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  2. 小川 博之

小川 博之

オガワ ヒロユキ  (Hiroyuki Ogawa)

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 教授
学位
博士(工学)(1996年3月 名古屋大学)
連絡先
ogawa.hiroyukijaxa.jp
J-GLOBAL ID
200901051344540154
researchmap会員ID
1000253790
外部リンク

将来の科学衛星に向けた先進的熱制御システムの研究
　科学衛星プロジェクトの経験を基に，現状の課題と将来計画を分析し，将来の科学衛星に必要な先進的熱制御システムの研究開発をおこなっています．研究成果はX線天文衛星ひとみに搭載された熱制御システムにフィードバックされている他，次期科学衛星計画への適用が検討されている等，科学衛星の可能性を広げ，世界一流の成果を創出する活動に貢献しています．

科学衛星プロジェクトの熱制御
　日欧水星探査計画BepiColombo等のこれまで経験のない極限環境に晒される探査機や，X線大型望遠鏡衛星ひとみ等の熱流体デバイスを積極的に採用した挑戦的プロジェクトにおいては，従来の衛星開発手法やその延長線上では対応できず，これまで経験のない新しい衛星開発手法が求められます．極限環境に耐える新規材料開発や熱設計・解析手法の構築，試験設備整備や検証手法の開発など，新しい研究開発を熱流体力学の学術的知見をもって先導し，熱の観点でプロジェクトの成功に貢献しています．

熱流体力学の応用
　熱流体とその周辺の学術的知見を基に，さまざまな宇宙科学プロジェクト活動に貢献しています．再使用ロケットの研究では，エンジン流れや極低温タンク，外部流等熱流体にかかわる課題解決に貢献しています．衛星推進系ではヒドラジンスラスタ内部化学反応流の研究によりスラスタ解析技術の向上に貢献し，ロケット推進系では固体ロケット内部流解析手法を開発し，M-VロケットやSRB-Aの不具合原因究明に貢献しました．その他，ロケットの飛行安全やロケット排気プルームの電波干渉問題等に関わり，ロケット研究に貢献しています．また高速電磁流体中の衝撃波干渉の理論研究や電磁流体を利用した推進システムの研究をおこないました．

研究キーワード

 8

研究分野

 4

経歴

 6
もっとみる

学歴

 1

委員歴

 1

受賞

 1

論文

 80
  • Xinyu Chang, Takeshi Yokouchi, Kimihide Odagiri, Hiroyuki Ogawa, Hosei Nagano, Hiroki Nagai
    International Journal of Heat and Mass Transfer 221 125037-125037 2024年4月  
  • Kimihide Odagiri, Xinyu Chang, Hiroki Nagai, Hiroyuki Ogawa
    Applied Thermal Engineering 121109-121109 2023年7月  
  • 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 2023年4月  
  • Masaru Hirata, Kimihide Odagiri, Hiroyuki Ogawa
    Applied Thermal Engineering 219 119573-119573 2023年1月  
    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 2022年2月  
    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.
もっとみる

