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  2. Hiroyuki Ogawa

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

 81
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Misc.

 380
  • 河合宏紀, 宮崎芳郎, 小川博之, 岩田直子
    宇宙科学技術連合講演会講演集(CD-ROM), 54th, 2010  
  • 森井雄飛, 小川洋昌, 坪井伸幸, 越光男, 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, 48th, 2010  
  • 坪井伸幸, 森井雄飛, 越光男, 林光一, 清水太郎, 小川博之
    日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集, 2010-11th, 2010  
  • IWATA NAOKO, OGAWA HIROYUKI, MIYAZAKI YOSHIRO
    Proceedings of National Heat Transfer Symposium, 47th 120-120, 2010  
  • FUKUYOSHI Fuyuko, NAGANO Hosei, OGAWA Hiroyuki, NAGAI Hiroki
    Proceedings of National Heat Transfer Symposium, 47th 239-239, 2010  
  • Okazaki Shun, Ogawa Hiroyuki
    Proceedings of National Heat Transfer Symposium, 47th 241-241, 2010  
  • IWATA Naoko, OGAWA Hiroyuki
    Proceedings of National Heat Transfer Symposium, 47th 27-27, 2010  
  • 森井雄飛, 坪井伸幸, 越光男, 小川博之, 林光一, 清水太郎
    衝撃波シンポジウム講演論文集, 2008, 2009  
  • 森井雄飛, 坪井伸幸, 越光男, 小川博之, 林光一, 清水太郎
    火薬学会年会講演要旨集, 2009, 2009  
  • 坪井伸幸, 森井雄飛, 越光男, 林光一, 清水太郎, 小川博之
    日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集, 2009-10th, 2009  
  • 日比敦士, 森井雄飛, 坪井伸幸, 越光男, 小川博之, 林光一, 清水太郎
    燃焼シンポジウム講演論文集, 47th, 2009  
  • 松田竜太, 勝身俊之, 井上朋, 澤井秀次郎, 小川博之, 水書稔治, 堀恵一
    燃焼シンポジウム講演論文集, 47th, 2009  
  • 佐藤洋一, 杉田寛之, 山脇敏彦, 中川貴雄, 塩谷圭吾, 岡本篤, 村上浩, 小川博之, 村上正秀, 高田誠, 高井茂希, 吉田誠至, 恒松正二, 金尾憲一
    日本天文学会年会講演予稿集, 2009, 2009  
  • 小川博之, 野中聡, 成尾芳博, 稲谷芳文, 吉田誠, 徳留真一郎
    宇宙科学技術連合講演会講演集(CD-ROM), 53rd, 2009  
  • 徳留真一郎, 成尾芳博, 志田真樹, 小川博之, 福吉芙由子, 八木下剛, 野中聡, 岩田直子
    宇宙科学技術連合講演会講演集(CD-ROM), 53rd, 2009  
  • 野中聡, 鈴木俊之, 小川博之, 稲谷芳文
    宇宙科学技術連合講演会講演集(CD-ROM), 53rd, 2009  
  • 森井雄飛, 日比敦士, 清水和弥, 坪井伸幸, 越光男, 小川博之, 林光一, 清水太郎
    火薬学会秋季研究発表講演会講演要旨集, 2009, 2009  
  • 福吉芙由子, 豊田裕之, 小川博之
    スペース・プラズマ研究会, 2008, 2009  
  • 杵淵紀世志, 船木一幸, 小川博之, 加藤輝雄, 太刀川純孝, 嶋田徹, 安部隆士
    航空原動機・宇宙推進講演会講演論文集(CD-ROM), 49th, 2009  
  • 坪井伸幸, 森井雄飛, 越光男, 林光一, 清水太郎, 小川博之
    航空原動機・宇宙推進講演会講演論文集(CD-ROM), 49th, 2009  
  • Miyazaki Yoshiro, Ogawa Hiroyuki, Iwata Naoko, Fukuyosi Fuyuko
    (39) 328-335, 2009  
    Spacecraft for future scientific missions demand evolutional thermal control technologies with small resources of power and weight. An accurate temperature control technology of light weight is especially important. We proposed VC-OHP (Variable Conductance Oscillating Heat Pipe) as a candidate for such a requirement. VC-OHP is a new concept of a temperature control device, which consists of an oscillating heat pipe and a reservoir. The thermal conductance of the heat pipe can be varied with assist of the reservoir and the heating section temperature can be controlled. This paper describes the analytical study on temperature control mechanism of VC-OHP.
  • Onogawa Ei, Nagano Hosei, Fukuyoshi Fuyuko, Ogawa Hiroyuki, Nagai Hiroki
    Proceedings of National Heat Transfer Symposium, 2009 348-348, 2009  
  • FUKUYOSHI FUYUKO, NAGANO HOSEI, OGAWA HIROYUKI, NAGAI HIROKI
    Proceedings of National Heat Transfer Symposium, 2009 351-351, 2009  
  • Nagai Hiroki, Nagano Hosei, Fukuyoshi Fuyuko, Ogawa Hiroyuki
    Proceedings of National Heat Transfer Symposium, 2009 356-356, 2009  
  • IWATA Naoko, OGAWA Hiroyuki, MIYAZAKI Yoshiro
    Proceedings of National Heat Transfer Symposium, 2009 82-82, 2009  
