坂井真一郎, 小川博之, 福田盛介, 中須賀真一, 酒匂信匡
    日本天文学会年会講演予稿集, 2015, 2015  
  • 森順一, 松本大史, 尾崎真司, 福家英之, 岡崎峻, 宮崎芳郎, 小川博之
    混相流シンポジウム講演論文集(CD-ROM), 2015, 2015  
  • 高橋克征, 岡崎峻, 福家英之, 山田昇, 小川博之
    混相流シンポジウム講演論文集(CD-ROM), 2015, 2015  
  • 岩田直子, 小川博之, 高木亮治, 宮崎芳郎
    混相流シンポジウム講演論文集(CD-ROM), 2015, 2015  
  • 岡崎峻, 福家英之, 高橋克征, 山田昇, 小川博之
    混相流シンポジウム講演論文集(CD-ROM), 2015, 2015  
  • 木村俊哉, 橋本知之, 佐藤正喜, 高田仁志, 八木下剛, 成尾芳博, 小川博之, 伊藤隆, 尾場瀬公人, 大村啓聡
    宇宙科学技術連合講演会講演集(CD-ROM), 59th, 2015  
  • 伊藤隆, 野中聡, 山本高行, 丸祐介, 八木下剛, 竹内伸介, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM), 59th, 2015  
  • 森順一, 松本大史, 尾崎真司, 福家英之, 岡崎峻, 小川博之, 宮崎芳郎
    宇宙科学技術連合講演会講演集(CD-ROM), 59th, 2015  
  • 木澤雅文, 長野方星, 岡崎峻, 小川博之, 永井大樹
    宇宙科学技術連合講演会講演集(CD-ROM), 59th, 2015  
  • 宮田喜久子, 長野方星, 岡崎峻, 太刀川純孝, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM), 59th, 2015  
  • 岡崎峻, 長野方星, 永井大樹, 小川博之, 川勝康弘
    宇宙科学技術連合講演会講演集(CD-ROM), 59th, 2015  

Books and Other Publications

 1

Presentations

 33
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Professional Memberships

 5

Research Projects

 9
More

Industrial Property Rights

 6
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Academic Activities

 1

● 指導学生等の数

 6
  • Fiscal Year
    2018年度(FY2018)
    Doctoral program
    1
  • Fiscal Year
    2019年度(FY2019)
    Doctoral program
    2
    Master’s program
    1
    JSPS Research Fellowship (Young Scientists)
    1
  • Fiscal Year
    2020年度(FY2020)
    Doctoral program
    1
    Master’s program
    1
    JSPS Research Fellowship (Young Scientists)
    1
  • Fiscal Year
    2018年度(FY2018)
    Doctoral program
    1
  • Fiscal Year
    2019年度(FY2019)
    Doctoral program
    2
    Master’s program
    1
    JSPS Research Fellowship (Young Scientists)
    1
  • Fiscal Year
    2020年度(FY2020)
    Doctoral program
    1
    Master’s program
    1
    JSPS Research Fellowship (Young Scientists)
    1

● 専任大学名

 2
  • Affiliation (university)
    東京大学（University of Tokyo)
  • Affiliation (university)
    東京大学（University of Tokyo)

● 所属する所内委員会

 6
  • ISAS Committee
    研究所会議
  • ISAS Committee
    プログラム会議
  • ISAS Committee
    信頼性品質会議
  • ISAS Committee
    環境・安全管理統括委員会
  • ISAS Committee
    ISASニュース編集小委員会
  • ISAS Committee
    宇宙科学プログラム技術委員会
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