Matsuo, Akiko

写真a

Affiliation

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

Position

Professor

Related Websites

External Links
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Profile Summary 【 Display / hide 】

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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

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Academic Degrees 【 Display / hide 】

  • 工学, Nagoya University, 1993.09

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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

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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

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Papers 【 Display / hide 】

  • 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

  • Visualization and Performance Evaluation of a Liquid-Ethanol Cylindrical Rotating Detonation Combustor

    Ishihara, K., Yoneyama, K., Sato, T., Watanabe, H., Itouyama, N., Kawasaki, A., Matsuoka, K., Kasahara, J., Matsuo, A., and Funaki, I.

    Transaction of the Japan Society for Aeronautical and Space Sciences （Transactions of the Japan Society for Aeronautical and Space Sciences)  66 （ 2 ） 46 - 58 2023.03

    Research paper (scientific journal), Accepted,  ISSN  05493811

    　View Summary

    Rotating detonation combustors (RDCs) are among the combustors that use supersonic combustion waves known as detonation waves, and are expected to simplify engine systems and improve thermal efficiency due to their supersonic combustion and compression performance using shock waves. Research is also being actively conducted worldwide on a cylindrical RDC; a RDC without an inner cylinder, which is expected to simplify and downsize the combustor. However, most of the research was performed using gas propellants, and liquid propellants were rarely used. Since liquid propellants are used in many combustors, it is important to evaluate the performance of RDCs with liquid propellants. In this study, a cylindrical RDC with a liquid ethanol-gas oxygen mixture was constructed and tested at a flow rate of 31.5 ± 5.0 g/s, an equivalence ratio of 0.46-1.39, and a back pressure of 14.5 ± 2.5 kPa. The thrust was shown to depend strongly on the combustor bottom pressure history. In addition, the start-up process of the cylindrical RDC with liquid fuel was clarified by self-luminous and CH+ radical visualizations. It was found that the detonation wavefront propagated at a distance of 2-3mm from the combustor bottom, and the main combustion region was 10-15mm in height.

  • Thrust Performance of Converging Rotating Detonation Engine Compared with Steady Rocket Engine

    Ishihara, K., Yoneyama, K., Watanabe, H., Itouyama, N., Kawasaki, A., Matsuoka, K., Kasahara, J., Matsuo, A., Funaki, I., and Higashino, K.

    Journal of Propulsion and Power （Journal of Propulsion and Power)  39 （ 3 ） 297 - 307 2023.02

    Research paper (scientific journal), Joint Work, Accepted,  ISSN  07484658

    　View Summary

    Rotating detonation engines (RDEs) have been actively researched around the world for application to nextgeneration aerospace propulsion systems because detonation combustion has theoretically higher thermal efficiency than conventional combustion. Moreover, because cylindrical RDEs have simpler combustors, further miniaturization of conventional combustors is expected. Therefore, in this study, with the aim of applying RDEs to space propulsion systems, a cylindrical RDE with a converging-diverging nozzle was manufactured; the combustor length Lc was changed to 0, 10, 30, 50, and 200 mm; and the thrust performance and combustion mode with the different combustor lengths were compared. As a result, four combustion modes were confirmed. Detonation combustion occurred with a combustor length of Lc = 0 mm: that is, a converging rotating detonation engine. The thrust performance of this engine was 94 to 100% of the theoretical rocket thrust performance, which is equivalent to the thrust performance of conventional rocket combustion generated at Lc = 200 mm. This study shows that detonation combustion can significantly reduce engine weight while maintaining thrust performance.

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

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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 】

  • A Bread Board Model Testing for In-Space Flight Demonstration of a Liquid-Propellant Detonation Engine System

    Kawasaki, A., Nakata, K., Sato, T., Sawada, S., Kudo, Y., Suzuki, Y., Itouyama, N., Matsuoka, K., Matsuyama, K., Kasahara, J., Nakata, D., Namera, M., Eguchi, H., Uchiumi, M., Matsuo, A., Funaki, I., Nakamura, S., Higashino, K., and Hirashima, H.

    AIAA SciTech 2024 (Orland, Florida, U.S.A.) , 

    2024.01
    , 

    Oral presentation (general)

  • Combustion Characteristics and Thrust Performance of RDEs of Different Designs and Scale

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

    AIAA SciTech 2024 (Orland, Florida, U.S.A.) , 

    2024.01
    , 

    Oral presentation (general)

  • Experimental research for clustering with the coupled cylindrical rotating detonation engine

    Sakata, R., Inada, M., Itouyama, N., Matsuoka, K., Kasahara, J., Kawasaki, A., Matsuo, A., and Funaki, I.

    AIAA SciTech 2024 (Orland, Florida, U.S.A.) , 

    2024.01
    , 

    Oral presentation (general)

  • Numerical Investigation on Throatless Diverging Rotating Detonation Engines

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

    AIAA SciTech 2024 (Orland, Florida, U.S.A.) , 

    2024.01
    , 

    Oral presentation (general)

  • The Rotating Detonation Engines with The Helical Combustion Chambers

    Sawada, S., Itouyama, I., Matsuoka, K., Kasahara, J., Braun, J., Paniagua, G., Kawasaki, A., Watanabe, H., Matsuo, A., and Funaki, I.

    AIAA SciTech 2024 (Orland, Florida, U.S.A.) , 

    2024.01
    , 

    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

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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

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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 】

  • 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

  • 応用計算力学特論第１

    Keio University

    2014.04
    -
    2015.03
    , 

    Spring Semester, Lecture

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Social Activities 【 Display / hide 】

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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 】

  • 2023.11
    -
    2030.03

    経済安全保障重要技術育成プログラム/小型無人機の自律制御・分散制御技術に係るプログラム・オフィサー, 国立研究開発法人新エネルギー・産業技術総合開発機構（NEDO）

  • 2023.10
    -
    2023.12

    令和五年度研究進捗中間確認会に係るアドバイザー, 国立研究開発法人宇宙航空研究開発機構

  • 2023.10
    -
    2025.09

    宇宙輸送系専門委員会 委員, 国立研究開発法人宇宙航空研究開発機構

  • 2023.10
    -
    2026.09

    第26期（令和5年10月～令和8年9月）機械工学委員会 委員, 日本学術会議

  • 2023.09
    -
    2025.03

    NEDO技術委員, 国立研究開発法人新エネルギー・産業技術総合開発機構（NEDO）

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