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  2. 小林 弘明

小林 弘明

コバヤシ ヒロアキ  (Hiroaki Kobayashi)

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
工学博士(東京大学)
J-GLOBAL ID
200901061542880861
researchmap会員ID
5000019456

研究分野

 1

経歴

 8
もっとみる

学歴

 1

委員歴

 2

論文

 174
  • Takayuki Kojima, Hideyuki Taguchi, Syunsuke Imamura, Hiroaki Kobayashi, Atsushi Ueno, Tomonari Hirotani, Keisuke Fujii, Mitsuharu Tsukamoto
    17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 2011年  
  • Masamitsu Watanabe, Hitomi Iizuka, Takato Goto, Ayumu Hirayama, Tetsuya Sato, Hiroaki Kobayashi, Hideyuki Taguchi, Kenya Harada
    62nd International Astronautical Congress 2011, IAC 2011 8 6660-6667 2011年  
  • 渡辺 和樹, 井上 拓郎, 柁川 一弘, 金澤 昌哉, 山田 豊, 小林 弘明, 田口 秀之, 青木 五男
    電気関係学会九州支部連合大会講演論文集 2011 34-34 2011年  
    現在、液体水素の残量を外部から高精度、高信頼度を持って判断できる技術は確立されていない。そこで、我々のグループでは、超電導線と非超電導線を用いた新構造液体水素用液面計を提案している。この液面計は従来構造液面計に非超電導線を回路的に直列に配置したもので、超電導の発生電圧と非超電導線の差分を取ることで、高精度に液面を計測することが可能である。非超電導線は線引き加工後の未熱処理線を用いた。そして、SUSシースMgB2線とこの未熱処理線を用いて液面計を試作し、液体水素中で動作模擬試験を行った。また、数値解析により実験結果の再現を試みた。
  • Hideyuki Taguchi, Hiroaki Kobayashi, Takayuki Kojima, Atsushi Ueno, Shunsuke Imamura, Motoyuki Hongoh, Kenya Harada, Takeshi Tsuchiya
    17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 2011年  査読有り
  • Yasuyuki Shirai, Hideki Tatsumoto, Masahiro Shiotsu, Koichi Hata, Hiroaki Kobayashi, Yoshihiro Naruo, Yoshifumi Inatani
    CRYOGENICS 50(6-7) 410-416 2010年6月  査読有り
  • 吹場 活佳, 坪井 伸幸, 小林 弘明
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 58(676) 130-137 2010年5月5日  
    Numerical simulation on the Air Data Sensor System (ADS), which measures the flow angles and Mach number using the surface pressures on a nose cone, was conducted in this study. The effect of the half cone angle on the flow angle and Mach number measurement was investigated. As a result, we found that a large half cone angle achieves a high sensitivity at the flow angle measurement. It was also found that a small half cone angle achieves a high sensitivity at the Mach number measurement. To satisfy these conflicting requests, we proposed a new shape nose cone which has two different gradients. The high sensitivity was achieved at both the flow angle measurement and Mach number measurement by this new shape nose cone.
  • Tetsuya Sato, Hideyuki Taguchi, Hiroaki Kobayashi, Takayuki Kojima, Katsuyoshi Fukiba, Daisaku Masaki, Keiichi Okai, Kazuhisa Fujita, Motoyuki Hongo, Shujiro Sawai
    ACTA ASTRONAUTICA 66(7-8) 1169-1176 2010年4月  査読有り
  • Hiroaki Kobayashi, H. Taguchi, T. Kojima, Y. Maru, S. Sawai, T. Sato
    61st International Astronautical Congress 2010, IAC 2010 9 7500-7507 2010年  
  • Hideyuki Taguchi, Hiroaki Kobayashi, Takayuki Kojima, Atsushi Ueno, Shunsuke Imamura, Motoyuki Hongoh, Kenya Harada
    61st International Astronautical Congress 2010, IAC 2010 9 7494-7499 2010年  
  • H. Tatsumoto, Y. Shirai, M. Shiotsu, K. Hata, H. Kobayashi, Y. Naruo, Y. Inatani, T. Kato, M. Futakawa, K. Kinoshita
