Dept. of Space Flight Systems

Takashi Aoyama

  (青山 剛史)

Profile Information

Affiliation
Specially Appointed Professor, Institute of Space and Astronautical Science, Department of Space Flight Systems, Japan Aerospace Exploration Agency
(Concurrent)Assigned to the Program Director of Aviation Technology, Aeronautical Technology Directorate
Degree
Ph.D(Engineering)(The University of Tokyo)

J-GLOBAL ID
200901010462740011
researchmap Member ID
0000040157

External link

Papers

 46
  • AOYAMA Takashi, MIZOBUCHI Yasuhiro, HASHIMOTO Atsushi
    Aeronautical and Space Sciences Japan, 72(6) 193-199, Jun 5, 2024  
  • Yoimi Kojima, Takashi Ishida, Atsushi Hashimoto, Takashi Aoyama
    AIAA Scitech 2020 Forum, 1 PartF, 2020  
    We simulate unsteady flows over a 30P30N slat by taking account of velocity fluctuations inside the turbulent boundary layer (TBL) on the slat. Embedded Large Eddy Simulation method is employed to generate pseudo turbulences inside the TBL. Also, we conduct additional simulation by Delayed Detached Eddy Simulation (DDES), which has been made without the pseudo turbulence, for making comparisons with the ELES case. Comparisons between the ELES and DDES results suggests that the pseudo turbulence makes the vortex structures of a shear layer extending from the cusp more three-dimensionally. The difference of vortex structure leads to the shear layer in the ELES case curves with a smaller radius of curvature. The time-averaged flow field of the ELES case is closer to the experimental result than those in the DDES case. While the shear layer on the cusp side is affected by the pseudo turbulence, there is no significant difference between the ELES and DDES cases in the shear layer extending from the TE of the slat.
  • Yamamoto, J, Kojima, Y, Kameda, M, Watanabe, Y, Hashimoto, A, Aoyama, T
    Aerospace Science and Technology, 96 105523-105523, Oct 31, 2019  Peer-reviewed
  • Noboru KOBIKI, Yasutada TANABE, Takashi AOYAMA, Do-Hyung KIM, Hee Jung KANG, Seong-Yong WIE, Seung-Ho KIM
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 62(2) 64-74, Jan, 2019  Peer-reviewed
    The Japan Aerospace Exploration Agency (JAXA) and The Korea Aerospace Research Institute (KARI) jointly started activities related to the research and development of "Active Tab," a helicopter noise reduction technique. KARI constructed the analytical methodology consisting of the aerodynamic, structural dynamic and acoustic codes for defining the requirements to be used in evaluating the performance of Active Tab when installed in a Mach scaled assumed blade. Based on the requirements defined, JAXA carried out a conceptual design study, developed the Active Tab drive mechanism and evaluated its performance. The analytical results show Active Tab satisfying the requirements has sufficient noise reduction capability. Evaluation for the Active Tab drive mechanism demonstrated the dynamic performance and durability required practical use installed in helicopter blades.
  • Keita Kimura, Yasutada Tanabe, Takashi Aoyama, Yuichi Matsuo, Makoto Iida
    Springer Proceedings in Physics, 323-329, 2019  

Misc.

 164
  • 布施, 亮祐, 上島, 啓司, 菅原, 瑛明, 保江, かな子, 石田, 崇, 口石, 茂, 青山, 剛史, 田辺, 安忠, Fuse, Ryosuke, Ueshima, Keiji, Sugawara, Hideaki, Yasue, Kanako, Ishida, Takashi, Kuchiishi, Shigeru, Aoyama, Takashi, Tanabe, Yasutada
    宇宙航空研究開発機構特別資料: 第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム論文集 = JAXA Special Publication: Proceedings of the 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium, JAXA-SP-19-007 193-199, Feb 4, 2020  
    第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム (2019年7月1日-3日. 早稲田大学早稲田キャンパス国際会議場), 新宿区, 東京 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium (July 1-3, 2019. International Conference Center, Waseda University), Shinjuku-ku, Tokyo, Japan A CFD solver “FaSTAR-Move” that enables analysis around moving and deformed objects have been developed by JAXA, and was applied to the analysis of separation of mounted objects, etc. Currently, the rotorcraft analysis module has been added to FaSTAR-Move in order to meet industrial needsdemands for the rotorcraft analysis . In this paper, comparisons and validations of the developed module with experiments of hovering rotor are performed and it is shown that reasonable results are obtained. 形態: カラー図版あり Physical characteristics: Original contains color illustrations 資料番号: AA1930011017 レポート番号: JAXA-SP-19-007
  • 青山剛史, 山崎渉, 坂本淳, 市橋大樹, 上野真
    宇宙航空研究開発機構特別資料 JAXA-SP-(Web), (20-002), 2020  
  • 青山剛史, 上野真, 鳥井田浩也, 上野優子
    宇宙航空研究開発機構特別資料 JAXA-SP-(Web), (20-002), 2020  
  • 青山剛史, 上野真, 鳥井田浩也, 内山貴啓, 保江かな子, 林謙司, 石田崇, 黒田文武, 上野優子
    宇宙航空研究開発機構特別資料 JAXA-SP-(Web), (19-002), 2019