研究者業績

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.


受賞

 1

論文

 95
  • Yuki Akizuki, Kimihide Odagiri, Kenichiro Sawada, Hiroshi Yoshizaki, Masahiko Sairaiji, Hiroyuki Ogawa
    Applied Thermal Engineering 264 2025年4月1日  
    A loop heat pipe is a two-phase fluid loop driven by capillary force. Fabrication of a loop heat pipe evaporator by additive manufacturing has been investigated as a low-cost, quick-delivery method for producing a high-performance loop heat pipe. This study investigated the evaporation and heat transfer performance of a wick-integrated evaporator fabricated by additive manufacturing. It is essential to understand the thermal characteristics of the evaporator for a loop heat pipe with an additive-manufactured evaporator for all applications. A tested loop heat pipe with an additive-manufactured evaporator achieved a maximum heat transport capability of 120 W (heat flux: 7.96 W/cm2) and a minimum thermal resistance of 0.321 °C/W in the horizontal orientation at a 20 °C sink temperature. The evaporative heat transfer coefficient and heat leak ratio to the reservoir were calculated for each orientation test result. The maximum evaporative heat transfer coefficient was 50 kW/m2/K and the heat leak ratio was less than 10 % between 10 W and 70 W in the horizontal orientation. These results reveal that the increase in heat leakage to the reservoir due to the decrease in the evaporative heat transfer coefficient leads to the increase in the loop heat pipe operating temperature and thermal resistance. The novelty of this study is that it clarifies the relationship between a loop heat pipe's thermal resistance and evaporator thermal performance by correlating the evaporative heat transfer coefficient and the heat leakage of the wick-integrated evaporator, which uses additive manufacturing, based on the heat transport test results in each orientation.
  • Masaru Hirata, Yuki Akizuki, Kimihide Odagiri, Hiroyuki Ogawa
    International Journal of Thermal Sciences 207 2025年1月  
    A cryogenic capillary pumped loop (CCPL) is a highly efficient two-phase capillary-force-driven heat transport device that operates at cryogenic temperatures. CCPL satisfies the demands for space applications in cryogenic regions as it can transport heat over long distances without mechanical moving parts. In this study, the transient internal flow during the supercritical startup of CCPL was predicted, and various temperature relationships were used to determine whether CCPL starts up or not. The utilized CCPL comprised a wick (pore radius = 1.0 μm), exhibited a heat transport distance of 2 m, and was filled with nitrogen as the working fluid. The supercritical startup experiments were performed at a temperature range of 77–300 K; the startup procedure was initiated when the maximum temperature of CCPL decreased to ∼150 K. Three different liquid supply cycles were tested during the supercritical startup, and the startup time was reduced (a maximum and minimum of 4.1 and 1.9 h, respectively). CCPL started when the evaporator temperature was below the cold reservoir temperature. Thus, the temperature relationship between the cold reservoir and evaporator at the time of applying the heat load to the evaporator could be used to determine the possibility of starting CCPL. The startup was considered successful when the cold reservoir temperature was higher than the evaporator temperature, as the cold reservoir, which exhibited a two-phase state, supplied sufficient liquid to the evaporator, filling the inside of the evaporator with liquid.
  • Takeshi Yokouchi, Xinyu Chang, Kimihide Odagiri, Hiroyuki Ogawa, Hosei Nagano, Hiroki Nagai
    International Journal of Heat and Mass Transfer 231 2024年10月  
