Research Career 【 display / non-display 】

Research Career 【 display / non-display 】

• 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：

• 磁気ノズルによるプラズマ加速

  Project Year：

• 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

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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

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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

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Books 【 display / non-display 】

Books 【 display / non-display 】

• 宇宙ビジネス参入の留意点と求められる新技術、新材料

  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 ）

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  Total pages：478   Responsible for pages：pp. 337-345   Language：Japanese Book type：Scholarly book

• 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 ）

  Amazon

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  Language：Japanese Book type：Scholarly book

Thesis for a degree 【 display / non-display 】

Thesis for a degree 【 display / non-display 】

• Development of a Miniature Electrothermal Thruster Using Microwave-Excited Microplasmas for Ultra Small Satellites

  Y. Takao

  2007.3

  Doctoral Thesis   Single Work    [Reviewed]

• 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  

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  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 】

Papers 【 display / non-display 】

• Fabrication and Demonstration of SU-8 Based Emitter Arrays for Ionic Liquid Electrospray Thrusters

  SHINGU Takumi, NAGAO Masayoshi, MURAKAMI Katsuhisa, MURATA Hiromasa, KHUMPUANG Sommawan, HARA Shiro … Show more authors

  Journal of Evolving Space Activities   1 ( 0 )   n/a   2023  [Reviewed]

  DOI CiNii Research

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  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>A high-density emitter array for ionic liquid electrospray thrusters is fabricated using a fabrication process for field emitter arrays. SU-8 photoresist is employed as the inter-electrode material. The distance between the emitter and the extractor electrodes was about 10 µm, enough for about 1-kV application between the electrodes. Adequate thrust and specific impulse can be obtained without an accelerator electrode, resulting in a simple propulsion system. Optimal parameters for the photolithography of SU-8 are determined. The fabricated emitter array had a tip diameter of about 1 µm and an emitter density 200 times higher than conventional emitter arrays. A preliminary experiment for ion emissions showed a negative current of −79 nA at 800 V using a 4 × 4 emitter array in an area of 100 µm square, resulting in approximately twice as much current density as a conventional type.</p>

• Design and Fabrication of Ionic Liquid Electrospray Thruster with Two-Stage Electrodes

  NISHIMURA Akane, KATSUTA Hirohide, TAKAO Yoshinori, TSUCHIYA Toshiyuki

  Journal of Evolving Space Activities   1 ( 0 )   n/a   2023.3  [Reviewed]

  DOI CiNii Research

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  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>An ionic liquid electrospray thruster (ILEST) is expected as a propulsion system to control nano-spacecraft attitude and orbit in space. To produce high thrust, we propose a two-stage electrodes thruster which has an accelerator in addition to an extractor. We fabricated emitters on a silicon wafer and the two-stage electrodes on a glass substrate with through holes using microfabrication technologies. We confirmed that the fabricated ILEST emitted ions or droplets from the silicon emitters at near 2.0 kV. The maximum current in single-stage operation was -570 µA at 3.0 kV. With two-stage operation using the accelerator, ion emission happens at high voltage without conduction between the extractor and the accelerator. The results show the advantage of the fabricated two-stage electrodes. Currently, extracted ions were captured mostly at the extractor because of the poor alignment of the emitter silicon chip to the jig.</p>

• Density profile transition and high-energy electron transport in a magnetically expanding radio frequency plasma

  Emoto Kazuma, Takahashi Kazunori, Takao Yoshinori

  Physics of Plasmas   30 ( 1 )   2023.1  [Reviewed]

  DOI Web of Science

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  Language：English   Publishing type：Research paper (scientific journal)   Joint Work  

• Molecular Dynamics Simulations of Ion Extraction from Nanodroplets for Ionic Liquid Electrospray Thrusters

  Takaaki Enomoto, Shehan M. Parmar, Ryohei Yamada, Richard E. Wirz, Yoshinori Takao

  Journal of Electric Propulsion   1 ( 1 )   13 (21pp)   2022.9  [Reviewed]

  DOI

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  Authorship：Last author,　Corresponding author   Language：English   Publishing type：Research paper (scientific journal)   Publisher：Springer Science and Business Media {LLC}   Joint Work  

  <jats:title>Abstract</jats:title><jats:p>Molecular dynamics (MD) simulations were performed for ion extraction from electrospray thrusters to investigate relevant extraction processes numerically. To approximate the electrospray jet tip, a simulation domain consisting of 4-5 nm-sized ionic liquid droplets was used. The extracted ion angles and kinetic energies from EMI–BF<jats:sub>4</jats:sub> (1-ethyl-3-methylimidazolium tetrafluoroborate) and EMI–Im (1-ethyl-3-methylimidazolium bis((trifluoromethyl)sulfonyl)imide) droplets were quantified by applying uniform electric fields of 1.3–1.7 V nm<jats:sup>−1</jats:sup>. The MD simulations are in great agreement with simulations presented in the literature and consistently show a greater preference for monomer emission than reported experimentally. At field strengths above 1.5 V nm<jats:sup>−1</jats:sup>, apparent droplet fracturing and breakup lead to an increase in ion angular velocity distributions. Greater mobility of EMI–BF<jats:sub>4</jats:sub> ions than EMI–Im was also observed, indicative of the crucial role of cation-anion hydrogen bond strengths in ion extraction and beam composition between different propellants.</jats:p>

