Matsuo, Akiko

写真a

Affiliation

Faculty of Science and Technology, Department of Mechanical Engineering (Yagami)

Position

Professor

Related Websites

External Links

Profile Summary 【 Display / hide

Career 【 Display / hide

  • 1989.04
    -
    1993.03

    (株)リクルート スーパーコンピュータ研究所勤務

  • 1992.01
    -
    1993.09

    日本学術振興会(DC1)(名古屋大学), 特別研究員

  • 1993.10
    -
    1995.03

    日本学術振興会(PD)(文部省宇宙科学研究所), 特別研究員

  • 1995.04
    -
    1997.03

    慶應義塾大学理工学部, 助手

  • 1995.06

    文部科学省宇宙科学研究所, 共同研究員

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Academic Background 【 Display / hide

  • 1987.03

    Tsuda College, Faculty of Arts and Science, 数学科

    University, Graduated

  • 1989.03

    Nagoya University, Graduate School, Division of Engineering, 航空工学専攻課程

    Graduate School, Completed, Master's course

  • 1993.09

    Nagoya University, Graduate School, Division of Engineering, 航空工学専攻課程

    Graduate School, Completed, Doctoral course

Academic Degrees 【 Display / hide

  • 工学, Nagoya University, 1993.09

 

Research Areas 【 Display / hide

  • Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Fluid engineering

  • Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering) / Aerospace engineering

 

Books 【 Display / hide

  • Detonation Control for Propulsion: Pulse Detonation and Rotating Detonation Engines (Shock Wave and High Pressure Phenomena)

    K. Matsuoka, H. Taki, J. Kasahara, H. Watanabe, A. Matsuo, and T. Endo, Springer International Publishing, 2018.01

    Scope: Pulse Detonation Cycle at Kilohertz Frequency, Chapter 8, pp.183-198

  • Detonation Control for Propulsion: Pulse Detonation and Rotating Detonation Engines (Shock Wave and High Pressure Phenomena)

    J. Kasahara, Y. Kato, K. Ishihara, K. Goto, K. Matsuoka, A. Matsuo, I. Funaki, H. Moriai, D. Nakata, K. Higashino, and N. Tanatsugu, Springer International Publishing, 2018.01

    Scope: Application of Detonation Waves to Rocket Engine Chamber, Chapter 4, pp.61-76

  • 機械工学便覧 基礎編 α5 熱 工 学

    松尾亜紀子 他62名, 日本機械学会, 2006.12

    Scope: 2・14 気体の流動 pp44-48

  • 数値流体力学ハンドブック

    松尾亜紀子 他79名, 丸善, 2003.03

    Scope: 6・6 デトネーション pp300-303

Papers 【 Display / hide

  • Combustion Structure of a Cylindrical Rotating Detonation Engine with Liquid Ethanol and Nitrous Oxide

    Sato T., Nakata K., Ishihara K., Itouyama N., Matsuoka K., Kasahara J., Kawasaki A., Nakata D., Eguchi H., Uchiumi M., Matsuo A., Funaki I.

    Combustion and Flame (Combustion and Flame)  264 2024.06

    ISSN  00102180

     View Summary

    Liquid propellants are commonly used in rocket engines due to their high energy density. In this study, we focused on the use of liquid ethanol and liquid nitrous oxide as propellants in a cylindrical rotating detonation engine (RDE) for practical applications, and examined the effects of various conditions on the bipropellant RDE performance. We varied the vapor quality of nitrous oxide in a mixture of liquid and gaseous nitrous oxide due to the flash boiling. In addition, we varied the liquid ethanol temperature, the injector stiffness, and momentum angle of the propellant. We then analyzed the effects of these changes on the propagation mode of the RDE under atmospheric pressure conditions. The results showed that a rotating detonation wave was observed under the combination of high vapor quality of nitrous oxide, high injector stiffness, high liquid ethanol temperature, and high momentum angle. The propagation velocity was obtained as 73∼83 % of the Chapman-Jouguet velocity. Long-duration combustion tests were also conducted, and the internal combustion structure was confirmed from the erosion of the carbon-carbon (C/C) composite material. The detonation wave was considered to propagate near the bottom of the RDE with liquid propellants from the erosion heights of the C/C composite. The erosion height was confirmed to be consistent with the fill height calculated using the sound speed of the nitrous oxide. In addition, characteristic exhaust velocity efficiencies of more than 85 % were achieved in all combustion tests.

  • Effect of channel expansion angle near injector outlet on a rotating detonation engine performance

    Nakajima K., Matsuoka K., Itouyama N., Kasahara J., Kawasaki A., Matsuo A.