MISC

 380
  • 松田雄太, 長野方星, 岡崎峻, 小川博之, 永井大樹
    日本機械学会論文集(Web) 81(827) 15-00104-15-00104 2015年  
    Loop Heat Pipes (LHPs) have been used in thermal control of spacecraft as next generation heat transport devices. Recently, multiple-evaporators LHP (MLHP) is under studied since the MLHP supplies autonomous thermal control function. However, some physical phenomena in the MLHP have not been clarified yet. The purpose of this study is to clarify thermal behavior of the MLHP under the microgravity. The MLHP used in this research has two evaporators and one condenser. Distilled water is used as the working fluid. 40W/40W, 80W/80W, 120W/0W, 0W/120W heat load were applied during the test. This experiment was conducted under microgravity for about 20 seconds, which was realized by parabolic flight. The vapor-liquid distribution in the wick core and the compensation chamber (CC) under the microgravity is presented. The effect of the microgravity for the working the MLHP is also discussed. The heat distributions in the MLHP when one and both evaporators were heated is also clarified
  • 岡崎峻, 福家英之, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 59th 5p 2015年  
  • 小川 博之, 野中 聡, 伊藤 隆, 橋本 知之, 八木下 剛, 成尾 芳博, 佐藤 正喜, 高田 仁志, 木村 俊哉, 稲谷 芳文, Ogawa Hiroyuki, Nonaka Satoshi, Ito Takashi, Hashimoto Tomoyuki, Yagishita Tsuyoshi, Naruo Yoshihiro, Sato Masaki, Takada Satoshi, Kimura Toshiya, Inatani Yoshifumi
    第15回宇宙科学シンポジウム 講演集 = Proceedings of the 15th Space Science Symposium 33(3) 2015年1月  
    第15回宇宙科学シンポジウム (2015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: SA6000034335レポート番号: S5-001
  • 石村 康生, 山川 宏, 飯野 晶, 小山 遼, 岡崎 峻, 小川 博之, 河野 太郎, 船越 裕亮, 秋田 剛, 仙場 敦彦, 大型高精度光学架台の研究メンバー, Ishimura Kosei, Yamakawa Hiroshi, Iino Akira, Koyama Ryo, Okazaki Shun, Ogawa Hiroyuki, Kawano Taro, Funakoshi Yusuke, Akita Takeshi, Senba Atsuhiko, Members for R&D of Large and Precise Optical Bench
    第30回宇宙構造・材料シンポジウム：講演集録 = Proceedings of 30th Symposium on Aerospace Structure and Materials 2014年12月  
    第30回宇宙構造・材料シンポジウム（2014年12月1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: SA6000043001レポート番号: A01
  • 福家 英之, 野々村 拓, 小川 博之, 岡崎 峻, 田中 結, 吉田 哲也, 安部 拓洋, 井上 剛良, 松宮 宏明, 依田 悠太郎, 大丸 拓郎, 永井 大樹, 河内 明子, 増山 陽介, 清水 憲政, 高橋 俊, 小池 貴久, 宮崎 芳郎, 佐藤 大輔, 高橋 克征, 山田 昇, 吉田 貴則, 荒牧 嗣夫, Gahbauer F., Hailey C. J., Madden N., 森 嘉野, Perez K., Boggs S., Hoberman J., Fuke Hideyuki, Nonomura Taku, Ogawa Hiroyuki, Okazaki Shun, Tanaka Yui, Yoshida Tetsuya, Abe Takumi, Inoue Takayoshi, Matsumiya Hiroaki, Yoda Yutaro, Daimaru Takuro, Nagai Hiroki, Kawachi Akiko, Masuyama Yousuke, Shimizu Kensei, Takahashi Shun, Koike Takahisa, Miyazaki Yoshio, Sato Daisuke, Takahashi Katsumasa, Yamada Noboru, Yoshida Takanori, Aramaki Tsuguo, Gahbauer F., Hailey C. J., Madden N., Mori Kaya, Perez K., Boggs S., Hoberman J.
    大気球シンポジウム: 平成26年度 = Balloon Symposium: 2014 2014年11月  
    大気球シンポジウム 平成26年度（2014年11月6-7日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)）, 相模原市, 神奈川県著者人数: 37名資料番号: SA6000021002レポート番号: isas14-sbs-002
  • Yasuko Shibano, Hisayoshi Suzuki, Takehiro Maki, Keita Fukuzawa, Shingo Matsuura, Hiroyuki Ogawa, Takeshi Takashima