  • Satoshi Nonaka, Hiroyuki Ogawa, Yoshihiro Naruo, Yoshifumi Inatani
    PROCEEDINGS OF THE 19TH ESA SYMPOSIUM ON EUROPEAN ROCKET AND BALLOON PROGRAMMES AND RELATED RESEARCH, 671 249-254, 2009  
    A fully reusable sounding rocket is proposed in ISAS/JAXA. Vehicle systems and ground/flight operations are designed for observations of atmospheric phenomena, micro-gravity experiments and so on. In the present design of the reusable sounding rocket, the vehicle carries a 100kg payload up to 120km altitude. The turnaround time for one flight is less than 24 hours (1 day). In the typical ballistic-flight up to 120km, the total flight time is about 600sec. Maximum Mach number is about 4, and the flight condition of Mach number below 1.0 (subsonic speed) is kept for about 70sec over 110km altitude. In this subsonic flight, the observed atmosphere around the vehicle is not affected by the shock wave. This is desirable for the atmospheric observation. Maximum acceleration in the flight is about 4G in ascent and 7G in descent. For the micro-gravity experiments, the flight environments of acceleration less than 10(-3)G, 10(-4)G and 10(-5)G is able to be made for about 180, 150 and 120sec, respectively.
  • 早川基, 小川博之, 峯杉賢治, 高島健, 松岡彩子, 中澤暁, 亀田真吾, 山川宏, 笠羽康正
    日本惑星科学会秋季講演会予稿集(Web), 2009 68-68, 2009  
  • S. Sasaki, K. Tanaka, K. Higuchi, N. Okuizumi, H. Ogawa, K. Ishimura, S. Kawasaki, N. Shinohara, K. Senda, Y. Fujino
    International Astronautical Federation - 59th International Astronautical Congress 2008, IAC 2008, 9 6014-6019, 2008  
    Tethered-Solar Power Satellite (Tethered-SPS) consists of power generation/transmission panels suspended by tether wires. The most important feature of the Tethered-SPS is that it is constructed by perfectly equivalent power generation/transmission units. Each unit panel, 100 m × 95 m, is suspended by four 5 km-tether wires deployed from a bus unit. The weight and output power of the unit SPS are 42.5 MT and 2.1 MW, respectively. The engineering studies have been conducted to design the power generation/ transmission panel and to show how to deploy the panel. In addition to the engineering research, two major environmental issues, the effect of hyper-velocity impact of the debris or meteoroids and the interaction of the solar cell array with the ambient plasma, have been studied. The engineering studies have shown that the power generation/transmission panel is technically feasible using the near-term technologies. The environmental studies have shown preliminary guidelines to design the power generation/transmission panel.
  • 森井雄飛, 坪井伸幸, 越光男, 小川博之, 林光一, 清水太郎
    衝撃波シンポジウム講演論文集, 2007, 2008  
  • 森井雄飛, 坪井伸幸, 越光男, 小川博之, 林光一, 清水太郎
    燃焼シンポジウム講演論文集, 46th, 2008  
  • 坪井伸幸, 森井雄飛, 越光男, 林光一, 清水太郎, 小川博之
    流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集, 40th-2008, 2008  
  • 野中聡, 稲谷芳文, 小川博之, 藤井孝蔵, 飯塚宣行, 平木講儒, 岸光一, 関野展弘, 平井研一
    宇宙航空研究開発機構特別資料 JAXA-SP-, (07-023), 2008  
  • 小川博之, 森田泰弘, 山田哲哉, 入門朋子, 中島俊, 野中聡, 稲谷芳文
    宇宙航空研究開発機構特別資料 JAXA-SP-, (07-023), 2008  
  • 山川宏, 前田行雄, 石井信明, 小川博之, 野中聡, 山本高行, 津田雄一, 川口淳一郎, 周東三和子, 感応寺治城, 迫田幸恵, 古林剛士, 北田恒行, 渋谷彰, 大塚浩仁, 内田洋, 江西達也, 後藤晋一, 齋藤一晶, 佐藤裕彦, 櫻井博昭, 有沢雄三
    宇宙航空研究開発機構特別資料 JAXA-SP-, (07-023), 2008  
  • 野中聡, 小川博之, 稲谷芳文
    流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集, 40th-2008, 2008  
  • 小川博之
    JAXA宇宙航空技術研究発表会前刷集, 2008, 2008  
  • 福吉芙由子, 豊田裕之, 長岡洋一, 細田聡史, 田中孝治, 小川博之