    This paper investigated the effect of filling pressure on the operating characteristics of a gravity-assisted cryogenic loop heat pipe(CLHP) for use in gravity environments such as terrestrial and lunar environments. The CLHP wick is made of sintered stainless-steel fibers with a pore radius of 1.56 μm and designed with a heat transport distance of 2.05 m. The experiments were conducted under gravity-assisted conditions (the condenser was placed 0.1 m higher than the evaporator). Notably, the filling pressure originated from the assumed vapor-liquid distribution in the CLHP under steady-state conditions. The filling pressure was varied from 2.9 MPa to 3.4 MPa in 0.1 MPa increments for six different conditions. Specifically, (1) 2.9 MPa and (2) 3.0 MPa are conditions where the heat leakage due to the vapor phase in the evaporator core is large, while (3) 3.1 MPa and (4) 3.2 MPa are conditions where there is no vapor phase in the evaporator core and the surplus vapor phase escapes to the CC. In general, this condition is considered to be the optimum amount of working fluid for room-temperature LHPs when designing. (5) 3.3 MPa and (6) 3.4 MPa are overfilling conditions that cause the CC to be filled with liquid. The results revealed that the higher the filling pressure, the more obvious the variation in operating temperature caused by the transition of drive modes. The maximum heat transfer capability reached 25 W in cases (1)-(4). In cases (5) and (6), the heat transfer capabilities increased to 30 W, although the operating temperature was higher. Furthermore, the hysteresis effect under different filling pressure conditions was newly confirmed. The power cycling experiments demonstrated that hysteresis in the operating temperature occurred at high heat loads and showed a similar trend to the room-temperature LHP.
  • Hideyuki FUKE, Shun OKAZAKI, Akiko KAWACHI, Manami KONDO, Masayoshi KOZAI, Hiroyuki OGAWA, Masaru SAIJO, Kakeru TOKUNAGA
    Journal of Evolving Space Activities 2 156 2024年7月25日  査読有り
  • Kimihide Odagiri, Xinyu Chang, Hiroki Nagai, Hiroyuki Ogawa
    Applied Thermal Engineering 255 123878-123878 2024年7月  
    One of the main advantages of a cryogenic loop heat pipe (CLHP) is its heat transfer capability over long distances and operability under anti-gravity conditions. However, there are only a few studies on the thermal characteristics of long-distance CLHPs. It is essential to investigate the effect of a hydraulic head on CLHP performance to enhance the utilization of CLHPs in various applications. This study investigated the thermofluidic behaviors of a 2-m nitrogen CLHP with a capillary starter pump (CSP) under horizontal and anti-gravity conditions where the evaporator was 350 mm higher than the condenser. The novelty of the study is to reveal the heat transfer characteristics and operating mechanisms under anti-gravity conditions based on comparisons with experimental results under horizontal conditions. In the CLHP, a fine stainless-steel porous wick with a pore radius of 1.0 μm and permeability of 1.3 × 10−13 m2 was used for an evaporator and the CSP. The lengths of the vapor line, condenser, and liquid line were 2000, 1500, and 2000 mm, respectively. When a heat load of 4 W was applied to the CSP and evaporator, the CLHP successfully started with an initial cooling condition called a supercritical startup under anti-gravity conditions. The startup temperature behaviors were compared under horizontal and anti-gravity conditions. The thermal resistance of the CLHP with a stepped-up evaporator heat load and various CSP heat loads was evaluated for two CLHP orientations. The CLHP stably operated under evaporator heat loads of 4–24 W (horizontal) and 4–20 W (anti-gravity) for three CSP heat loads of 0, 2, and 4 W. The effect of the CLHP orientation on the thermal resistance with various CSP heat loads is discussed. This study enhances the applicability of the long-distance CLHP to various applications with a high degree of postural freedom by revealing the operating mechanism and thermal characteristics of the long-distance CLHP under anti-gravity and horizontal conditions.

