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Affiliation |
Faculty of Engineering, Division of Systems Research |
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Job Title |
Professor |
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Research Fields, Keywords |
Plasma Application, Electric Propulsion |
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Mail Address |
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Web Site |
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Related SDGs |
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TAKAO Yoshinori
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The Best Research Achievement in Research Career 【 display / non-display 】
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【Published Thesis】 Fabrication of nano-capillary emitter arrays for ionic liquid electrospray thrusters 2021.06
【Published Thesis】 Three-dimensional particle-in-cell simulation of a miniature plasma source for a microwave discharge ion thruster 2014.11
【Published Thesis】 A miniature electrothermal thruster using microwave-excited microplasmas: Thrust measurement and its comparison with numerical analysis 2007.06
The Best Research Achievement in the last 5 years 【 display / non-display 】
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【Published Thesis】 Direct detection of neutral species from ionic liquid electrospray thrusters in the purely ionic regime(Review of Scientific Instruments) 2025.07
【Published Thesis】 Electrospray Characteristics of High-Energetic Ionic Liquids: Ammonium Dinitramide and Hydroxyethylhydrazinium Nitrate(Journal of Propulsion and Power) 2025.11
【Published Thesis】 Simple model of multi-scale and multi-site emissions for porous ionic liquid electrospray thrusters(Journal of Applied Physics) 2024.06
【Published Thesis】 Emission measurements and in-situ observation of ionic liquid electrospray thrusters with longitudinally grooved emitters(Journal of Electric Propulsion) 2023.10
【Published Thesis】 Molecular Dynamics Simulations of Ion Extraction from Nanodroplets for Ionic Liquid Electrospray Thrusters(Journal of Electric Propulsion) 2022.09
Education 【 display / non-display 】
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2004.4-2007.3
Kyoto University Department of Aeronautics and Astronautics Doctor Course Completed
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2002.4-2004.3
Kyoto University Department of Aeronautics and Astronautics Master Course Completed
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1998.4-2002.3
Kyoto University Graduated
Degree 【 display / non-display 】
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Doctor of Engineering - Kyoto University
Campus Career 【 display / non-display 】
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2025.4
Duty Yokohama National UniversityFaculty of Engineering Division of Systems Research Professor
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2014.4-2025.3
Duty Yokohama National UniversityFaculty of Engineering Division of Systems Research Associate Professor
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2025.4
Concurrently Yokohama National UniversityCollege of Engineering Science Department of Mechanical Engineering, Materials Science and Ocean Engineering Professor
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2025.4
Concurrently Yokohama National UniversityGraduate school of Engineering Science Department of Mechanical Engineering, Materials Science and Ocean Engineering Professor
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2018.4-2025.3
Concurrently Yokohama National UniversityGraduate school of Engineering Science Department of Mechanical Engineering, Materials Science and Ocean Engineering Associate Professor
External Career 【 display / non-display 】
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2018.4-2020.3
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science Visiting Associate Professor
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2009.3-2014.3
Kyoto University Graduate School of Engineering, Department of Aeronautics and Astronautics Assistant Professor
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2007.4-2009.3
THine Electronics,Inc.