    Journal of Physics: Conference Series 234(PART 3) 2010年  査読有り
  • Y. Shirai, H. Tatsumoto, K. Hata, M. Shiotsu, H. Kobayashi, Y. Naruo, Y. Inatani
    AIP Conference Proceedings 1218(Pt.A) 337-344 2010年  査読有り
  • 小川 正倫, 佐藤 哲也, 小林 弘明, 田口 秀之
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 57(670) 453-460 2009年11月5日  
    The aim of this paper is to apply a multi-objective optimization generic algorithm (MOGA) to the conceptual design of the hypersonic/supersonic vehicles with different cruise Mach number. The pre-cooled turbojet engine is employed as a propulsion system and some engine parameters such as the precooler size, compressor size, compression ratio and fuel type are varied in the analysis. The result shows that the optimum cruise Mach number is about 4 if hydrogen fuel is used. Methane fuel instead of hydrogen reduces the vehicle gross weight by 33% in case of the Mach 2 vehicle.
  • H. Hirai, Y. Suzuki, M. Hirokawa, H. Kobayashi, Y. Kamioka, M. Iwakuma, Y. Shiohara
    Physica C: Superconductivity and its Applications 469(15-20) 1857-1861 2009年10月15日  査読有り
  • 小林 弘明, 田口 秀之, 澤井 秀次郎, 藤田 和央, 小島 孝之, 岡井 敬一, 本郷 素行, 正木 大作, 石塚 只夫, 原田 賢哉, 丸 祐介, 二村 尚夫, 柳 良二
    宇宙航空研究開発機構研究開発報告 8(08-012) 1-25 2009年3月  
    JAXA では,マッハ5 クラスの極超音速機へ搭載するための極超音速ターボジェットエンジンの開発研究を進めている.このエンジンの特徴は,液体水素燃料の冷熱を利用して圧縮機入口の空気を冷却する空気予冷却サイクルを採用している点にあり,これによって従来のターボジェットエンジンでは動作不可能な極超音速飛行が可能になる.現在,推力100 kgf 級のサブスケールエンジンを製作し,飛行実験機搭載形態での地上燃焼試験を実施している.本稿では,極超音速ターボジェットエンジンの飛行実験用に開発した搭載型エンジン制御装置の設計と,地上実験による性能確認結果を示す.
  • 小林 弘明, 澤井 秀次郎, 坂東 信尚, 坂井 真一郎, 石川 穀彦, 稲富 裕光, 藤田 和央, 丸 祐介, 橋本 樹明
    宇宙航空研究開発機構研究開発報告 8(08-005) 1-24 2009年3月  
    現在JAXA では,高々度気球からの自由落下を利用した微小重力実験装置の開発が進められている.この装置の特徴は,独特の二重殻構造を持つ点にあり,気球からの自由落下中に,内側の実験部を機体内部で浮遊させることで,30 秒から60 秒の良質な微小重力環境が得られる.落下中の機体姿勢制御,および実験部と機体内壁の隙間制御用に,合計16 基の50N 級コールドガスジェットスラスタが搭載されている.本稿では,微小重力実験装置用に開発されたガスジェットスラスタの設計と,その地上性能試験結果,飛行試験による実証結果について示す.
  • 丸 祐介, 澤井 秀次郎, 橋本 樹明, 坂井 真一郎, 坂東 信尚, 福家 英之, 藤田 和央, 小林 弘明, 小島 孝之, 田口 秀之, 上野 誠也, 宮路 幸二, 門岡 昇平
    JASMA : Journal of the Japan Society of Microgravity Application 26(1) 43-50 2009年1月31日  
  • 坂東 信尚, 坂井 真一郎, 澤井 秀次郎, 星野 慎二, 田島 賢一, 門岡 昇平, 橋本 樹明, 上野 誠也, 曽子 隆博, 小林 弘明, 藤田 和央, 石川 穀彦, 稲富 裕光
    JASMA : Journal of the Japan Society of Microgravity Application 26(1) 29-35 2009年1月31日  
  • 澤井 秀次郎, 橋本 樹明, 坂井 真一郎, 坂東 信尚, 吉光 徹雄, 石川 毅彦, 稲富 裕光, 福家 英之, 鎌田 幸男, 長江 朋子, 小林 弘明, 藤田 和央, 小島 孝之, 上野 誠也, 宮路 幸二, 門岡 昇平, 平木 講儒, 鈴木 宏二郎, 上原 聡
    JASMA : Journal of the Japan Society of Microgravity Application 26(1) 21-28 2009年1月31日  
  • 橋本 樹明, 澤井 秀次郎, 坂井 真一郎, 坂東 信尚, 小林 弘明, 石川 毅彦, 稲富 裕光, 藤田 和央, 吉光 徹雄, 斎藤 芳隆, 福家 英之
    JASMA : Journal of the Japan Society of Microgravity Application 26(1) 9-14 2009年1月31日  
  • Takayuki Kojima, Hiroaki Kobayashi, Hideyuki Taguchi, Ken Goto, Tetsuya Sato
    16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 2009年  
  • Akiko Hasegawa, Katsuyoshi Otsuka, Hitomi Lizuka, Masamitsu Watanabe, Tetsuya Sato, Hiroaki Kobayashi, Hideyuki Taguchi