MISC

 382
  • 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.
  • Naoko Iwata, Takashi Usui, Akihiko Miki, Yukihiro Kaizu, Mizuho Ikeda, Hiroyuki Ogawa, Tadayuki Takahashi
    42nd International Conference on Environmental Systems 2012年7月  筆頭著者
  • Hiroyuki Ogawa, Tsutomu Yamazaki, Akira Okamoto, Naoko Iwata, Shun Okazaki
    42nd International Conference on Environmental Systems 2012年7月  筆頭著者
  • 森井雄飛, 坪井伸幸, 小川博之, 寺島洋史, 徳留真一郎, 林光一
    衝撃波シンポジウム講演論文集 2011 2012年  
  • 小川博之
    日本航空宇宙学会年会講演会講演集(CD-ROM) 43rd 2012年  
  • 岡崎峻, 福家英之, 宮崎芳郎, 大久保卓磨, 小川博之
    日本混相流学会年会講演会講演論文集 2012 2012年  
  • 宮崎芳郎, 河合宏紀, 岩田直子, 小川博之, 福田盛介
    宇宙科学技術連合講演会講演集(CD-ROM) 56th 2012年  
  • 小川博之, 横澤裕, 岡本章, 宮崎慈, 大貫弘和
    宇宙科学技術連合講演会講演集(CD-ROM) 56th 2012年  
  • 長野方星, 岡崎裕幸, 野津亮太, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 56th 2012年  
  • 岡崎峻, 福家英之, 宮崎芳郎, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 56th 2012年  
  • 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) 56th 2012年  
  • 井手陽介, 佐々木敦志, 石川佳太郎, 川戸博史, 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) 56th 2012年  
  • 矢部高宏, 畠中龍太, 杉田寛之, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 56th 2012年  
  • 小川博之, 野中聡
    宇宙科学技術連合講演会講演集(CD-ROM) 56th 2012年  
  • 岩田直子, 小川博之, 宮崎芳郎
    日本伝熱シンポジウム講演論文集(CD-ROM) 49th 2012年  
  • 宮崎芳郎, 河合宏紀, 岩田直子, 小川博之, 福田盛介
    日本伝熱シンポジウム講演論文集(CD-ROM) 49th 2012年  
  • 奥谷翔, 長野方星, 岡崎俊, 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) 49th 2012年  
  • 岩田直子, 臼井隆, 池田瑞穂, 湯本隆宏, 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) 56th 2012年  
  • 西川原理仁, 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) 56th 2012年  
  • Atsushi Sasaki, Keitaro Ishikawa, Hiroshi Kawato, Tatsuru Tokunaga, Takashi Ito, Satoshi Nonaka, Hiroyuki Ogawa
    Proceedings of the International Astronautical Congress, IAC 11 8842-8847 2012年  
    A new reusable sounding rocket is proposed (1) to reduce operation costs from that of existing expendable sounding rockets and (2) to provide frequent launch opportunities. This paper describes the current status of the conceptual design of the reusable sounding rocket, including system concept, mission profile and system configuration. Some of the R&D status is also presented. Copyright © (2012) by the International Astronautical Federation.
  • Ryuta Hatakenaka, Takahiro Yabe, Naoko Iwata, Hiroyuki Ogawa, Masanori Saitoh
    42nd International Conference on Environmental Systems 2012, ICES 2012 2012年  
    The inflation and peel-off characteristics of a multilayer insulation (MLI) blanket under a depressurization environment have been evaluated for establishing a JAXA design standard. The venting conductance of gas flow from inside to the outside of MLI was evaluated in a steady state test, and was confirmed to take a value of the same level regardless of shape or size or pressure level when having the same perforation, spacer type, and attachment specification. In the depressurization test, MLI was observed as not inflating in a region of higher pressure even at higher depressurization speed, while inflating in a lower pressure region. The differential pressure between the inside and outside of MLI peaks when the level of pressure drops to about one kilo pascal or less. In addition, a simple mathmatical model of MLI inflation and venting is constructed and numerical simulations based on the model are conducted, which indicate that depressurization ratio (depressurization speed per the level of pressure) and volume of MLI are the dominantparameters. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