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2004.4-2007.3
Japan Society for the Promotion of Science Special researcher of the Japan Society for the Promotion of Science
Academic Society Affiliations 【 display / non-display 】
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2004
The American Institute of Aeronautics and Astronautics
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2004
The Japan Society for Aeronautical and Space Sciences
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2003
The Japan Society of Applied Physics
Research Areas 【 display / non-display 】
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Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering) / Aerospace engineering
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Energy Engineering / Basic plasma science
Research Career 【 display / non-display 】
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半導体プロセス用容量結合型プラズマ源の粒子計算モデル(PIC-MCC)構築
Project Year：
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磁気ノズルによるプラズマ加速
Project Year：
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マイクロ波放電式マイクロイオン推進機の粒子計算モデル(PIC-MCC)構築
Project Year：
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誘導結合型プラズマ源を用いた静電加速型マイクロイオン推進機の研究開発
Project Year：
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イオン液体を利用したエレクトロスプレー式マイクロスラスタの研究開発
Project Year：
Books 【 display / non-display 】
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技術情報協会（編集）（ Role： Contributor , 第5章 第9節）
技術情報協会 （ ISBN:978-4-86104-792-3 ）
Total pages：478 Responsible for pages：pp. 337-345 Language：Japanese Book type：Scholarly book
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プラズマプロセス技術 ナノ材料作製・加工のためのアトムテクノロジ
プラズマ核融合学会 (編集) （ Role： Contributor , 第4章）
森北出版 （ ISBN:9784627775619 ）
Language：Japanese Book type：Scholarly book
Thesis for a degree 【 display / non-display 】
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Development of a Miniature Electrothermal Thruster Using Microwave-Excited Microplasmas for Ultra Small Satellites
Y. Takao
2007.3
Doctoral Thesis Single Work [Reviewed]
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超小型推進機のためのマイクロプラズマ源とマイクロノズル流れの解析
鷹尾 祥典
2004.3
Master Thesis Single Work
京都大学大学院 工学研究科 航空宇宙工学専攻
超小型人工衛星の軌道・姿勢制御を用途としたマイクロ波励起マイクロプラズマスラスタを対象に、数値計算による性能見積もりを行った。解析にはマイクロプラズマ源とマイクロノズル流れを分けて行い、前者には体積平均モデルとマクスウェル方程式を利用し、後者には2温度モデルに基づくナビエ・ストークス方程式を利用した。分散関係式との比較により表面波の伝播を確認し、また、境界層が支配的なことから、ノズルの全長を短くすることが性能向上に望ましいと分かった。
Papers 【 display / non-display 】
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Ion Dynamics in Porous Emitter Ionic Liquid Electrospray Thrusters
TAKAGI Koki, TSUKIZAKI Ryudo, TAKAO Yoshinori
Journal of Evolving Space Activities 4 ( 0 ) 239 2026.4 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：宇宙技術および科学の国際シンポジウム Joint Work
<p>We report on the effect of feeding the propellant on the ion beam in porous ionic liquid electrospray thrusters and discuss it in the context of the ion dynamics in the ionic liquid. Ionic liquid electrospray thrusters are a promising, game-changing electric propulsion system that enables high ∆<i>V</i> even for small spacecraft. Especially, a porous emitter is beneficial for storing ionic liquids and is widely used in the development of electrospray thrusters. However, there are no guidelines for the design of propellant feeding in porous emitters. This is one of the bottlenecks in improving the thruster technology. To understand the effect of the pressure of the feeding, we applied feeding pressure to the emitter using a liquid column, using gravity to make it an actively fed system. This active feeding with positive pressure enhanced the emitted current. Based on the theoretical model in [Takagi et al., <i>J. Appl. Phys</i>, <b>135</b> (2024), 244502], applying feeding pressure increased the ion transport driven by the ion pressure gradient, resulting in an increase in the emitted current. The importance of controlling the feeding pressure for the porous emitter is thus clarified.</p>
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Numerical Investigation of Plasma Acceleration and Wave-Driven Transport in a Magnetic Nozzle
KITAUCHI Yuto, TAKAHASHI Kazunori, TAKAO Yoshinori
