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Affiliation |
Faculty of Engineering, Division of Systems Research |
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Job Title |
Associate 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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ORCID
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】 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
【Published Thesis】 Axial momentum gains of ions and electrons in magnetic nozzle acceleration(Plasma Sources Science and Technology) 2021.11
【Published Thesis】 Fabrication of nano-capillary emitter arrays for ionic liquid electrospray thrusters 2021.06
【Published Thesis】 Uniform needle-emitter arrays for ionic liquid electrospray thrusters with precise thrust control 2021.06
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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2014.4
Duty Yokohama National UniversityFaculty of Engineering Division of Systems Research Associate Professor
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2018.4
Concurrently Yokohama National UniversityGraduate school of Engineering Science Department of Mechanical Engineering, Materials Science and Ocean Engineering Associate Professor
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2017.4
Concurrently Yokohama National UniversityCollege of Engineering Science Department of Mechanical Engineering, Materials Science and Ocean Engineering Associate Professor
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2014.4
Concurrently Yokohama National UniversityGraduate School of Engineering Department of Systems Integration Associate Professor
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2014.4
Concurrently Yokohama National UniversityCollege of Engineering Science Department of Mechanical Engineering and Materials Science 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 Japan Society for Aeronautical and Space Sciences
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2004
The American Institute of Aeronautics and Astronautics
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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 / Fundamental plasma
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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Simple model of multi-scale and multi-site emissions for porous ionic liquid electrospray thrusters
Takagi, K; Yamashita, Y; Tsukizaki, R; Nishiyama, K; Takao, Y
Journal of Applied Physics 135 ( 24 ) 244502 2024.6 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Time-of-Flight Measurements of Ion Beam Compositions in Electrospray Thrusters
NAEMURA Momoko, TAKAO Yoshinori
Journal of Evolving Space Activities 2 146 2024.6 [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>Time-of-flight (ToF) mass spectroscopy for electrospray thrusters was constructed to investigate the species and fraction of ions in the beam and the presence of fragmentation, where a cylindrical shield was placed just in front of the collector. The shield was expected to prevent the detection of secondary species, which were recently found to be one of the vacuum facility effects. However, the shield seemed to have almost no effects on the ToF signals because the signal did not decrease to zero, and some particles were always detected as they had been detected without the shield. To examine the cause of this signal detection, the collector current was measured under the condition that the gate electrode completely blocked the ion beam. The results implied that the electrospray ion source also emitted some neutrals. The measurement system was reconstructed to detect ions using a high-speed amplifier to avoid neutral particle detection. Then, the results showed that the electrospray thruster was operating in the pure ion mode.</p>
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GUO Shujun, NAGAO Masayoshi, MURAKAMI Katsuhisa, MURATA Hiromasa, TAKAO Yoshinori
Journal of Evolving Space Activities 2 142 2024.6 [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>In this study, we have fabricated ionic liquid electrospray thrusters to prevent ionic liquid leakage and provide high current density. A double-emitter structure with a needle protruding from the capillary emitter, where the ionic liquid was intended to be held by the needle, was proposed. The fabrication process employs a fabrication technique of a field emitter array, and a newly designed process to reduce the distance between emitters was used to improve emitter density. As a result of the fabrication, the needle was successfully formed in the emitter electrode, and it was found that emitter density could be improved by changing the deposition conditions of multiple SiO<sub>2</sub> layers.<sup> </sup></p>
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Evaluation of Grooved Needle Emitter Performance for Ionic Liquid Electrospray Thrusters
MATSUKAWA Koki, TAKAO Yoshinori
Journal of Evolving Space Activities 2 149 2024.6 [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 have fabricated an externally wetted emitter array with a deep-grooved structure using grayscale lithography for ionic liquid electrospray thrusters to improve the ionic liquid transport to the emitter tips and to reduce the percentage of the current intercepted by the extractor electrode, which was more than 30% with our conventional deep-grooved emitter. The experimental results of the ion emission have shown that a stable ion emission characteristic and the percentage of the current intercepted by the extractor electrode decreases by approximately one-third compared with our previous one. This decrease indicates that the emitter fabrication process using grayscale lithography optimized the deep-grooved emitter shape.</p>
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Yoshinori Tanaka and Yoshinori Takao
Acta Astronautica 219 243 - 249 2024.3 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Single 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
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 - 2025.3
Japan Science and Technology Agency 創発的研究支援事業
Investigator(s)：鷹尾 祥典
Authorship：Principal investigator
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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
2021.6 - 2022.2
2021年度宇宙工学委員会戦略的開発研究費
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宇宙産業革命を担う超小型衛星船団に不可欠なマイクロ推進機
2021.4 - 2024.3
研究助成プログラム 「新産業を生む科学技術」
Investigator(s)：鷹尾 祥典
Presentations 【 display / non-display 】
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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
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Validation of a 3D Particle Simulation Model for a Miniature Microwave Discharge Ion Thruster
Yoshinori Takao, Koji Eriguchi, Kouichi Ono, Yuto Sugita, Hiroyuki Koizumi, and Kimiya Komurasaki
Proceedings of the 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference (Propulsion and Energy Forum),
Event date： 2014.7
Language：English Presentation type：Oral presentation (general)
Venue：Cleveland, USA
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Plasma Diagnostics in a Miniature Microwave Discharge Ion Thruster
Y. Sugita, H.Koizumi, R. Tsukizaki, H. Kuninaka, Y. Takao, Y. Yamagiwa, M. Matsui
Proceedings of the 33rd International Electric Propulsion Conference,
Event date： 2013.10
Language：English Presentation type：Oral presentation (general)
Venue：Washington, D.C., USA
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Three-Dimensional Particle-in-Cell Simulation of a Miniature Microwave Discharge Ion Thruster µ1
Y. Takao, K. Eriguchi, K. Ono, Y. Sugita, H. Koizumi, and K. Komurasaki
Proceedings of the 33rd International Electric Propulsion Conference,
Event date： 2013.10
Language：English Presentation type：Oral presentation (general)
Venue：Washington, D.C., 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： 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 - 2025.3
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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： 2021.6 - 2022.2
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イオン源と電子源双方の高電流密度化によるデブリ除去用軌道遷移技術の確立
Offer organization: 宇宙航空研究開発機構 Funded Research offered by Enterprises
Project Year： 2017.11 - 2020.3
Charge of on-campus class subject 【 display / non-display 】
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2024 Manufacturing of Thermal and Fluid Systems B
Graduate school of Engineering Science
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2024 Manufacturing of Thermal and Fluid Systems A
Graduate school of Engineering Science
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2024 Design of Thermal and Fluid Systems B
Graduate school of Engineering Science
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2024 Design of Thermal and Fluid Systems A
Graduate school of Engineering Science
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2024 Space Propulsion Engineering
Graduate school of Engineering Science
Committee Memberships 【 display / non-display 】
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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 - 2026.3 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 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
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日本学術振興会 DXプラズマプロセス委員会
2023.5 委員
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