    Shock Waves (Shock Waves)   2024

    ISSN  09381287

     View Summary

    A rotating detonation engine (RDE) is expected to achieve a pressure gain (PG) in which the total pressure of the product at the engine exit exceeds the total pressure of the supplied oxidizer. However, many non-ideal phenomena exist in the RDE, which hinder the achievement of a PG. This study focused on the channel expansion angle near injector outlet which is considered to impact the structure of detonation wave and the PG performance. Combustion tests were conducted by varying the channel expansion angle near the axially injected oxidizer injector outlet to 90∘ and 30∘. As a result, the thrust was not affected by the expansion angle, but the propagation velocity of detonation wave at an expansion angle of 90∘ was approximately 5% higher than that at an expansion angle of 30∘. A comparison utilizing the pressure increase ratio obtained from the fluctuating pressure in the combustion chamber suggested that the Mach number of the detonation wave was higher for an expansion angle of 90∘. As a result of evaluating the PG performance utilizing the equivalent available pressure obtained from thrust measurements, it was not confirmed to differ with changes in the expansion angle.

  • Lagrangian dispersion and averaging behind a two-dimensional gaseous detonation front

    Watanabe H., Matsuo A., Chinnayya A., Itouyama N., Kawasaki A., Matsuoka K., Kasahara J.

    Journal of Fluid Mechanics (Journal of Fluid Mechanics)  968 2023.08

    ISSN  00221120

     View Summary

    Two-dimensional numerical simulations with the particle tracking method were conducted to analyse the dispersion behind the detonation front and its mean structure. The mixtures were 2H-O-7Ar and 2H-O of increased irregularity in ambient conditions. The detonation could be described as a two-scale phenomenon, especially for the unstable case. The first scale is related to the main heat release zone, and the second where some classical laws of turbulence remain relevant. The dispersion of the particles was promoted by the fluctuations of the leading shock and its curvature, the presence of the reaction front, and to a lesser extent transverse waves, jets and vortex motion. Indeed, the dispersion and the relative dispersion could be scaled using the reduced activation energy and the parameter, respectively, suggesting that the main mechanism driving the dispersion came from the one-dimensional leading shock fluctuations and heat release. The dispersion within the induction time scale was closely related to the cellular structure, particles accumulating along the trajectory of the triple points. Then, after a transient where the fading transverse waves and the vortical motions coming from jets and slip lines were present, the relative dispersion relaxed towards a Richardson-Obukhov regime, especially for the unstable case. Two new Lagrangian Favre average procedures for the gaseous detonation in the instantaneous shock frame were proposed and the mean profiles were compared with those from Eulerian procedure. The characteristic lengths for the detonation were similar, meaning that the Eulerian procedure gave the mean structure with a reasonable accuracy.

  • Impact of mixture mass flux on hydrodynamic blockage ratio and Mach number of rotating detonation combustor

    Noda, T., Matsuoka, K., Goto, K., Kawasa, A., Watanabe, H., Itouyama, N., Kasahara, J., and Matsuo, A.

    Acta Astronautica (Acta Astronautica)  207   219 - 226 2023.06

    Research paper (scientific journal), Joint Work,  ISSN  00945765

     View Summary

    To analyze non-ideal phenomena, such as burned gas backflow and non-detonation combustion, which affect the rotating detonation wave Mach number, simultaneous self-luminous visualization, time-averaged static pressure, fluctuating pressure, and thrust measurements with gaseous ethylene and oxygen were performed. Consequently, by doubling the number density of the fuel injectors, the hydrodynamic blockage ratio at the oxidizer inlet increased approximately 1.7-fold under the same oxidizer inlet area conditions. This may be attributed to the increase in the detonation propagation Mach number owing to the enhanced mixing of fuel and oxidizer. The relationship between the parasitic combustion fraction in front of the rotating detonation wave and the Mach number was also investigated by using a distributed heat release model. Consequently, it was suggested that experimental Mach number decreased from approximately 4.1 to 2.8 with increase in a mixture mass flux, and the theoretical detonation wave propagation Mach number was 7.3.

  • Numerical investigation of the effects of injector configuration on flow structures in annular and cylindrical rotating detonation combustors

    Sada, T., Matsuo, A., Shima, E., Kawasaki, A., Matsuoka, K., and Kasahara, J.

    Science and Technology of Energetic Materials 84 ( 2 ) 17 - 23 2023.05

    Research paper (scientific journal), Joint Work, Accepted

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Papers, etc., Registered in KOARA 【 Display / hide

Reviews, Commentaries, etc. 【 Display / hide

  • 特集 航空宇宙分野御コンピューターシミュレーション

    松尾 亜紀子 他

    計算工学 28 ( 3 )  2023.07

    Article, review, commentary, editorial, etc. (scientific journal), Corresponding author

  • 爆発現象等に関する安全工学の研究に従事する理工学部機械工学科女性教授ープラントにおける爆発現象ー

    松尾 亜紀子

    高圧ガス (高圧ガス保安協会)  57 ( 1 ) 23 - 27 2020.01

    Article, review, commentary, editorial, etc. (other), Single Work,  ISSN  0452-2311