  • 野田博文, 内山秀樹, 中澤知洋, 牧島一夫, 川原田円, 太田方之, 渡辺伸, 国分紀秀, 高橋忠幸, 岩田直子, 小川博之, 大野雅功, 深沢泰司, 田島宏康
    日本物理学会講演概要集 67(1) 139-139 2012年  
  • 大野雅功, 野田博文, 太田方之, 上野一誠, 深沢泰司, 田島宏康, 中澤知洋, 牧島一夫, 渡辺伸, 国分紀秀, 高橋忠幸, 岩田直子, 小川博之
    日本物理学会講演概要集 67(1) 140-140 2012年  
  • Hiroyuki Ogawa, Tsutomu Yamazaki, Akira Okamoto, Naoko Iwata, Shun Okazaki, Tomoko Irikado, Fuyuko Fukuyoshi
    41st International Conference on Environmental Systems AIAA-2011-518 2011年7月  筆頭著者
  • MORII Youhi, OGAWA Yousuke, TSUBOI Nobuyuki, OGAWA Hiroyuki, TOKUDOME Shinichiro, HAYASHI A.Koichi
    火薬学会秋季研究発表講演会講演要旨集 2011 2011年  
  • 大山聖, 永井大樹, 竹内伸介, 豊田裕之, 砂田茂, 得竹浩, 小川博之, 戸田和朗, 小池勝, 元田敏和, 藤田和央
    日本航空宇宙学会年会講演会講演集(CD-ROM) 42nd 2011年  
  • 森井雄飛, 小川洋昌, 坪井伸幸, 小川博之, 徳留真一郎, 林光一
    火薬学会年会講演要旨集 2011 2011年  
  • 小川博之
    ISASニュース (369) 2011年  
  • 岡崎峻, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 岩田直子, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 川崎春夫, 岡本篤, 杉田寛之, 小川博之, 田中好和, 三井浩一, 金森康郎, 加藤秀, 関時明, 小林孝
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 嶋田貴信, 豊田裕之, 久木田明夫, 今泉充, 廣瀬和之, 小川博之, 前島弘則, 早川基, 田島道夫, 渡部浩一, 野崎幸重, 岡本章, 久松正, 島田啓二, 中村一世, 高本達也
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 河合宏紀, 宮崎芳郎, 岩田直子, 小川博之
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 畠中龍太, 斎藤雅規, 矢部高宏, 岩田直子, 小川博之, 川崎春夫, 杉田寛之
    宇宙科学技術連合講演会講演集(CD-ROM) 55th 2011年  
  • 森井雄飛, 坪井伸幸, 小川博之, 徳留真一郎, 林光一
    燃焼シンポジウム講演論文集 49th 2011年  
  • 永井大樹, 玉村大道, 真籠耕平, 長野方星, 小川博之
    日本混相流学会年会講演会講演論文集 2011 2011年  
  • 黒井正和, 長野方星, 岡本篤, 小川博之
    日本混相流学会年会講演会講演論文集 2011 2011年  
  • 岩田直子, 小川博之, 宮崎芳郎
    Thermophysical Properties 32nd 2011年  
  • 森井雄飛, 坪井伸幸, 小川博之, 徳留真一郎, 林光一
    数値流体力学シンポジウム講演論文集(CD-ROM) 25th 2011年  
  • 野田博文, 牧島一夫, 中澤知洋, 桜井壮希, 笹野理, 中野俊男, 田島宏康, 田中孝明, 榎戸輝揚, 高橋忠幸, 国分紀秀, 渡辺伸, 小川博之, 岩田直子, 深沢泰司
    日本物理学会講演概要集 66(1) 122-122 2011年  
  • 野田博文, 牧島一夫, 中澤知洋, 田島宏康, 田中孝明, 榎戸輝揚, 高橋忠幸, 国分紀秀, 渡辺伸, 小川博之, 岩田直子, 深沢泰司, 大野雅功
    日本物理学会講演概要集 66(2) 113-113 2011年  
  • Satoshi Nonaka, Hiroyuki Ogawa, Yoshihiro Naruo, Yoshifumi Inatani
    20TH ESA SYMPOSIUM ON EUROPEAN ROCKET AND BALLOON PROGRAMMES AND RELATED RESEARCH 700 137-142 2011年  
    A fully reusable sounding rocket is proposed in ISAS/JAXA. Vehicle systems and ground / flight operations are conceptually designed for observations of atmospheric phenomena, micro-gravity experiments and so on. The present design of the reusable sounding rocket is summarized. In phase A in the proposed reusable sounding rocket project, technical demonstrations for key technologies to develop the reusable sounding rocket are planed as follows; 1) reusable engine development and repeated engine operation development, 2) reusable insulation development for cryogenic tank, 3) aerodynamic design and flight demonstration for returning flight, 4) fuel/oxidizer management demonstration, 5) landing gear development and 6) health management system construction.
  • 河合宏紀, 宮崎芳郎, 岩田直子, 小川博之
    日本伝熱シンポジウム講演論文集(CD-ROM) 48th 93-93 2011年  査読有り
    自励振動ヒートパイプの動作限界に関する理論を提案し、実験により検証を行っている。理論の概要は以下の通りである:自励振動ヒートパイプは圧力とボイド率の相互作用により、熱力学サイクルを構成し、このサイクルによって得られる仕事により、振動流が発生する。得られる仕事は圧力とボイド率の位相差が90度のときにもっとも高く、位相差が180度で仕事の発生はなくなる。位相差は流速が大きくなるとともに大きくなるので、流速には仕事の発生の低下による限界があり、これが自励振動ヒートパイプの作動限界となる。