    44th International Conference on Environmental Systems 2014年7月  
  • Naoko Iwata, Takashi Usui, Akihiko Miki, Mizuho Ikeda, Takahiro Yumoto, Yukari Ono, Kazuhiro Abe, Hiroyuki Ogawa, Tadayuki Takahashi
    44th International Conference on Environmental Systems 2014年7月  
  • Satoshi Nonaka, Takashi Ito, Hiroyuki Ogawa, Yoshifumi Inatani
    Proceedings of the International Astronautical Congress, IAC 10 7446-7453 2014年  
    Copyright © 2014 by the International Astronautical Federation. At ISAS/JAXA, we have various space flight tools such as scientific satellites and planetary probe, various launchers including sounding rockets and balloons. In relatively small size of the flight program such as sounding rockets and balloons, we have been conducting both studies using these flight opportunities such as scientific observations, utilization of micro-G environment and so on. In order to make the access to space for researches by the sounding rocket much easier and make the opportunities of the rocket launches much frequent, a fully reusable sounding rocket is proposed, and its preliminary system design study is underway in ISAS/JAXA. In the phase-A, we are progressing the system design and technical demonstrations which are indispensable for the development of the operational system. The technical key issues are 1) a reusable engine, 2) aerodynamics and returning flight mechanics, 3) cryogenic propellant management, 4) health management system, 5) repeated operations. Present status of the reusable sounding rocket activities is summarized in this paper.
  • Hiroyuki Ogawa, Fumitaka Urayama, Susumu Baba, Eiji Miyazaki, Akira Okamoto, Hajime Hayakawa
    44th International Conference on Environmental Systems 2014年  筆頭著者
  • 郷田直輝, 小林行泰, 辻本拓司, 矢野太平, 丹羽佳人, 山口正輝, 宇都宮真, 鹿島伸悟, 亀谷收, 浅利一善, 中島紀, 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, 佐藤洋一, 石村康生, 坂井真一郎, 小川博之, 中須賀真一, 酒匂信匡
    日本天文学会年会講演予稿集 2014 2014年  
  • 松田雄太, 長野方星, 岡崎峻, 小川博之, 永井大樹
    日本伝熱シンポジウム講演論文集(CD-ROM) 51st 2014年  
  • 岡崎峻, 永井大樹, 長野方星, 小川博之
    日本伝熱シンポジウム講演論文集(CD-ROM) 51st 2014年  
  • 岡崎峻, 松宮宏明, 福家英之, 宮崎芳郎, 井上剛良, 小川博之
    日本伝熱シンポジウム講演論文集(CD-ROM) 51st 2014年  
  • 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
    Thermophysical Properties 35th 2014年  
  • 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, 中島紀, 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 2014 2014年  
  • 長野方星, 大野翔也, 藤田涼平, 西川泰司, 沓水真琴, 太刀川純孝, 小川博之
    Thermophysical Properties 35th 2014年  
  • 岡崎峻, 吉田周平, 押山大佑, 大丸拓郎, 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) 58th 2014年  
  • 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) 2014 2014年  
  • 清水憲政, 岡崎峻, 福家英之, 増山陽介, 河内明子, 宮崎芳郎, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 58th 2014年  
  • 篠崎慶亮, 杉田寛之, 佐藤洋一, 安藤麻紀子, 澤田健一郎, 岡崎峻, 小川博之, 松原英雄, 中川貴雄, 高田誠, 高井茂希, 岡林明伸, 恒松正二, 楢崎勝弘
    宇宙科学技術連合講演会講演集(CD-ROM) 58th 2014年  
  • 八木下剛, 橋本知之, 佐藤正喜, 高田仁志, 木村俊哉, 成尾芳博, 伊藤隆, 小川博之, 尾場瀬公人, 福田勇也, 甲斐毅, 丹生謙一, 瀧田純也, 木村竜也, 金子敬郎
    宇宙科学技術連合講演会講演集(CD-ROM) 58th 2014年  
  • 長野方星, 松田雄太, 岡崎駿, 小川博之, 永井大樹
    混相流シンポジウム講演論文集(CD-ROM) 2014 2014年  
  • 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, 中島紀, 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 2014 2014年  
