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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】 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
【Published Thesis】 Electron extraction enhancement via the magnetic field in a miniature microwave discharge neutralizer 2019.12
【Published Thesis】 Effects of negative ions on discharge characteristics of water plasma source for a miniature microwave discharge ion thruster 2019.04
【Awards】 ミニマルファブを用いたエレクトロスプレースラスタの試作 2017.09
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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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 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 / 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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Numerical investigation of internal plasma currents in a magnetic nozzle
Kazuma Emoto, Kazunori Takahashi, Yoshinori Takao
Physics of Plasmas 28 ( 9 ) 2021.9 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Publisher：AIP Joint Work
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Uniform needle-emitter arrays for ionic liquid electrospray thrusters with precise thrust control
60 ( SC ) SCCL06-1 - SCCL06-9 2021.6 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Joint Work
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Fabrication of nano-capillary emitter arrays for ionic liquid electrospray thrusters
Suzuki Kanta, Nagao Masayoshi, Liu Yongxun, Murakami Katsuhisa, Khumpuang Sommawan, Hara Shiro, Tak … Show more authors
Suzuki Kanta, Nagao Masayoshi, Liu Yongxun, Murakami Katsuhisa, Khumpuang Sommawan, Hara Shiro, Takao Yoshinori Hide authors
JAPANESE JOURNAL OF APPLIED PHYSICS 60 ( SC ) SCCF07-1 - SCCF07-6 2021.6 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Joint Work
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Increased Thrust-to-Power Ratio of a Stepped-Diameter Helicon Plasma Thruster with Krypton Propellant
Takahashi Kazunori, Takao Yoshinori, Ando Akira
JOURNAL OF PROPULSION AND POWER 36 ( 6 ) 961 - 965 2020.11 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Joint Work
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Design of High Efficiency Grid System for Water Propellant Miniature Ion Thrusters
NAKANO Masakatsu, NAKAMURA Kengo, NAKAGAWA Yuichi, TAKAO Yoshinori, KOIZUMI Hiroyuki
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 18 ( 6 ) 412 - 416 2020.11 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Publisher：一般社団法人 日本航空宇宙学会 Joint Work
<p>The two-grid ion optics of a water propellant miniature ion propulsion system (MIPS) was numerically studied by full-aperture ion-optics simulation considering an inhomogeneous plasma source in the discharge chamber. Three dominant ion species (H<sub>2</sub>O<sup>+</sup>, OH<sup>+</sup>, and H<sup>+</sup>) of water vapor plasma were included in the model. Their trajectories were tracked considering charge-exchange and elastic collisions between ions and neutral water molecules. The model was validated by experiments using the MIPS with two grids having 295 apertures each. The calculated accelerator impingement current agreed reasonably well with those obtained from the experiment. To increase its low propellant utilization efficiency, a new grid design method was introduced. This successfully improved neutral confinement by decreasing the diameter of the accelerator grid apertures without causing direct impingement of ions by optimizing the grid thickness distribution using the Particle In Cell-Monte Carlo Collision (PIC-MCC) calculation results.</p>
Other Link： https://ci.nii.ac.jp/naid/130007935946
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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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
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
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
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2019.4 - 2023.3
科学研究費補助金 Grant-in-Aid for Scientific Research(A)
Investigator(s)：高橋和貴
Grant type：Competitive
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電子放出面の電位構造が従来と逆になる電子源を用いた新規超小型イオン推進機の実現
2018.4 - 2021.3
科学研究費補助金 Grant-in-Aid for Challenging Research (Exploratory)
Investigator(s)：鷹尾 祥典
Grant type：Competitive
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推力密度の飛躍的な増加と冗長系の確保が可能な超小型エレクトロスプレー宇宙推進機
2018.4 - 2021.3
科学研究費補助金 Grant-in-Aid for Scientific Research(B)
Investigator(s)：鷹尾 祥典
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
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
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宇宙の利活用を飛躍的に高める超小型衛星用イオンエンジンの実現
2020.9 - 2022.8
2020年度研究助成金
Investigator(s)：鷹尾 祥典
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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
2017.11 - 2020.3
デブリ除去実証システムの共同研究および委託研究
Investigator(s)：鷹尾 祥典
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推力密度２桁増を目指す革新的エレクトロスプレー宇宙推進機の実現
2017.7 - 2018.3
平成29年度学術研究助成事業
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), (Salt Lake City, USA)
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), (Cleveland, USA)
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, (Washington, D.C., USA)
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, (Washington, D.C., USA)
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： 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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2021 機械工学国際インターンシップ
Graduate school of Engineering Science
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2021 サブ・リサーチ機械工学演習B
Graduate school of Engineering Science
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2021 サブ・リサーチ機械工学演習A
Graduate school of Engineering Science
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2021 機械工学特別研究
Graduate school of Engineering Science
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2021 機械工学学外研修
Graduate school of Engineering Science
Committee Memberships 【 display / non-display 】
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日本航空宇宙学会 第53期電気推進・先端推進部門
2021.3 - 2022.2 委員
Committee type：Academic society
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IEPC 2022
2020.6 - 2022.6 Technical Committee
Committee type：Academic society
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日本航空宇宙学会 第52期電気推進・先端推進部門
2020.3 - 2021.2 幹事
Committee type：Academic society
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日本航空宇宙学会 第51期電気推進・先端推進部門
2019.3 - 2020.2 幹事
Committee type：Academic society
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日本航空宇宙学会 第50期会誌集編集委員会
2018.5 - 2019.3 委員
Committee type：Academic society