  • Tadayuki Takahashi, Kazuhisa Mitsuda, Richard Kelley, Felix Aharonian, Fumie Akimoto, Steve Allen, Naohisa Anabuki, Lorella Angelini, Keith Arnaud, Hisamitsu Awaki, Aya Bamba, Nobutaka Bando, Mark Bautz, Roger Blandford, Kevin Boyce, Greg Brown, Maria Chernyakova, Paolo Coppi, Elisa Costantini, Jean Cottam, John Crow, Jelle de Plaa, Cor de Vries, Jan-Willem den Herder, Michael DiPirro, Chris Done, Tadayasu Dotani, Ken Ebisawa, Teruaki Enoto, Yuichiro Ezoe, Andrew Fabian, Ryuichi Fujimoto, Yasushi Fukazawa, Stefan Funk, Akihiro Furuzawa, Massimiliano Galeazzi, Poshak Gandhi, Keith Gendreau, Kirk Gilmore, Yoshito Haba, Kenji Hamaguchi, Isamu Hatsukade, Kiyoshi Hayashida, Junko Hiraga, Kazuyuki Hirose, Ann Hornschemeier, John Hughes, Una Hwang, Ryo Iizuka, Kazunori Ishibashi, Manabu Ishida, Kosei Ishimura, Yoshitaka Ishisaki, Naoki Isobe, Masayuki Ito, Naoko Iwata, Jelle Kaastra, Timothy Kallman, Tuneyoshi Kamae, Hideaki Katagiri, Jun Kataoka, Satoru Katsuda, Madoka Kawaharada, Nobuyuki Kawai, Shigeo Kawasaki, Dmitry Khangaluyan, Caroline Kilbourne, Kenzo Kinugasa, Shunji Kitamoto, Tetsu Kitayama, Takayoshi Kohmura, Motohide Kokubun, Tatsuro Kosaka, Taro Kotani, Katsuji Koyama, Aya Kubota, Hideyo Kunieda, Philippe Laurent, Francois Lebrun, Olivier Limousin, Michael Loewenstein, Knox Long, Grzegorz Madejski, Yoshitomo Maeda, Kazuo Makishima, Maxim Markevitch, Hironori Matsumoto, Kyoko Matsushita, Dan McCammon, Jon Miller, Shin Mineshige, Kenji Minesugi, Takuya Miyazawa, Tsunefumi Mizuno, Koji Mori, Hideyuki Mori, Koji Mukai, Hiroshi Murakami, Toshio Murakami, Richard Mushotzky, Yujin Nakagawa, Takao Nakagawa, Hiroshi Nakajima, Takeshi Nakamori, Kazuhiro Nakazawa, Yoshiharu Namba, Masaharu Nomachi, Steve O' Dell, Hiroyuki Ogawa, Mina Ogawa, Keiji Ogi, Takaya Ohashi, Masanori Ohno, Masayuki Ohta, Takashi Okajima, Naomi Ota, Masanobu Ozaki, Frits Paerels, Stéphane Paltani, Arvind Parmer, Robert Petre, Martin Pohl, Scott Porter, Brian Ramsey, Christopher Reynolds, Shin-ichiro Sakai, Rita Sambruna, Goro Sato, Yoichi Sato, Peter Serlemitsos, Maki Shida, Takanobu Shimada, Keisuke Shinozaki, Peter Shirron, Randall Smith, Gary Sneiderman, Yang Soong, Lukasz Stawarz, Hiroyuki Sugita, Andrew Szymkowiak, Hiroyasu Tajima, Hiromitsu Takahashi, Yoh Takei, Toru Tamagawa, Takayuki Tamura, Keisuke Tamura, Takaaki Tanaka, Yasuo Tanaka, Yasuyuki Tanaka, Makoto Tashiro, Yuzuru Tawara, Yukikatsu Terada, Yuichi Terashima, Francesco Tombesi, Hiroshi Tomida, Miyako Tozuka, Yoko Tsuboi, Masahiro Tsujimoto, Hiroshi Tsunemi, Takeshi Tsuru, Hiroyuki Uchida, Yasunobu Uchiyama, Hideki Uchiyama, Yoshihiro Ueda, Shinichiro Uno, Meg Urry, Shin Watanabe, Nicholas White, Takahiro Yamada, Hiroya Yamaguchi, Kazutaka Yamaoka, Noriko Yamasaki, Makoto Yamauchi, Shigeo Yamauchi, Yoichi Yatsu, Daisuke Yonetoku, Atsumasa Yoshida
    SPACE TELESCOPES AND INSTRUMENTATION 2010: ULTRAVIOLET TO GAMMA RAY 7732 2010年10月24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 by performing high-resolution, high-throughput spectroscopy with moderate angular resolution. ASTRO-H covers very wide energy range from 0.3 keV to 600 keV. ASTRO-H allows a combination of wide band X-ray spectroscopy (5-80 keV) provided by multilayer coating, focusing hard X-ray mirrors and hard X-ray imaging detectors, and high energy-resolution soft X-ray spectroscopy (0.3-12 keV) provided by thin-foil X-ray optics and a micro-calorimeter array. The mission will also carry an X-ray CCD camera as a focal plane detector for a soft X-ray telescope (0.4-12 keV) and a non-focusing soft gamma-ray detector (40-600 keV) . The micro-calorimeter system is developed by an international collaboration led by ISAS/JAXA and NASA. The simultaneous broad bandpass, coupled with high spectral resolution of Delta E ~7 eV provided by the micro-calorimeter will enable a wide variety of important science themes to be pursued.
  • Shun Okazaki, Hiroyuki Ogawa
    40th International Conference on Environmental Systems AIAA-2010-6056 2010年7月  
  • Hiroyuki OGAWA, Tsutomu YAMAZAKI, Akira OKAMOTO, Shigeru MIYAZAKI, Hirokazu OHNUKI, Fuyuko Fukuyoshi, Naoko Iwata
    40th International Conference on Environmental Systems AIAA-2010-6089 2010年7月  
  • T. Shimada, H. Toyota, A. Kukita, M. Imaizumi, K. Hirose, M. Tajima, H. Ogawa, H. Hayakawa, A. Okamoto, Y. Nozaki, H. Watabe, T. Hisamatsu
    Conference Record of the IEEE Photovoltaic Specialists Conference 1112-1117 2010年  査読有り
    The Japan Aerospace Exploration Agency has been developing the Mercury Magnetospheric Orbiter (MMO), which is Japanese part of the BepiColombo mission. During its mission around Mercury, the spacecraft will be exposed to high solar irradiance of up to 11 suns, with an estimated maximum solar panel temperature of 230°C. In such an environment, solar cells are required to operate under high intensity and high temperature (HIHT) conditions. Therefore, it is necessary to evaluate the durability of solar cells to meet the power requirements throughout the mission life. We conducted a continuous operation test under HIHT conditions to examine the validity of the solar array configuration, using the interior planetary thermal vacuum chamber. Our HIHT tests clarified the following facts: (i) Transparency of the coverglass and the performance of the solar cells do not degrade and (ii) transparency of the DC93-500 adhesive in the top cell response region degrades mainly due to ultraviolet exposure at high temperatures. We decided to use AR0213 coverglass (from JDSU) with a thickness of 300 μm, which have a longer cut-on wavelength in ultraviolet region. With this configuration, the predicted decrease in Pmax due to the HIHT environment is 17.3% and that due to radiation effects is 11.0% Our new design will offer the available power at EOL of 394.2 W, which is 46.7 W greater than the required power. © 2010 IEEE.
  • 森井雄飛, 坪井伸幸, 越光男, 小川博之, 徳留真一郎
    衝撃波シンポジウム講演論文集 2009 2010年  
  • Hosei Nagano, Fuyuko Fukuyoshi, Hiroyuki Ogawa, Hiroki Nagai
    40th International Conference on Environmental Systems, ICES 2010 2010年  査読有り
    This paper reports development of an experimental small LHP with PTFE wick. PTFE porous materials with 0.8 - 2.2 μm pore radius were fabricated and the basic properties were evaluated. An experimental small LHP with the PTFE wicks was designed and tested in an atmospheric condition. A PTFE wick with 1.2 μm pore radius was used to demonstrate the loop performance. The test results showed excellent operating characteristics of the LHP. © 2010 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

書籍等出版物

 1

講演・口頭発表等

 33

共同研究・競争的資金等の研究課題

 10

産業財産権

 6

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