  • 極超音速飛しょう体におけるサボ分離挙動に関する数値解析

    笠原弘貴, 松尾亜紀子

    防衛技術ジャーナル (一般財団法人 防衛技術協会)  2019年9月号 ( 462 ) 46 - 52 2019.09

    Rapid communication, short report, research note, etc. (scientific journal), Joint Work

  • 化学プラント爆発事象再現へ向けた燃焼過程の解析技術

    松尾亜紀子

    安全工学 (安全工学会)  57 ( 6 ) 465 - 470 2018.12

    Article, review, commentary, editorial, etc. (scientific journal), Single Work,  ISSN  0570-4480

  • デトネーション解析における数値シミュレーションモデル

    松尾 亜紀子

    機械の研究 70 ( 9 ) 713 - 716 2018.09

    Article, review, commentary, editorial, etc. (scientific journal), Single Work

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Presentations 【 Display / hide

  • Numerical Analysis of an Air-breathing Engine Using Exhaust Jets from a Rotating Detonation Engine

    Tahara, J., Matsuo, A., Shima, E., Itouyama, N., Kawasaki, A., Matsuoka, K., and Kasahara, J.

    13th International Workshop on Detonation for Propulsion (IWDP2024) (Michigan, USA) , 

    2024.06

    Oral presentation (general)

  • Numerical Investigation of the Interaction between the Exhaust Flow of Reflective Shuttling Detonation Combustor and Supersonic Turbulent Flow

    Miyashita, M., Matsuo, A., Shima, E., Itouyama, N., Kawasaki,A., Matsuoka, K., and Kasahara, J.

    19th International Conference on Numerical Combustion (ICNC2024) (Kyoto, Japan) , 

    2024.05

    Oral presentation (general)

  • A low-dimensional modeling approach to acceleration of an internal flow of a rotating detonation engine

    Nakata, K., Itouyama, N., Matsuoka, K., Kasahara, J., Kawasaki, A., Matsuo, A., Funaki, I., and Higashino, K.

    19th International Conference on Numerical Combustion (ICNC2024) (Kyoto, Japan) , 

    2024.05

    Oral presentation (general)

  • Numerical Consideration to Geometry of Diverging Rotating Detonation Engine

    Sada, T., Matsuo, A., Shima, E., Itouyama, N., Kawasaki,A., Matsuoka, K., and Kasahara, J.

    19th International Conference on Numerical Combustion (ICNC2024) (Kyoto, Japan) , 

    2024.05

    Oral presentation (general)

  • Numerical Analysis of Exhaust Jet Characteristics from Annular RDEs with Various Outlet Geometries

    Tahara, J., Matsuo, A., Shima, E., Itouyama, N., Kawasaki,A., Matsuoka, K., and Kasahara, J.

    19th International Conference on Numerical Combustion (ICNC2024) (Kyoto, Japan) , 

    2024.05

    Oral presentation (general)

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Research Projects of Competitive Funds, etc. 【 Display / hide

  • 多分散系微粉体がもたらす爆発被害:シミュレーションが解き明かす炭塵燃焼と安全評価

    2018.04
    -
    2021.03

    MEXT,JSPS, Grant-in-Aid for Scientific Research, Grant-in-Aid for Scientific Research (B), Principal investigator

Intellectual Property Rights, etc. 【 Display / hide

  • パルスデトネーションエンジン用多孔微細管燃料酸化剤供給プレート

    Date applied: 2000-258181  2000.07 

    Date announced: 2002-39012  2002.02 

    Patent, Joint

Awards 【 Display / hide

  • 2023年度日本燃焼学会論文賞

    川﨑央, 稲川 智也, 笠原次郎, 後藤 啓介, 松岡健, 松尾亜紀子, 船木一幸, 2023.11, 日本燃焼学会, Critical condition of inner cylinder radius for sustaining rotating detonation waves in rotating detonation engine thruster

    Type of Award: Award from Japanese society, conference, symposium, etc.

  • Fluids Science Research Award

    2023.11, 一般財団法人 機器研究会

    Type of Award: International academic award (Japan or overseas)

  • Pressure Gain Combustion Best Paper Award 2022

    K. Goto, K. Matsuoka, K. Matsuyama, A. Kawasaki, H. Watanabe, N. Itouyama, K. Ishihara, V. Buyakofu, T. Noda, J. Kasahara (Nagoya Univ.), A. Matsuo(Keio Univ.), I. Funaki (JAXA), D. Nakata, M. Uchiumi (Muroran Inst. Tech.), H. Habu, S. Takeuchi, S. Arakawa, J. Masuda, K. Maehara, T. Nakao, K. Yamada (JAXA), 2023.01, AIAA, Flight Demonstration of Detonation Engine System Using Sounding Rocket S-520-31: Performance of Rotating Detonation Engine