  • 柴野靖子, 小川博之
    Thermophysical Properties 35th 2014年  
  • 岡崎峻, 福家英之, 松宮宏明, 宮崎芳郎, 井上剛良, 小川博之
    混相流シンポジウム講演論文集(CD-ROM) 2014 2014年  
  • 置塩章悟, 野津亮太, 長野方星, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 58th 2014年  
  • 柴野靖子, 浅村和史, 豊田裕之, 小川博之
    スペース・プラズマ研究会・講演集(Web) 2013 2014年  
  • Shun Okazaki, Hideyuki Fuke, Hiroyuki Ogawa, Yoshiro Miyazaki
    IEEE Aerospace Conference Proceedings 2014年  
    Meter-scale Oscillating Heat Pipe (OHP) has been developed for the General Anti Particle Spectrometer (GAPS) project. Two types of the OHP routing have been investigated. One is a U-shaped routing and the other is an O-shaped routing. For the operation at low temperature, R410A was used as the working fluid. As the result of the investigation, we verified for the first time that both the meter-scale O-shaped and U-shaped OHPs can transfer heat in gravity at low temperature. Between the heat input section and the radiator section, the thermal conductance larger than 10 W/K was achieved under particular sets of conditions. In terms of thermal characteristics, the O-shaped OHP showed better performance than the U-shaped OHP. The O-shaped OHP started up more quickly than the U-shaped OHP at low temperature. The temperature uniformity of the O-shaped-OHP heating section was also better without drying-out at around the top of the heating section. The U-shaped OHP could transfer heat at temperatures above around 240 K, and the O-shaped OHP could transfer heat at temperatures above around 210 K. We consider the O-shaped OHP utilizes the gravity to assist the circulation of the working fluid resulting in better performance. © 2014 IEEE.
  • 野津亮太, 長野方星, 小川博之
    日本機械学会論文集(Web) 80(815) TEP0199-TEP0199 2014年  
    A lunar long duration method which utilizes a characteristic of a very low thermal conductivity of lunar regolith has been proposed. The principle of this method is to put heater in desired depth of the regolith and heat up the regolith layer during lunar daytime. Because of the very low thermal conductivity of regolith, stored heat in regolith propagates gradually and raises the surface temperature at cold lunar night. By this method, a lunar lander will be kept warm passively during cold lunar night. In this paper, a temporospatially small-scale experimental apparatus which simulate lunar surface environment was fabricated and thermal cycling condition and heater setting position was calculated by comparing lunar environment, and thermophysical properties of the lunar regolith and regolith simulant used in this work. The feasibility of a passive thermal control method with no electrical power during lunar night time was evaluated.
  • 野中聡, 伊藤隆, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 58th 6p 2014年  
  • 岡崎峻, 小川博之, 鈴木久仁, 牧丈弘, 吉田誠至, 高井茂希, 高田誠
    宇宙科学技術連合講演会講演集(CD-ROM) 58th 5p 2014年  
  • Hirofumi Noda, Kazuhiro Nakazawa, Kazuo Makishima, Naoko Iwata, Hiroyuki Ogawa, Masayuki Ohta, Goro Sato, Madoka Kawaharada, Shin Watanabe, Motohide Kokubun, Tadayuki Takahashi, Masanori Ohno, Yasushi Fukazawa, Hiroyasu Tajima, Hideki Uchiyama, Shuji Ito, Keita Fukuzawa