    60th International Astronautical Congress 2009, IAC 2009 8 6442-6450 2009年  
  • Tatsuaki Hashimoto, Shujiro Sawai, Shin'ichiro Sakai, Nobutaka Bando, Hiroaki Kobayashi, Kazuhisa Fujita, Yuko Inatom, Takehiko Ishikawa, Tetsuo Yoshimitsu, Yoshitaka Saito
    60th International Astronautical Congress 2009, IAC 2009 1 725-730 2009年  査読有り
  • 澤井 秀次郎, 橋本 樹明, 坂井 真一郎, 坂東 信尚, 小林 弘明, 藤田 和央, 吉光 徹雄, 石川 毅彦, 稲富 裕光, 福家 英之, 鎌田 幸男, 星野 慎二, 田島 賢一, 門岡 昇平, 上原 聡, 小島 孝之, 上野 誠也, 宮路 幸二, 坪井 伸幸, 平木 講儒, 鈴木 宏二郎, 松嶋 清穂, 中田 孝
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 56(654) 339-346 2008年7月5日  
    Rocket-shaped vehicle is developed to conduct microgravity experiment by dropping from the high-altitude balloon. Its design strategy and development status is introduced. Also, the result of its 2nd flight test is summarized to show the feasibility of the balloon-based microgravity experiment.
  • 吹場 活佳, 佐藤 哲也, 小林 弘明, 大久保 英敏
    日本冷凍空調学会論文集 25(2) 97-106 2008年6月30日  
  • 稲富 裕光, 神保 至, 石川 毅彦, 橋本 樹明, 澤井 秀次郎, 斉藤 芳隆, 吉光 徹雄, 坂井 真一郎, 小林 弘明, 藤田 和央, 坂東 信尚, 後藤 雅享, 山川 宏
    宇宙航空研究開発機構研究開発報告 7(07-009) 23-33 2008年2月  
    ドラッグフリー技術に基づいた新しい自由落下カプセルを,2006年5月に高高度気球B200を用いて高度40km から投下し,微小重力実験が行われた。今回の最初の試験飛行により,三陸大気球観測所の制御室とカプセルとの間での無線通信,ドラッグフリー制御,そして飛行シーケンスを分析するための基本的データを得ることに成功した.
  • 石川 毅彦, 稲富 裕光, 橋本 樹明, 澤井 秀次郎, 斎藤 芳隆, 吉光 徹雄, 坂井 真一郎, 小林 弘明, 藤田 和央, 坂東 信尚, 後藤 雅享
    JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 25(1) 3-10 2008年1月31日  
  • Takayuki Kojima, Hiroaki Kobayashi, Hideyuki Taguchi, Katsuyoshi Fukiba, Kazuhisa Fujita, Hiroshi Hatta, Ken Goto, Takuya Aoki, Tetsuya Sato
    15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2008年  
  • 吹場 活佳, 佐藤 哲也, 小林 弘明, 大久保 英敏
    日本冷凍空調学会論文集 25(2) 97-106 2008年  
    The Japan Aerospace Exploration Agency has developed a hypersonic aircraft flying at Mach 5. A precooled turbojet engine is the candidate of the engine for the hypersonic aircraft. The precooled turbojet engine has a heat exchanger(precooler) which cools the breathed air by using cryogenic propellant, such as liquid hydrogen. The precooler has a problem that frost forms on the cooling tubes of the precooler, and the frost decrease the engine performance. Some approaches to deal with the frost formation problem have employed in the development. In this paper, those approaches are introduced and the results of some fundamental studies about frost are also shown.
  • 鈴木 広一, 苅田 丈士, 甲斐 高志, 小林 弘明, 高嵜 浩一, 廣谷 智成, 倉谷 尚志
    宇宙航空研究開発機構研究開発報告 7 1-20 2008年1月  
    宇宙航空研究開発機構では,将来の宇宙輸送システムコンセプトの絞り込み,開発すべき技術課題の抽出,および現状技術の改善目標を設定するため,概念設計ツール(Systems Evaluation and Analysis Tool: SEAT)を開発中である。本報告書では,まずSEAT開発の目的,開発シナリオをまとめ,開発した雛形ツールについて報告する。ついで,代表的なエンジンの評価を行うため,雛形ルールを用いて5種類の宇宙輸送システムの概念設計を行った。本報告書では,液体ロケットエンジン,Turbine-Based Combined Cycle(TBCC)エンジン,およびRocket-Based Combined Cycle(RBCC)エンジンを対象とした。概念設計は,全備重量が最小となるように行った。その結果,母機,軌道機共にロケットエンジンを使用する二段式宇宙往還機のコンセプトが,最も軽量となる結果が得られた,本システムはエンジン搭載性についても問題がなく,最も現実的なシステムである。TBCCエンジンやRBCCエンジンといった空気吸い込み式のエンジンを使用する場合には,必要なエンジン基数が多くなり,その搭載性に問題があるという結果が得られた。
