Curriculum Vitaes

Hiroaki Kobayashi

  (小林 弘明)

Profile Information

Affiliation
Professor, Institute of Space and Astronautical Science, JAXA
Degree
工学博士(東京大学)

J-GLOBAL ID
200901061542880861
researchmap Member ID
5000019456

Education

 1

Papers

 152
  • KOBAYASHI Hiroaki, SATO Tetsuya
    Aeronautical and Space Sciences Japan, 46(532) 303-310, May, 1998  
    Air intake is one of the most important components for an airbreathing propulsion system of supersonic and hypersonic vehicles. Air intake can be evaluated by air mass capture ratio and total pressure recovery ratio. In higher Mach number flight condition, larger total pressure losses occurs in the compression processes of air intake and reduces the propulsion performance. By utilizing the precompression coming from oblique shocks generated underneath vehicle forebody, a part of functions loaded in air intake can be substituted by the forebody precompression, thereby overall propulsive performance is able to be improved effectively. In the present paper, the precompression effects given by nose shape of forebody and geometrical arrangement of air intake underneath fuselage were analyzed by CFD calculation using 3-dimensional compressible Navier-Stokes equations.
  • SATO Tetsuya, TAKAGI Ikuo, KOJIMA Takayuki, KOBAYASHI Hiroaki
    Aeronautical and Space Sciences Japan, 46(539) 651-659, 1998  
    Mixed-compression type axisymmetric air intakes for ATREX engine have been tested in the supersonic wind tunnel from Mach 0.5 to 4 since 1993. The throat area of the intake can be variable with a translating center spike to accomplish starting and off-design operation since the ATREX intake must work well over the wide flight Mach number up to 6. Here are presented effects of the intake design Mach number, the air bleed from a center spike and/or a cowl around the throat, an angle of attack and blunt nose of the spike on the intake performance characteristics, that is total pressure recovery and mass capture ratio. It is found that bleeding from the center spike and the cowl influences mainly on total pressure recovery and mass capture ratio respectively. The advantage of rounding properly off the spike nose is confirmed. Small center spike cone angle and/or blunt nose is sensitive to the angle of attack.

Misc.

 164
  • 森穂高, 大山聖, 丸祐介, 坂本勇樹, 小林弘明, 江口光
    日本航空宇宙学会年会講演会講演集(CD-ROM), 54th, 2023  
  • 宍戸, 拓, 伊藤, 千珠, 真子, 弘泰, 小林, 弘明, 丸, 祐介, 徳留, 真一郎, SHISHIDO, Taku, ITO, Senju, MANAKO, Hiroyasu, KOBAYASHI, Hiroaki, MARU, Yusuke, TOKUDOME, Shinichiro
    令和4年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2022, Jan, 2023  
    令和4年度宇宙輸送シンポジウム(2023年1月12日-13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 Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan 資料番号: SA6000184015 STCP-2022-015
  • 坂本勇樹, 小林弘明, 丸祐介, 徳留真一郎, 野中聡, 澤井秀次郎, 大山聖, 三浦政司, 正木大作, 高田仁志, 角銅洋実, 加賀亨, 山城龍馬, 杵淵紀世志, 真子弘泰, 内海政春, 中田大将, 江口光, RICHARDSON Matthew, 佐藤哲也
    宇宙科学技術連合講演会講演集(CD-ROM), 66th, 2022  
  • 近藤奨一郎, 別府玲緒, 杵淵紀世志, 梅村悠, 小林弘明
    宇宙科学技術連合講演会講演集(CD-ROM), 66th, 2022  
  • 近藤, 奨一郎, 福﨑, 俊哉, 坂野, 友哉, 杵淵, 紀世志, 藤浦, 彰友, 奈女良, 実央, 中田, 大将, 真子, 弘泰, 徳留, 真一郎, 小林, 弘明, 坂本, 勇樹, 丸, 祐介, KONDO, Shoichiro, FUKUZAKI, Toshiya, BANNO, Yuya, KINEFUCHI, Kiyoshi, FUJIURA, Akitomo, NAMERA, Mio, NAKATA, Daisuke, MANAKO, Hiroyasu, TOKUDOME, Shinichiro, KOBAYASHI, Hiroaki, SAKAMOTO, Yuki, MARU, Yusuke
    令和3年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2021, Jan, 2022  
    令和3年度宇宙輸送シンポジウム(2022年1月13日-14日. オンライン開催) Space Transportation Symposium FY2021 (January 13-14, 2022. Online Meeting) 著者人数: 12名 資料番号: SA6000173016 STCP-2021-016

Presentations

 64
  • MARU Yusuke, TAKESAKI Yuichiro, KOBAYASHI Hiroaki, NARUO Yoshihiro, KAWAI Tsutomu
    The Proceedings of Mechanical Engineering Congress, Japan, 2018
    <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>
  • KOBAYASHI Hiroaki, TAKESAKI Yuichiro, NARUO Yoshihiro, MARU Yusuke, TSUJIGAMI Hiroshi, MIYANABE Kota, KAWAMURA Satoru, DAIMON Yu, UMEMURA Yutaka, MUTO Daiki
    The Proceedings of Mechanical Engineering Congress, Japan, 2018
    <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
  • MARU Yusuke, TAKESAKI Yuichiro, KOBAYASHI Hiroaki, DAIMON Yu, UMEMURA Yutaka, NARUO Yoshihiro, MATSUNO Yu
    The Proceedings of Mechanical Engineering Congress, Japan, 2017
  • KOBAYASHI Hiroaki, TAKESAKI Yuichiro, NARUO Yoshihiro, MATSUNO Yu, TSUJIGAMI Hiroshi, MIYANABE Kota, KAWAMURA Satoru, MARU Yusuke, DAIMON Yu, UMEMURA Yutaka
    The Proceedings of Mechanical Engineering Congress, Japan, 2017
    <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>

Professional Memberships

 3

Research Projects

 13

Industrial Property Rights

 9