    SPACE TELESCOPES AND INSTRUMENTATION 2014: ULTRAVIOLET TO GAMMA RAY 9144 2014年  
    The Hard X-ray Imager and the Soft Gamma-ray Detector, onboard the 6th Japanese X-ray satellite ASTRO-H, aim at unprecedentedly-sensitive observations in the 5-80 keV and 40-600 keV bands, respectively. Because their main sensors are composed of a number of semi-conductor devices, which need to be operated in a temperature of -20 to -15 degrees C, heat generated in the sensors must be efficiently transported outwards by thermal conduction. For this purpose, we performed thermal design, with the following three steps. First, we additionally included thermally-conductive parts, copper poles and graphite sheets. Second, constructing a thermal mathematical model of the sensors, we estimated temperature distributions in thermal equilibria. Since the model had rather large uncertainties in contact thermal conductions, an accurate thermal dummy was constructed as our final step. Vacuum measurement with the dummy successfully reduced the conductance uncertainties. With these steps, we confirmed that our thermal design of the main sensors satisfies the temperature requirement.
  • Keisuke Shinozaki, Yoichi Sato, Kenichiro Sawada, Makiko Ando, Hiroyuki Sugita, Toshihiko Yamawaki, Tadahito Mizutani, Keiji Komatsu, Shun Okazaki, Hiroyuki Ogawa, Takao Nakagawa, Hideo Matsuhara, Makoto Takada, Akinobu Okabayashi, Shoji Tsunematsu, Katsuhiro Narasaki
    SPACE TELESCOPES AND INSTRUMENTATION 2014: OPTICAL, INFRARED, AND MILLIMETER WAVE 9143 2014年  
    The Space Infrared Telescope for Cosmology and Astrophysics (SPICA) is a pre-project of JAXA in collaboration with ESA to be launched around 2025. 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 3m large IR telescope below 6K. The use of 4K / 1K-class Joule-Thomson coolers is proposed in order to cool the telescope and provide a 4K / 1K temperature region for Focal Plane Instruments (FPIs). This paper introduces details of the thermal design study for the SPICA payload module in the Risk-Mitigation-Phase (RMP), in which the activity is focused on mitigating the mission's highest risks. As the result of the RMP activity, most of all the goals have been fully satisfied and the thermal design of the payload module has been dramatically improved.
  • Naoko Iwata, Takashi Usui, Akihiko Miki, Mizuho Ikeda, Yukihiro Kaizu, Takahiro Yumoto, Yukari Ono, Kazuhiro Abe, Hiroyuki Ogawa, Tadayuki Takahashi
    43rd International Conference on Environmental Systems 2013年7月  
  • Satoshi Nonaka, Takashi Ito, Hiroyuki Ogawa
    Proceedings of the International Astronautical Congress, IAC 11 8494-8501 2013年  
    To make the opportunities of space scientific researches by using sounding rockets much frequent, a fully reusable sounding rocket is proposed, and system/subsystem designs such as aerodynamics, propulsion systems, structures, etc are progressed in ISAS/JAXA. In the phase- A, we are conducting the technical demonstrations which are indispensable for the development of the operational system. The technical key issues are 1) a reusable engine, 2) aerodynamics and returning flight mechanics, 3) cryogenic propellant management, 4) health management system, 5) repeated operations. The present status of system design and the demonstrations of these technologies planed in phase A are introduced in this paper. Copyright© (2013) by the International Astronautical Federation.