  • Katsuyoshi Fukiba, Tetsuya Sato, Nobuyuki Tsuboi, Hiroaki Kobayashi
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 50(169) 151-159 2007年11月  査読有り
  • 小林 弘明, 吹場 活佳, 本郷 素行, 佐藤 哲也, 溝端 一秀
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 55(644) 418-425 2007年9月5日  
    Experimental studies on telescopic aerospikes for aerodynamic control are reported in this paper. Parametric study on the aerodynamic characteristics of the aerospike has performed including the effect of spike length L, base diameter of tip cone D, spike translating speed and direction. The Axial force coefficient <I>Ca</I> of the aerospike suddenly increases at L/D=3.0 due to flow mode transition from the separation to the reattachment. Reattachment/separation flow mode transition phenomenon can be applicable to a newly invented aerodynamic control device, which is called air-breathing aerospike. In this paper, verification test results of this air-breathing aerospike are also reported. A small solenoid valve in the body cylinder successfully controls reattachment/separation flow mode transition at the angle of attacks from 0 to 12 degree. The spiked bodies’ <I>Ca</I> varies according to the mode transition. As a result, we can control the aerodynamic property of the spiked body by opening/closing the valves periodically.
  • Yusuke Maru, Hiroaki Kobayashi, Shinsuke Takeuchi, Tetsuya Sato
    JOURNAL OF SPACECRAFT AND ROCKETS 44(5) 1012-1020 2007年9月  査読有り
  • 小林 弘明, 丸 祐介, 佐藤 哲也
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 55(642) 329-336 2007年7月5日  
    This paper reports experimental studies on telescopic aerospikes with multiple disks. The telescopic aerospike is useful as an aerodynamic control device; however, changing its length causes a buzz phenomenon, which many researchers have reported. The occurrence of buzzing might be critical to the vehicle because it brings about severe pressure oscillations on the surface. Disks on the shaft produce stable recirculation regions by dividing the single separation flow into several conical cavity flows. The telescopic aerospikes with stabilizer disks are useful without any length constraints. Aerodynamic characteristics of the telescopic aerospikes were investigated through a series of wind tunnel tests. Transition of recirculation/reattachment flow modes of a plain spike causes a large change in the drag coefficient. Because of this hysteresis phenomenon and the buzzing, the plain spike is unsuitable for fine aerodynamic control devices. Adding stabilizer disks is effective for the improved control of aerospikes.
  • 丸 祐介, 小林 弘明, 本郷 素行, 佐藤 哲也
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 55(641) 304-308 2007年6月5日  