Journal of Evolving Space Activities 4 ( 0 ) n/a 2026 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：宇宙技術および科学の国際シンポジウム Joint Work
<p>Plasma particle simulations were conducted using a three-dimensional particle-in-cell simulation with a Monte Carlo collision method (PIC/MCC) to investigate instabilities that could cause cross-field electron transport in a magnetic nozzle. The plasma was located upstream of the divergent magnetic field, in order to reduce the computational cost while effectively reproducing the acceleration process in the magnetic nozzle. The simulation results were qualitatively consistent with experimental observations, showing that plasma instabilities develop in the downstream region. Furthermore, it was demonstrated that low-frequency waves contributed to the inward transport of electrons, leading to electron detachment from the magnetic nozzle.</p>
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Flow Rate Influence on Ion Beam Characteristics for Externally Wetted Electrospray Thrusters
YASUNO Ayane, TAKAO Yoshinori
Journal of Evolving Space Activities 4 ( 0 ) n/a 2026 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：宇宙技術および科学の国際シンポジウム Joint Work
<p>Electrospray thrusters have attracted attention as compact propulsion systems capable of precise thrust control. The thrust of electrospray thrusters depends on the ion beam current and ion mass, and the form of the emitted ions varies depending on the flow rate of the ionic liquid supplied to the emitter. Therefore, it is necessary to understand the effect of the flow rate on the beam characteristics in order to optimize the thruster performance. In this study, we have developed a pressure-based flow control system to vary the flow rate of the ionic liquid to externally wetted emitters, and measured the ion beam currents to evaluate their characteristics. We find that the beam current tends to increase with increasing supply pressure, and that the current–voltage characteristic depends on the flow rate.</p>
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Evaluation of AMU as an Ionic Liquid for Multi-Mode Propulsion Using a Porous Ionic Liquid Electrospray Thruster
ARAKAKI Yoshito, TAKAGI Koki, YAMASHITA Yusuke, TAKAO Yoshinori, TSUKIZAKI Ryudo
Journal of Evolving Space Activities 4 ( 0 ) n/a 2026 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Publisher：宇宙技術および科学の国際シンポジウム Joint Work
<p>Recently, multimode propulsions that use the same ionic liquids (ILs) for electric and chemical propulsion, such as ammonium dinitramide (ADN) and hydroxylammonium nitrate (HAN), have been developed. In this study, an IL electrospray thruster was operated with an ADN-based energetic IL, and its characteristics were compared with a conventional IL, 1-ethyl-3-methylimidazolium tetrafluoroborate (EMI-BF<sub>4</sub>). The plume composition was analyzed using the time of flight (ToF), and the thruster performance was evaluated with an analytical balance. A broader mass distribution is observed for ADN-based energetic IL in ToF. In addition, the ADN-based energetic IL showed ranges of 225 – 415 s in specific impulse and 4.1 – 11.3% in thrust efficiency, while the conventional IL showed 446 – 876 s and 7.1 – 18.1%, respectively. Although these thruster performance obtained by the analytical balance include relatively large uncertainty due to several factors (e.g., instability in thruster operation and electrochemical reactions), the results confirm that AMU can operate as an electrospray propellant and is promising for multimode propulsion.</p>
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Date, S; Omori, R; Izato, Y; Takao, Y
Journal of Propulsion and Power 2025.11 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
Review Papers 【 display / non-display 】
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TAKAO Yoshinori
Oyo Buturi 90 ( 5 ) 298 - 302 2021.5 [Reviewed] [Invited]
Language：Japanese Publishing type：Article, review, commentary, editorial, etc. (scientific journal) Publisher：The Japan Society of Applied Physics Single Work