    Type of Award: Award from international society, conference, symposium, etc.,  Country: United States

     View Description

    深宇宙探査用デトネーションエンジンの宇宙飛行実証論文に対しAIAAが2022 AIAA Pressure Gain Combustion Best Paper Awardを授与。2021年7月27日に名古屋大学、宇宙航空研究開発機構、慶應義塾大学、室蘭工業大学との共同研究として観測ロケットS-520-31号機の第2段を用いてデトネーションエンジンの宇宙飛行実証を実施した。その結果を論文として公開し、その研究論文に対し、AIAAからBest Paper Awardを授与された。この賞は圧力増大燃研究(デトネーションエンジン研究)で2022年に米国航空宇宙学会で発表された口頭発表論文の内、優れた1件に授与される。

  • 2021年『美しい炎』の写真展最優秀作品賞

    松尾亜紀子 他, 2021.11, 一般社団法人 日本燃焼学会, World First! Detonation Engine Space Demonstration

    Type of Award: Award from Japanese society, conference, symposium, etc.

  • 2020年『美しい炎』の写真展最優秀作品賞

    松尾亜紀子 他, 2020.12, 一般社団法人 日本燃焼学会, Detonation Engine to Space

    Type of Award: Award from Japanese society, conference, symposium, etc.

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Courses Taught 【 Display / hide

  • LABORATORY IN SCIENCE

    2024

  • INTRODUCTION TO FLUID MECHANICS

    2024

  • INDEPENDENT STUDY ON SCIENCE FOR OPEN AND ENVIRONMENTAL SYSTEMS

    2024

  • INDEPENDENT STUDY FOR EXCHANGE STUDENT B

    2024

  • INDEPENDENT STUDY FOR EXCHANGE STUDENT A

    2024

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Courses Previously Taught 【 Display / hide

  • 宇宙推進工学

    Keio University

    2014.04
    -
    2015.03

    Spring Semester, Lecture

  • 機械工学創造演習

    Keio University

    2014.04
    -
    2015.03

    Autumn Semester, Seminar, Lecturer outside of Keio

  • 熱力学の基礎

    Keio University

    2014.04
    -
    2015.03

    Autumn Semester, Lecture

  • 高速空気力学

    Keio University

    2014.04
    -
    2015.03

    Autumn Semester, Lecture

  • 応用計算力学特論第2

    Keio University

    2014.04
    -
    2015.03

    Autumn Semester, Lecture

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Social Activities 【 Display / hide

  • 第Ⅱ部 特別企画「計算力学を拡張する新技術:量子コンピューティングと生成系AI」

    日本学術会議, 公開シンポジウム「第13回計算力学シンポジウム」 (日本学術会議講堂)

    2023.12
  • カンファレンストークセッション「日本の宇宙戦略、日本の勝ち筋」

    北海道宇宙サミット実行委員会, 北海道宇宙サミット2023「宇宙を動かせ。」 (ベルクラシック帯広)

    2023.10
  • HPCwire Japan 新シリーズ「Women in HPC」開始記念 本音を語る座談会

    HPCwire Japan,  (コモレ四谷)

    2023.09
  • 日本の未来を知る そして、エネルギー問題を工学で考える

    佐賀県立佐賀西高等学校, 佐賀県立佐賀西高等学校 新理想の星プロジェクト講演会 (佐賀県立佐賀西高等学校)

    2022.07
  • 産学官連携が切り拓く、日本の宇宙産業の新たなステージ

    一般社団法人SPACETIDE, SPACETIDE 2021 Spring "The Evolution of Commercial Space"宇宙ビジネス、事業化ステージのはじまり (虎ノ門ヒルズフォーラム)

    2021.03

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Media Coverage 【 Display / hide

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Memberships in Academic Societies 【 Display / hide

  • International Association for Hydrogen Safety, 

    2015.07
    -
    Present
  • International Shock Wave Institute, 

    2013
    -
    Present
  • 日本計算工学会, 

    2002.12
    -
    Present
  • 日本火災学会, 

    2002.11
    -
    2021
  • 日本原子力学会, 

    2002.11
    -
    2007.03

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Committee Experiences 【 Display / hide

  • 2024.05
    -
    2026.04

    第44期会長, 一般社団法人火薬学会

  • 2024.05
    -
    2026.03

    創発的研究支援事業アドバイザー, 国立研究開発法人 科学技術振興機構

  • 2024.04
    -
    2026.04

    ガス系消火設備等評価専門委員会 委員, 一般財団法人日本消防設備安全センター

  • 2024.04
    -
    2026.03

    2024年度(第32期)理事, 日本流体力学会

  • 2024.04
    -
    2026.03

    代表会員, 一般社団法人日本計算工学会

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