    In this paper, a concept of a new variable-geometry aerodynamics device, which is designated “Multiple-Row-Disk (MRD) device,” is introduced. The MRD device divides large separation region around the shaft of an aerospike into several small cavity flows with multiple disks arranged on the shaft. Experimental studies on aerodynamic characteristics of conical nose with axisymmetric cavities were conducted in order to evaluate a feasibility and a fundamental characteristics of the MRD device. It was found that the MRD device could improve not only drag characteristics compared to the conventional aerospikes, but also static longitudinal stability characteristics compared to the conical nose.
  • Tetsuya Sato, Hideyuki Taguchi, Hiroaki Kobayashi, Takayuki Kojima, Keiichi Okai, Kazuhisa Fujita, Daisaku Masaki, Motoyuki Hongo, Toyohiko Ohta
    ACTA ASTRONAUTICA 61(1-6) 367-375 2007年6月  査読有り
  • Takayuki Kojima, Nobuyuki Tsuboi, Hideyuki Taguchi, Hiroaki Kobayashi, Tetsuya Sato, Yu Daimon, Kazuaki Inaba
    Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference 1 871-879 2007年  
  • Nobutaka Bando, Ken Ichi Tajima, Shin Ichiro Sakai, Yuko Inatomi, Takehiko Ishikawa, Hiroaki Kobayashi, Kazuhisa Fujita, Hideyuki Fuke, Shujiro Sawai, Tatsuaki Hashimoto
    International Astronautical Federation - 58th International Astronautical Congress 2007 1 495-500 2007年  
  • Hiroaki Kobayashi, Yusuke Maru, Katsuyoshi Fukiba
    JOURNAL OF SPACECRAFT AND ROCKETS 44(1) 33-41 2007年1月  査読有り
  • 稲富 裕光, 神保 至, 石川 毅彦, 橋本 樹明, 澤井 秀次郎, 斉藤 芳隆, 吉光 徹雄, 坂井 真一郎, 小林 弘明, 藤田 和央, 坂東 信尚, 後藤 雅享, 山川 宏
    JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 23(4) 280-280 2006年11月30日  
  • 稲富 裕光, 石川 毅彦, 橋本 樹明, 澤井 秀次郎, 斉藤 芳隆, 吉光 徹雄, 坂井 真一郎, 小林 弘明, 藤田 和央, 坂東 信尚, 後藤 雅享, 神保 至, 山川 宏
    JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 23(4) 197-203 2006年11月30日  
  • K. Fujita, S. Sawai, H. Kobayashi, N. Tsuboi, H. Taguchi, T. Kojima, K. Okai, T. Sato, Koji Miyaji
    Acta Astronautica 59(1-5) 263-270 2006年7月  査読有り
  • 吹場 活佳, 佐藤 哲也, 坪井 伸幸, 小林 弘明
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 54(629) 257-265 2006年6月5日  
    A study on mass flux of water vapor and mist around a cold cylinder (120–250K) was conducted by means of both experimental and numerical methods. The cylinder was placed in a forced convection air flow at a speed of 1m/sec. The experimental study revealed that the mass flux of the cylinder decreases rapidly under the temperature of about 200K. The mass flux at the cylinder temperature of 120K is one-sixth of that of 240K. The numerical study could simulate the mass flux around the cylinder in which we used a new phase change model with considering the transfer of the particles of mist. By this calculation we found some characteristics of the mass transfer of the cold cylinder which is unique when the temperature of the cylinder becomes cold enough to occur condensation.
  • Hideyuki Taguchi, Takayuki Kojima, Kazuhisa Fijita, Hiroaki Kobayashi, Keiichi Okai, Tetsuya Sato
    Space Technology 26(1-2) 81-86 2006年  
  • 稲富裕光, 石川毅彦, 橋本樹明, 澤井秀次郎, 齋藤義隆, 吉光徹, 坂井真一郎, 小林弘明, 藤田和央, 坂東信尚, 後藤雅亨, 神保至, 山川宏
    日本マイクログラビテイ応用学会誌,Vol. 23 (4), 2006, pp. 197-203 2006年  査読有り