  • 岩田直子, 臼井隆, 三木明彦, 池田瑞穂, 湯本隆宏, 小野ゆかり, 阿部和弘, 小川博之, 高橋忠幸
    宇宙科学技術連合講演会講演集(CD-ROM) 57th 2013年  
  • 岩田直子, 宮崎芳郎, 河合宏紀, 小川博之, 福田盛介
    宇宙科学技術連合講演会講演集(CD-ROM) 57th 2013年  
  • 小川博之, 石本真二, 米本浩一, 渥美正博, 牧野隆, 浅川恵司, 緒川修治
    宇宙科学技術連合講演会講演集(CD-ROM) 57th 2013年  
  • 浦山文隆, 馬場勧, 美浦由佳, 宮崎英治, 小川博之, 早川基
    宇宙科学技術連合講演会講演集(CD-ROM) 57th 2013年  
  • 柴野靖子, 福澤慶太, 松浦真悟, 小川博之, 高島健, 浅村和史
    宇宙科学技術連合講演会講演集(CD-ROM) 57th 2013年  
  • 岩田直子, 小川博之, 宮崎芳郎, 福田盛介
    Thermophysical Properties 34th 2013年  
  • 岩田直子, 小川博之, 宮崎芳郎
    混相流シンポジウム講演論文集(CD-ROM) 2013 2013年  
  • 太田方之, 野田博文, 中澤知洋, 一戸悠人, 東郷淳, 斉藤新也, 武田伸一郎, 渡辺伸, 国分紀秀, 高橋忠幸, 岩田直子, 小川博之, 内山秀樹, 渋谷明伸, 冨塚慎司, 田島宏康, 食野吉史, 大野翔也, 長野方星, 中村竜, 大野雅功, 水野恒史, 深沢泰司
    日本物理学会講演概要集 68(1) 135-135 2013年  
  • 岡崎峻, 福家英之, 宮崎芳郎, 小川博之
    日本機械学会熱工学コンファレンス講演論文集 2013 429-430 2013年  
    Thermal performance of an O-shaped Oscillating Heat pipe (OHP) for balloon-borne General Anti-Particle Spectrometer (GAPS) experiment has been investigated. The developed OHP is a closed type and O-shaped for using the gravity assist. R410A is selected as the working fluid for the use at low temperatures. At -50 deg-C, we achieved a thermal conductance of 20 W/K for 150 W heat input with 32 loops and -40 deg-C heating section. We also found for the first time that this large-scale OHP can be operated at low temperatures. It is found that this OHP can satisfy the GAPS thermal control requirement.
  • 丸 祐介, 野中 聡, 竹内 伸介, 志田 真樹, 八木下 剛, 山本 高行, 伊藤 隆, 成尾 芳博, 小川 博之, 川崎 繁男, 小林 雄太, 吉田 賢史, 森 初男, 水越 紀良, 大貝 高士, 中上 禎章, 水谷 忠均, 岡崎 慎司, Maru Yusuke, Nonaka Satoshi, Takeuchi Shinsuke, Shida Maki, Yagishita Tsuyoshi, Yamamoto Takayuki, Ito Takashi, Naruo Yoshihiro, Ogawa Hiroyuki, Kawasaki Shigeo, Kobayashi Yuta, Yoshida Satoshi, Mori Hatsuo, Mizukoshi Noriyoshi, Ogai Takashi, Nakaue Yoshiaki, Mizutani Tadahito, Okazaki Shinji
    平成24年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium: FY2012 2013年1月  
    平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県形態: カラー図版あり形態: PDF著者人数: 18名資料番号: AA0061856051レポート番号: STCP-2012-051
  • 早川基, 前島弘則, 小川博之, 西野真木, 岡本章
    宇宙科学技術連合講演会講演集(CD-ROM) 57th 4p 2013年  
  • 岡崎峻, 杉本理英, 小川博之, 川勝康弘
    宇宙科学技術連合講演会講演集(CD-ROM) 57th 3p 2013年  
  • 野津亮太, 長野方星, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 57th 6p 2013年  
  • Philip Blumenfeld, Andreea Boca, Paul Sharps, Dennis Russell, Hiroyuki Ogawa, Hiroyuki Toyota
    2013 IEEE 39TH PHOTOVOLTAIC SPECIALISTS CONFERENCE (PVSC) 647-651 2013年  