    スペース・プラズマ研究会, 2007, 2008  
  • Nishida Hiroyuki, Ogawa Hiroyuki, Funaki Ikko, Yamakawa Hiroshi, Inatani Yoshifumi
    JAXA-SP-06-014(6) 111-121, Feb 1, 2007  
    Magnetic Sail is a deep space propulsion system which captures the momentum of the solar wind by a large artificial magnetic field produced around a spacecraft. To verify the momentum transfer process from the solar wind to the spacecraft, we simulated the interaction between the solar wind and the artificial magnetic field of Magnetic Sail using magnetohydrodynamic model. The result showed the same plasma flow and magnetic field structure as those of the Earth. The change of the solar wind momentum results in a pressure distribution on the magnetopause. The pressure on the magnetopause is then transferred to the spacecraft through the Lorentz force between the induced current along the magnetopause and the current along the coil of the spacecraft. The simulation successfully demonstrated that the solar wind momentum is transferred to the spacecraft via the Lorentz force. The drag coefficient (thrust coefficient) of the Magnetic Sail was estimated to be 5.0.
  • 小川 博之, 大南 香織
    ISASリサーチノート ISAS-RN-825, 1-22, 2007  
  • 小川博之
    平成18年度宇宙航行の力学シンポジウム, 83-86, 2007  
  • Hiroki Nagai, Hosei Nagano, Fuyuko Fukuyoshi, Hiroyuki Ogawa
    PROCEEDINGS OF THE ASME/JSME THERMAL ENGINEERING SUMMER HEAT TRANSFER CONFERENCE 2007, VOL 3, 721-726, 2007  
    The Loop Heat Pipes (LHPs) are robust, self-starting and a passive two-phase thermal control system that uses the latent heat of vaporization of an internal working fluid to transfer heat from an evaporator (the heat source) to a condenser (the heat sink). The circulation of the working fluid is accomplished by capillary pressure gradients in a fine porous wick with very small pores. LHPs are rapidly gaining acceptance in the aerospace community and several terrestrial applications are emerging as well.In the present study, a miniature LHP is investigated the thermal performance for spacecraft thermal control system. Tests will be conducted including start-up, low power, power ramp up, high power, rapid power change, and rapid sink temperature change. Finally, we want to demonstrate the potential of LHP to become the next-generation heat transfer device to cool terrestrial devices such as advanced electronic which have high power dissipations.First of all, this paper presents the influence of the gravitational forces on the LHP performance. The present tests performed under steady state condition with three different orientations (horizontal, gravity-assisted, anti-gravity).
  • 杉田寛之, 佐藤洋一, 岡本篤, 金森康郎, 中川貴雄, 村上浩, 小川博之, 大西晃, 金田英宏, 塩谷圭吾, 松原英雄, 片坐宏一, 岩田生, 常田佐久, 村上正秀, 恒松正二, 平林誠之
    日本天文学会年会講演予稿集, 2007, 2007  
  • 今村洋子, 野中聡, 小川博之, 稲谷芳文
    宇宙科学技術連合講演会講演集(CD-ROM), 51st, 2007  
  • 吉澤良典, 藤田和央, 小川博之, 稲谷芳文
    衝撃波シンポジウム講演論文集, 2006, 2007  
  • 吉澤良典, 藤田和央, 小川博之, 稲谷芳文
    宇宙科学技術連合講演会講演集(CD-ROM), 51st, 2007  
  • Nagano Hosei, Fukuyoshi Fuyuko, Ogawa Hiroyuki, Nagai Hiroki
    The Proceedings of the Thermal Engineering Conference, 2007 381-382, 2007  