  • Koji Shimoyama, Kozo Fujii, Hiroaki Kobayashi
    COMPUTATIONAL FLUID DYNAMICS 2004, PROCEEDINGS 705-+ 2006年  査読有り
  • 吹場 活佳, 佐藤 哲也, 坪井 伸幸, 小林 弘明
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 53(623) 577-585 2005年12月5日  
    A fundamental study for frost formation around a single cold cylinder was conducted using an experimental and numerical method. We focused on the mass transfer around the cylinder under the condition where phase change of the vapor in the flow occurs. By the experimental study, the mass transfer rate on the cold surface of the cylinder at a constant surface temperature (200–250K) was measured. The results show that the mass transfer rate decreases according to the decrease of the wall temperature below 230K, while it increases above 230K. This phenomenon can not be expressed by the common equation of Sherwood number in which the phase change of the vapor (condensation) is excluded. In the numerical study, we calculated the flow around the cylinder including the phase change of the vapor. The scheme for compressible flow was modified to be able to solve lower speed flow. As a result of the calculation we obtain same tendency as that of the experiment that the mass flux decreases at low temperatures where the phase change occurs.
  • 小島 孝之, 田口 秀之, 岡井 敬一, 小林 弘明, 佐藤 哲也
    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 53(622) 532-540 2005年11月5日  
    Aerodynamic performances of a rectangular intake were investigated experimentally. After a tradeoff study of rectangular intakes whose operative Mach number is from 0 to 6, 20% external compression intake is selected as the best intake from the viewpoint of low number of actuators. Intake performances such as total pressure recovery and mass flow ratio are evaluated by wind tunnel tests. The free stream Mach number of the wind tunnel was M5.1. The size of the intake was 75mm in cowl capture height. Low ramp driving force was achieved by connecting links of the second ramp and third ramp. After the first wind tunnel test that is performed to evaluate the basic performance of the intake, the configuration of the intake is modified. Ramp length of the first ramp and the second ramp were changed to improve the total pressure recovery. Bleed from the second ramp is added. Seal mechanism between the variable ramps and the sidewall is modified. Total pressure recovery is improved from 9.9% to 21.7% by the modifications.
  • Tetsuya Sato, Hideyuki Taguchi, Hiroaki Kobayashi, Takayuki Kojima
    JBIS - Journal British Interplanetary Society 58(7-8) 231-240 2005年7月  
  • Hiroaki Kobayashi, Osamu Amano, Fumio Kawamura, Masakatsu Aoi, Kyniyoshi Hoshino, Akira Sasahira, Yuko Kani
    Progress in Nuclear Energy 47(1-4) 380-388 2005年7月  査読有り
  • Hideyuki Taguchi, Tetsuya Sato, Hiroaki Kobayashi, Takayuki Kojima, Keiichi Okai, Kazuhisa Fujita, Toyohiko Ohta
    A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference 3 1914-1922 2005年  