<p>In recent years, many nano/microsatellites have been launched in space for various applications in near-earth orbit, and they are now used even for deep-space exploration. The situation naturally requires a micropropulsion system or microthruster. It is expected that electric propulsion will play an important role in achieving the required velocity increment (⊿<i>v</i>) because nano/microsatellites have strict constraints on space and weight. In this paper, we focus on two types of microthrusters, an ion engine and an electrospray thruster, which obtain thrust by electrostatically accelerating ions, and describe their characteristics, current results, and some issues. We also introduce electron sources, which do not directly contribute to thrust but are essential components.</p><p>In recent years, many nano/microsatellites have been launched in space for various applications in near-earth orbit, and they are now used even for deep-space exploration. The situation naturally requires a micropropulsion system or microthruster. It is expected that electric propulsion will play an important role in achieving the required velocity increment (⊿<i>v</i>) because nano/microsatellites have strict constraints on space and weight. In this paper, we focus on two types of microthrusters, an ion engine and an electrospray thruster, which obtain thrust by electrostatically accelerating ions, and describe their characteristics, current results, and some issues. We also introduce electron sources, which do not directly contribute to thrust but are essential components.</p>
Other Link： https://ci.nii.ac.jp/naid/130008034658
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鷹尾 祥典
油空圧技術 59 ( 9 ) 12 - 18 2020.9
Language：Japanese Publishing type：Article, review, commentary, editorial, etc. (trade magazine, newspaper, online media) Publisher：日本工業出版 Single Work
Other Link： https://www.nikko-pb.co.jp/products/detail.php?product_id=4897
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Current status of a magnetic nozzle RF plasma thruster
TAKAHASHI Kazunori, CHARLES Christine, BOSWELL Rod, TAKAO Yoshinori, ANDO Akira
Space Solar Power Systems 5 ( 0 ) 14 - 17 2020.2
Language：Japanese Publishing type：Article, review, commentary, editorial, etc. (scientific journal) Publisher：Space Solar Power Systems Society Joint Work
<p> The magnetic nozzle RF plasma thruster simply consists of a radiofrequency (RF) discharge and a magnetic nozzle. The high density plasma produced by inductively-coupled and/or helicon-wave-coupled discharge is transported along the axial magnetic field lines to the open source exit; the spontaneous plasma acceleration and momentum conversion processes seem to contribute to enhance the thrust generation. Current status of the studies on the fundamental physics and the performance improvement will be shown here.</p><p> The magnetic nozzle RF plasma thruster simply consists of a radiofrequency (RF) discharge and a magnetic nozzle. The high density plasma produced by inductively-coupled and/or helicon-wave-coupled discharge is transported along the axial magnetic field lines to the open source exit; the spontaneous plasma acceleration and momentum conversion processes seem to contribute to enhance the thrust generation. Current status of the studies on the fundamental physics and the performance improvement will be shown here.</p>
Other Link： https://ci.nii.ac.jp/naid/130007799145
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Discussion for Orbital Transfer Vehicle Using Electric Propulsion
FUNAKI Ikkoh, NAKANO Masakatsu, KOMURASAKI Kimiya, TAKAO Yoshinori, YOKOTA Shigeru, CHO Shinatora, … Show more authors
FUNAKI Ikkoh, NAKANO Masakatsu, KOMURASAKI Kimiya, TAKAO Yoshinori, YOKOTA Shigeru, CHO Shinatora, KAWASHIMA Rei Hide authors
Space Solar Power Systems 5 ( 0 ) 1 - 2 2020.2
Language：Japanese Publishing type：Article, review, commentary, editorial, etc. (scientific journal) Publisher：Space Solar Power Systems Society Joint Work