    This paper presents an experimental study to investigate the effectiveness of using a thermoelectric converter to control the loop heat pipe operating temperature. The compensation chamber (CC) was controlled at the set point temperature by cooling and heating the TEC module, of which one side is attached to the CC and the other side is connected to the evaporator through a thermal strap. The test results show that the TEC can control the operating temperature to the set point temperature. The power saving by using the TEC was also demonstrated.
  • Satoshi Nonaka, Hiroyuki Ogawa, Yoshihiro Naruo, Nobuaki Ishii, Takumi Abe, Yoshifumi Inatani
    18TH ESA SYMPOSIUM ON EUROPEAN ROCKET AND BALLOON PROGRAMMES AND RELATED RESEARCH, 647 187-192, 2007  
    A fully reusable rocket vehicle is proposed as a sounding rocket for observations of atmospheric phenomena, micro-gravity experiments and so on. Vehicle systems and ground / flight operations are designed for such science observations. For the development of the reusable rocket, a small test vehicle was built and flight-tested. This Reusable Vehicle Testing (RVT) lessons campaign provide repeated experiences of turnaround operations and vertical take-off and landing flights. In the present design of the reusable sounding rocket, the total length and maximum diameter of the vehicle is about 10m and 3m, respectively. The vehicle is propelled by the propulsion system composed of four liquid hydrogen / liquid oxygen engines. The weight of a payload carried to 120 km altitude is 100kg in the nose-fairing. The instrument for observations can be reused because of the repeated flight. The turnaround time for one flight is less than 24 hours (1 day). In the typical ballistic flight up to 120 km, the flight environments under 10(-5)G acceleration is able to be made for about 120 sec. The flight Mach number can be subsonic around the summit in the trajectory. These properties of reusable sounding rocket are expected to be useful and effective for many science missions.
  • 杉田寛之, 中川貴雄, 村上浩, 大西晃, 小川博之
    宇宙航空研究開発機構特別資料 JAXA-SP-, (05-008), 2006  
  • Satoshi Nonaka, Koji Watanabe, Hiroyuki Ogawa, Hiroyuki Kato, Yoshifumi Inatani
    Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting, 5 3106-3114, 2006  
    A vertical take-off and vertical landing rocket is one of the future space transportation vehicle expected as fully reusable system. In the landing phase of vertical lander, the vehicle is decelerated by the main engine thrust and lands softly to the ground site. Then its aerodynamic characteristics are affected by the interaction between the engine plume and the subsonic free-stream against the vehicle. In order to investigate the influence of such interaction, wind tunnel tests were conducted. The aerodynamic forces and surface pressure were measured by using scale model of the Reusable Vehicle Testing (RVT) which is a small vehicle built for flight tests in ISAS/JAXA. Flowfield around the vehicle model was visualized by using Particle Image Velocimetry (PIV) method. As a result, the drag force and pitching moment acting the vehicle were affected by the change of pressure distribution due to the jet/free-stream interaction.
  • 吉澤良典, 藤田和央, 小川博之, 稲谷芳文
    宇宙科学技術連合講演会講演集(CD-ROM), 50th, 2006  

Books and Other Publications

 1

Presentations

 33
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Professional Memberships

 5

Research Projects

 9
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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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