MISC

 170
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講演・口頭発表等

 64
  • 丸 祐介, 竹崎 悠一郞, 小林 弘明, 成尾 芳博, 河合 努
    年次大会 2018年
    <p>A loading system plays a role of loading and unloading liquid hydrogen between a carrier ship and a ground storage facility in hydrogen supply chain in which hydrogen in the form of liquid phase is transported by the carrier ship from a resource-rich country to a consuming country. An emergency release system (ERS), which is one of components of the loading system, is installed in the middle of transfer pipe of the loading system, and has function of separating and plugging the pipe at an abnormality during loading so as to prevent a large amount of cryogenic fluid from scattering. We have conducted R & D study of the ERS for liquid hydrogen based on an existing one for liquid natural gas (LNG). Whole system function of the ERS including separation behavior was verified conducting a field experiment with the ERS test model and liquid hydrogen. Through several tests, the separation mechanism and behavior were verified, and also, soundness of the seal mechanism was evaluated. While, auto-ignition phenomena were observed on the separation surface of the ERS after the separation, of which causes have not been identified yet. Characteristics of dispersion behavior of hydrogen that was released at the separation could be investigated measuring distribution of temperature and hydrogen concentration around the ERS test model.</p>
  • 小林 弘明, 竹崎 悠一郎, 成尾 芳博, 丸 祐介, 辻上 博司, 宮鍋 昂大, 河村 哲, 大門 優, 梅村 悠, 武藤 大貴
    年次大会 2018年
    <p>To improve safety regulations for fuel cell vehicles and hydrogen infrastructure, experiments of cryo-compressed hydrogen leakage diffusion were conducted. The experimental apparatus can supply 90 MPa hydrogen of various temperature conditions. Measurement items were hydrogen concentration distribution, blast pressure, flame length, and radiant heat. In addition, high speed camera observation was carried out to investigate the near-field of cryogenic hydrogen jet at supercritical pressure. The experimental apparatus can supply 90 MPa hydrogen at various temperature conditions (50 K–300 K) at a maximum flow rate of 100 kg/h. The hydrogen leakage flow rate was measured using pinhole nozzles with different outlet diameters (0.2 mm, 0.4 mm, 0.7 mm, and 1 mm). It was confirmed that the hydrogen leakage flow rate increases as the supply temperature decreases. The hydrogen concentration distribution was measured by injecting high-pressure hydrogen from the 0.2-mm pinhole for 10 min under a constant pressure/temperature condition. As the hydrogen injection temperature decreased, it was found that the hydrogen concentration increased, and an empirical formula of the 1% concentration distance for the cryogenic hydrogen system was newly presented.</p>
  • 坂本 勇樹, PEVERONI Laura, 小林 弘明, 箕手 一眞, 多根 翔平, 佐藤 哲也, VETRANO Rosaria
    日本冷凍空調学会年次大会講演論文集 Proceedings of the JSRAE Annual Conference 2017年
  • 丸 祐介, 竹崎 悠一郞, 小林 弘明, 大門 優, 梅村 悠, 成尾 芳博, 松野 優
    年次大会 2017年
  • 小林 弘明, 竹崎 悠一郎, 成尾 芳博, 松野 優, 辻上 博司, 宮鍋 昂大, 河村 哲, 丸 祐介, 大門 優, 梅村 悠
    年次大会 2017年
    <p>JAXA has constructed an experimental facility to pressurize and supply liquid hydrogen at a maximum pressure of 90 MPa to conduct experimental research on the injection of high pressure liquid hydrogen into the atmosphere. Liquid hydrogen has a property that its density greatly changes depending on pressure despite being a liquid phase. In addition, the high pressure hydrogen gas is in a supercritical state and has an intermediate property between a gas and a liquid. Therefore, it is a difficult question whether to treat the injection of high pressure liquid hydrogen as a gas phase phenomena or as a liquid phase phenomena. As a result of the experiment, it was found good to apply the liquid orifice equation to predict the discharge flow rate of high pressure liquid hydrogen.</p>
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所属学協会

 3

共同研究・競争的資金等の研究課題

 14
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産業財産権

 9
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