    Emcore has been performing High Intensity High Temperature (HIHT) tests on covered, interconnected cell (CIC) assemblies. End-of-life performance of spacecraft solar panels depends to a great extent on changes in the optical properties of the CICs' coverglass adhesive during the mission. An important change in silicone coverglass adhesives is observed as degradation of short wavelength transmission, often called "darkening" or "yellowing". This is understood to be driven by exposure to high intensity UV and by exposure to elevated temperature. Solar panels on the Solar Probe Plus (SPP) spacecraft will be exposed to both high UV irradiance and elevated temperature over the course of a long mission. This paper reports on the thermal-mechanical design work performed and planned by Emcore in order to test CICs designed for SPP under these extreme conditions. Three types of thermal test designs are presented: conduction/convection with a single fixed temperature, thermal radiation with multiple fixed temperatures, and thermal radiation with a variable single temperature. We present some detail from predictive thermal models used in the test designs along with temperature data measured during the test runs.
  • Tadayuki Takahashi, Kazuhisa Mitsuda, Richard Kelley, Henri AartsFelix Aharonian, Hiroki Akamatsu, Fumie Akimoto, Steve Allen, Naohisa Anabuki, Lorella Angelini, Keith Arnaud, Makoto Asai, Marc Audard, Hisamitsu Awaki, Philipp Azzarello, Chris Baluta, Aya Bamba, Nobutaka Bando, Mark Bautz, Roger Blandford, Kevin Boyce, Greg Brown, Ed Cackett, Maria Chernyakova, Paolo Coppi, Elisa Costantini, Jelle de Plaa, Jan-Willem den Herder, Michael DiPirro, Chris Done, Tadayasu Dotani, John Doty, Ken Ebisawa, Megan Eckart, Teruaki Enoto, Yuichiro Ezoe, Andrew Fabian, Carlo Ferrigno, Adam Foster, Ryuichi Fujimoto, Yasushi Fukazawa, Stefan Funk, Akihiro Furuzawa, Massimiliano Galeazzi, Luigi Gallo, Poshak Gandhi, Keith Gendreau, Kirk Gilmore, Daniel Haas, Yoshito Haba, Kenji Hamaguchi, Isamu Hatsukade, Takayuki Hayashi, Kiyoshi Hayashida, Junko Hiraga, Kazuyuki Hirose, Ann Hornschemeier, Akio Hoshino, John Hughes, Una Hwang, Ryo Iizuka, Yoshiyuki Inoue, Kazunori Ishibashi, Manabu Ishida, Kosei Ishimura, Yoshitaka Ishisaki, Masayuki Ito, Naoko Iwata, Naoko Iyomoto, Jelle Kaastra, Timothy Kallman, Tuneyoshi Kamae, Jun Kataoka, Satoru Katsuda, Hajime Kawahara, Madoka Kawaharada, Nobuyuki Kawai, Shigeo Kawasaki, Dmitry Khangaluyan, Caroline Kilbourne, Masashi Kimura, Kenzo Kinugasa, Shunji Kitamoto, Tetsu Kitayama, Takayoshi Kohmura, Motohide Kokubun, Tatsuro Kosaka, Alex Koujelev, Katsuji Koyama, Hans Krimm, Aya Kubota, Hideyo Kunieda, Stephanie LaMassa, Philippe Laurent, Francois Lebrun, Maurice Leutenegger, Olivier Limousin, Michael Loewenstein, Knox Long, David Lumb, Grzegorz Madejski, Yoshitomo Maeda, Kazuo Makishima, Genevieve Marchand, Maxim Markevitch, Hironori Matsumoto, Kyoko Matsushita, Dan McCammon, Brian McNamara, Jon Miller, Eric Miller, Shin Mineshige, Kenji Minesugi, Ikuyuki Mitsuishi, Takuya Miyazawa, Tsunefumi Mizuno, Hideyuki Mori, Koji Mori, Koji Mukai, Toshio Murakami, Hiroshi Murakami, Richard Mushotzky, Housei Nagano, Ryo Nagino, Takao Nakagawa, Hiroshi Nakajima, Takeshi Nakamori, Kazuhiro Nakazawa, Yoshiharu Namba, Chikara Natsukari, Yusuke Nishioka, Masayoshi Nobukawa, Masaharu Nomachi, Steve O' Dell, Hirokazu Odaka, Hiroyuki Ogawa, Mina Ogawa, Keiji Ogi, Takaya Ohashi, Masanori Ohno, Masayuki Ohta, Takashi Okajima, Atsushi Okamoto, Tsuyoshi