<p> A panel discussion was held to discuss the technical challenges in orbital transfer vehicle (OTV) development using electric propulsion. Electric propulsion is advantageous in the transportation of SSPS if the solar array panel in the payload can be used in the OTV. Argon is the candidate for the propellant, and the technical issues for the development of high-power argon-propellant thruster are discussed. The collaboration with the ground launch vehicle is indispensable to attain the SSPS, in addition to the cross-field collaboration for the optimization of the OTV. The necessity of technology demonstration missions and technical roadmap is reconfirmed to promote the collaboration among the researchers.</p><p> A panel discussion was held to discuss the technical challenges in orbital transfer vehicle (OTV) development using electric propulsion. Electric propulsion is advantageous in the transportation of SSPS if the solar array panel in the payload can be used in the OTV. Argon is the candidate for the propellant, and the technical issues for the development of high-power argon-propellant thruster are discussed. The collaboration with the ground launch vehicle is indispensable to attain the SSPS, in addition to the cross-field collaboration for the optimization of the OTV. The necessity of technology demonstration missions and technical roadmap is reconfirmed to promote the collaboration among the researchers.</p>
Other Link： https://ci.nii.ac.jp/naid/130007799144
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Research and Development of Ultra-Small High-Thrust-Density Electrospray Thrusters
Yoshinori TAKAO, Toshiyuki TSUCHIYA, Masayoshi NAGAO, Katsuhisa MURAKAMI
Aeronautical and Space Sciences Japan 67 ( 1 ) 5 - 11 2019.1 [Reviewed] [Invited]
Language：Japanese Publishing type：Article, review, commentary, editorial, etc. (scientific journal) Joint Work
Industrial Property Rights 【 display / non-display 】
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イオン源
鷹尾祥典，長尾昌善，村上勝久
Application no：2017-197041 Date applied：2017.10.10
Patent/Registration no：6927493 Date issued：2021.8.10
Country of applicant：Domestic
Awards 【 display / non-display 】
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The 78th JSAP Autumn Meeting 2017, Poster Award
2017.10 Japan Society of Applied Physics(JSAP) Fabrication of electrospray thrusters using Minimum System
Individual or group name of awards：Masayoshi Nagao,Naoki Inoue,Yoshinori Takao,Nariyuki Tasumi,Katsuhisa Murakami,Sommawan Khumpang,Shiro Hara
Grant-in-Aid for Scientific Research 【 display / non-display 】
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超小型エレクトロスプレー宇宙推進機における「疑似」質量損失機構の解明
Grant number：24K01076 2024.4 - 2027.3
Grant-in-Aid for Scientific Research(B)
Authorship：Principal investigator Grant type：Competitive
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Grant number：23H05442 2023.4 - 2028.3
Grant-in-Aid for Scientific Research(S)
Investigator(s)：高橋 和貴
Authorship：Coinvestigator(s) Grant type：Competitive
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効率と安定性のトレードオフ限界を超える超小型直流放電の実現とイオン推進機への応用
Grant number：22K18855 2022.6 - 2025.3
Grant-in-Aid for Challenging Research (Exploratory)
Investigator(s)：鷹尾 祥典
Authorship：Principal investigator Grant type：Competitive
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微小電極間エレクトロスプレー現象解明による超小型宇宙推進機の多用途化
Grant number：21H01530 2021.4 - 2024.3
科学研究費補助金 Grant-in-Aid for Scientific Research(B)
Investigator(s)：鷹尾 祥典
Authorship：Principal investigator Grant type：Competitive
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高密度イオン推進機のデジタルツイン創成と電子異常輸送制御法の確立
2020.4 - 2024.3
科学研究費補助金 Grant-in-Aid for Scientific Research(B)
Investigator(s)：川嶋 嶺
Grant type：Competitive
Other external funds procured 【 display / non-display 】
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将来深宇宙探査に向けた革新的超小型推進システム技術実証RG
2025.5 - 2026.2
2025年度宇宙工学委員会戦略的開発研究費
Authorship：Coinvestigator(s)
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将来深宇宙探査に向けた革新的超小型推進システム技術実証RG
2024.6 - 2025.2
2024年度宇宙工学委員会戦略的開発研究費
Authorship：Coinvestigator(s)
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将来深宇宙探査に向けた革新的超小型推進システム技術実証RG
2023.6 - 2024.2
2023年度宇宙工学委員会戦略的開発研究費
Authorship：Coinvestigator(s)
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将来深宇宙探査に向けた革新的超小型推進システム技術実証RG
2022.7 - 2023.2
2022年度宇宙工学委員会戦略的開発研究費
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90%超の効率を維持した推力可変な宇宙推進機
Grant number：JPMJFR2129 2022.4 - 2029.3
Japan Science and Technology Agency 創発的研究支援事業
Investigator(s)：鷹尾 祥典
Authorship：Principal investigator
Presentations 【 display / non-display 】
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Ion and Neutral Emissions from Ionic Liquid Electrospray Thrusters