• Oxidation Resistance Improvement of Graphene-Oxide-Semiconductor Planar-Type Electron Sources Using h-BN as an Oxygen-Resistant, Electron-Transmissive Coating

  Naoyuki Matsumoto, Yoshinori Takao, Masayoshi Nagao, Katsuhisa Murakami

  ACS Omega   7 ( 37 )   33004 - 33009   2022.9  [Reviewed]

  DOI Web of Science

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  Language：English   Publishing type：Research paper (scientific journal)   Publisher：American Chemical Society ({ACS})   Joint Work  

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Review Papers 【 display / non-display 】

Review Papers 【 display / non-display 】

• Microthrusters indispensable for nano/microsatellites that will lead the next-generation space industry

  TAKAO Yoshinori

  Oyo Buturi   90 ( 5 )   298 - 302   2021.5  [Reviewed]  [Invited]

  DOI CiNii Research

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  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

• イオンエンジン

  鷹尾 祥典

  油空圧技術   59 ( 9 )   12 - 18   2020.9

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  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

• Discussion for Orbital Transfer Vehicle Using Electric Propulsion

  FUNAKI Ikkoh, NAKANO Masakatsu, KOMURASAKI Kimiya, TAKAO Yoshinori, YOKOTA Shigeru, CHO Shinatora, … Show more authors

  Space Solar Power Systems   5 ( 0 )   1 - 2   2020.2

  DOI CiNii Research

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  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

• 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

  DOI CiNii Research

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  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

• 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]

  DOI

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  Language：Japanese   Publishing type：Article, review, commentary, editorial, etc. (scientific journal)   Joint Work  

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Industrial Property Rights 【 display / non-display 】

Industrial Property Rights 【 display / non-display 】

• イオン源

  鷹尾祥典，長尾昌善，村上勝久

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  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 】

Awards 【 display / non-display 】

• 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 】

Grant-in-Aid for Scientific Research 【 display / non-display 】

• 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

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  Authorship：Principal investigator  Grant type：Competitive

• 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

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  Authorship：Principal investigator  Grant type：Competitive

• 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

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  Grant type：Competitive

• 磁気ノズル中のプラズマ運動量輸送とディタッチメント

  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

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  Authorship：Coinvestigator(s)  Grant type：Competitive

• 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

  Grant number：18K18910  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

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  Authorship：Principal investigator  Grant type：Competitive

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Other external funds procured 【 display / non-display 】

Other external funds procured 【 display / non-display 】

• 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

• 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

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  Authorship：Principal investigator 

• 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

• 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

• 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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Presentations 【 display / non-display 】

Presentations 【 display / non-display 】

• Particle Simulations of 1-cm Class Plasma Sources with Applied Magnetic Fields and Their Application to Space Propulsion

  Yoshinori Takao  [Invited]

  Plasma Conference 2017 

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  Event date： 2017.11

  Language：English   Presentation type：Oral presentation (invited, special)  

• 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), 

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  Event date： 2016.7

  Language：English   Presentation type：Oral presentation (general)  

  Venue：Salt Lake City, USA  

• 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), 

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  Event date： 2014.7

  Language：English   Presentation type：Oral presentation (general)  

  Venue：Cleveland, USA  

• 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, 

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  Event date： 2013.10

  Language：English   Presentation type：Oral presentation (general)  

  Venue：Washington, D.C., USA  

• 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,  

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  Event date： 2013.10

  Language：English   Presentation type：Oral presentation (general)  

  Venue：Washington, D.C., USA  

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Past of Collaboration and Commissioned Research 【 display / non-display 】

Past of Collaboration and Commissioned Research 【 display / non-display 】

• 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 an affiliated university or institute  

  Project Year： 2022.7  -  2023.2 

• 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 

• 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 

• 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 】

Charge of on-campus class subject 【 display / non-display 】

• 2023   Fundamentals of Propulsion Engineering

  College of Engineering Science

• 2023   Thermodynamics 2

  College of Engineering Science

• 2023   Space Propulsion Engineering, Advanced

  Graduate school of Engineering Science

• 2023   Manufacturing of Thermal and Fluid Systems B

  Graduate school of Engineering Science

• 2023   Manufacturing of Thermal and Fluid Systems A

  Graduate school of Engineering Science

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Committee Memberships 【 display / non-display 】

Committee Memberships 【 display / non-display 】

• 日本航空宇宙学会 第55期電気推進・先端推進部門

  2023.3 - 2024.2  委員

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  Committee type：Academic society 

• Editorial Board of Advanced Space Propulsion

  2022.5 - 2024.4  Associate Editor

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  Committee type：Academic society 

• The 10th Asian Joint Conference on Propulsion and Power 実行委員会

  2022.4 - 2023.3  委員

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  Committee type：Academic society 

• 日本航空宇宙学会 第54期電気推進・先端推進部門

  2022.3 - 2023.2  委員

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  Committee type：Academic society 

• 次世代真空エレクトロニクス研究会

  2021.6  学界委員

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  Committee type：Academic society 

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