Okazaki, Naomi Ota, Masanobu Ozaki, Frits Paerels, Stephane Paltani, Arvind Parmar, Robert Petre, Martin Pohl, F. Scott Porter, Brian Ramsey, Rubens Reis, Christopher Reynolds, Helen Russell, Samar Safi-Harb, Shin-ichiro Sakai, Hiroaki Sameshima, Jeremy Sanders, Goro Sato, Rie Sato, Yoichi Sato, Kosuke Sato, Makoto Sawada, Peter Serlemitsos, Hiromi Seta, Yasuko Shibano, Maki Shida, Takanobu Shimada, Keisuke Shinozaki, Peter Shirron, Aurora Simionescu, Cynthia Simmons, Randall Smith, Gary Sneiderman, Yang Soong, Lukasz Stawarz, Yasuharu Sugawara, Hiroyuki Sugita, Satoshi Sugita, Andrew Szymkowiak, Hiroyasu Tajima, Hiromitsu Takahashi, Shin-ichiro Takeda, Yoh Takei, Toru Tamagawa, Takayuki Tamura, Keisuke Tamura, Takaaki Tanaka, Yasuo Tanaka, Makoto Tashiro, Yuzuru Tawara, Yukikatsu Terada, Yuichi Terashima, Francesco Tombesi, Hiroshi Tomida, Yoko Tsuboi, Masahiro Tsujimoto, Hiroshi Tsunemi, Takeshi Tsuru, Hiroyuki Uchida, Yasunobu Uchiyama, Hideki Uchiyama, Yoshihiro Ueda, Shiro Ueno, Shinichiro Uno, Meg Urry, Eugenio Ursino, Cor de Vries, Atsushi Wada, Shin Watanabe, Norbert Werner, Nicholas White, Takahiro Yamada, Shinya Yamada, Hiroya Yamaguchi, Noriko Yamasaki, Shigeo Yamauchi, Makoto Yamauchi, Yoichi Yatsu, Daisuke Yonetoku, Atsumasa Yoshida, Takayuki Yuasa
    Proceedings of SPIE - The International Society for Optical Engineering 8443 2012年10月16日  
    The joint JAXA/NASA ASTRO-H mission is the sixth in a series of highly successful X-ray missions initiated by the Institute of Space and Astronautical Science (ISAS). ASTRO-H will investigate the physics of the high-energy universe via a suite of four instruments, covering a very wide energy range, from 0.3 keV to 600 keV. These instruments include a high-resolution, high-throughput spectrometer sensitive over 0.3-2 keV with high spectral resolution of Delta E < 7 eV, enabled by a micro-calorimeter array located in the focal plane of thin-foil X-ray optics; hard X-ray imaging spectrometers covering 5-80 keV, located in the focal plane of multilayer-coated, focusing hard X-ray mirrors; a wide-field imaging spectrometer sensitive over 0.4-12 keV, with an X-ray CCD camera in the focal plane of a soft X-ray telescope; and a non-focusing Compton-camera type soft gamma-ray detector, sensitive in the 40-600 keV band. The simultaneous broad bandpass, coupled with high spectral resolution, will enable the pursuit of a wide variety of important science themes.

書籍等出版物

 1

講演・口頭発表等

 33
もっとみる

所属学協会

 5

共同研究・競争的資金等の研究課題

 9
もっとみる

産業財産権

 6
もっとみる

学術貢献活動

 1

● 指導学生等の数

 6
  • 年度
    2018年度(FY2018)
    博士課程学生数
    1
  • 年度
    2019年度(FY2019)
    博士課程学生数
    2
    修士課程学生数
    1
    学術特別研究員数
    1
  • 年度
    2020年度(FY2020)
    博士課程学生数
    1
    修士課程学生数
    1
    学術特別研究員数
    1
  • 年度
    2018年度(FY2018)
    博士課程学生数
    1
  • 年度
    2019年度(FY2019)
    博士課程学生数
    2
    修士課程学生数
    1
    学術特別研究員数
    1
  • 年度
    2020年度(FY2020)
    博士課程学生数
    1
    修士課程学生数
    1
    学術特別研究員数
    1

● 専任大学名

 2
  • 専任大学名
    東京大学（University of Tokyo)
  • 専任大学名
    東京大学（University of Tokyo)

● 所属する所内委員会

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