Yoshinori Takao [Invited]
The 248th ECS Meeting 2025.10 The Electrochemical Society
Event date： 2025.10
Language：English Presentation type：Oral presentation (general)
Venue：Chicago, IL, USA
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Ionic Liquid Electrospray Ion Sources for Space Propulsion
Yoshinori Takao [Invited]
The 243rd ECS Meeting 2023.5 The Electrochemical Society
Event date： 2023.5 - 2023.6
Language：English Presentation type：Oral presentation (invited, special)
Venue：Boston, MA, USA
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Electron transport and plasma instability in ECR plasma discharges for a miniature ion thruster
Yoshinori Takao, Kenta Hiramoto, Kengo Nakamura, Yosuke Sato, and Hiroyuki Koizumi [Invited]
4th Asia-Pacific Conference on Plasma Physics (AAPPS-DPP2020) 2020.10
Event date： 2020.10
Language：English Presentation type：Oral presentation (invited, special)
Venue：Remote e-conference
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Particle Simulations of 1-cm Class Plasma Sources with Applied Magnetic Fields and Their Application to Space Propulsion
Yoshinori Takao [Invited]
Plasma Conference 2017
Event date： 2017.11
Language：English Presentation type：Oral presentation (invited, special)
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3D Particle Simulation for Electron Extraction Mechanisms of a Miniature Microwave Discharge Neutralizer
Kenta Hiramoto, Yuichi Nakagawa, Hiroyuki Koizumi, and Kimiya Komurasaki, Yoshinori Takao
Proceedings of the 52nd AIAA/SAE/ASEE Joint Propulsion Conference (Propulsion and Energy Forum),
Event date： 2016.7
Language：English Presentation type：Oral presentation (general)
Venue：Salt Lake City, USA
Past of Collaboration and Commissioned Research 【 display / non-display 】
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将来深宇宙探査に向けた革新的超小型推進システム技術実証RG
Offer organization: 宇宙航空研究開発機構 Cooperative Research within Japan
Project Year： 2025.5 - 2026.2
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将来深宇宙探査に向けた革新的超小型推進システム技術実証RG
Offer organization: 宇宙航空研究開発機構 Cooperative Research within Japan
Project Year： 2024.6 - 2025.2
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将来深宇宙探査に向けた革新的超小型推進システム技術実証RG
Offer organization: 宇宙航空研究開発機構 Cooperative Research within Japan
Project Year： 2023.6 - 2024.2
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将来深宇宙探査に向けた革新的超小型推進システム技術実証RG
Offer organization: 宇宙航空研究開発機構 Cooperative Research within Japan
Project Year： 2022.7 - 2023.2
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90%超の効率を維持した推力可変な宇宙推進機
Offer organization: 科学技術振興機構 Others
Project Year： 2022.4 - 2029.3
Charge of on-campus class subject 【 display / non-display 】
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2026 Thermodynamics 2
College of Engineering Science
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2026 Fundamentals of Propulsion Engineering
College of Engineering Science
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2026 Space Propulsion Engineering
Graduate school of Engineering Science
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2026 Design of Thermal and Fluid Systems A
Graduate school of Engineering Science
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2026 Design of Thermal and Fluid Systems B
Graduate school of Engineering Science
Committee Memberships 【 display / non-display 】
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日本航空宇宙学会 第57期電気推進・先端推進部門
2025.3 - 2026.2 委員
Committee type：Academic society
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京都大学生存圏研究所電波科学計算機実験共同利用・共同研究専門委員会
2024.4 - 2028.3 委員
Committee type：Academic society
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日本航空宇宙学会 第56期電気推進・先端推進部門
2024.3 - 2025.2 委員
Committee type：Academic society
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第35回宇宙技術および科学の国際シンポジウム徳島大会プログラム小委員会
2024.2 - 2025.7 委員
Committee type：Academic society
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Journal of Evolving Space Activities
2023.9 - 2024.3 Associate Editor
Committee type：Academic society
Media Coverage 【 display / non-display 】
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多孔質エミッタから放出イオンの理論モデル構築
科学新聞 2024.7
Author：Other