Updated on 2022/04/01

写真a

 
ICHIHARA Daisuke
 
Organization
Graduate School of Engineering Aerospace Engineering 1 Assistant Professor
Graduate School
Graduate School of Engineering
Undergraduate School
School of Engineering Mechanical and Aerospace Engineering
Title
Assistant Professor
Contact information
メールアドレス

Degree 1

  1. Doctor(Engineering) ( 2017.9   Nagoya University ) 

Research Interests 4

  1. Plasma

  2. Electric propulsion

  3. Electric propulsion

  4. Plasma

Research Areas 2

  1. Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering) / Aerospace engineering  / Aerospace Engineering

  2. Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering) / Aerospace engineering

Current Research Project and SDGs 1

  1. Research and Development of Electric Propulsion

Research History 6

  1. Nagoya University   Institute for Space-Earth Environmental Research Center for Orbital and Suborbital Research   Researcher

    2018.10

  2. Nagoya University   Institute for Space-Earth Environmental Research Center for Orbital and Suborbital Research   Researcher

    2018.10

  3. Graduate School of Engineering, Nagoya University   Department of Aerospace Engineering   Assistant Professor

    2017.10

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    Country:Japan

  4. Graduate School of Engineering, Nagoya University   Department of Aerospace Engineering   Assistant Professor

    2017.10

  5. Graduate School of Engineering, Nagoya University   Department of Aerospace Engineering   Assistant Professor

    2017.10

  6. NEC Corporation   staff

    2013.4 - 2014.3

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    Country:Japan

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Education 4

  1. Nagoya University   Graduate School, Division of Engineering   Department of Aerospace Engineering

    2014.10 - 2017.9

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    Country: Japan

  2. Nagoya University   Graduate School, Division of Engineering   Department of Aerospace Engineering

    2014.10 - 2017.9

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    Country: Japan

  3. Nagoya University   Graduate School, Division of Engineering   Department of Aerospace Engineering

    2014.10 - 2017.9

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    Country: Japan

  4. Nagoya University   Faculty of Engineering   Mechanical and Aerospace Engineering

    2007.4 - 2011.3

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    Country: Japan

Professional Memberships 2

  1. The Japan Society for Aeronautical and Space Science

  2. The Japan Society for Aeronautical and Space Science

Committee Memberships 2

  1. 日本航空宇宙学会中部支部   幹事  

    2019.3 - 2021.2   

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    Committee type:Academic society

  2. 日本航空宇宙学会中部支部   幹事  

    2019.3 - 2020.2   

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    Committee type:Academic society

 

Papers 15

  1. Electrostatic-magnetic hybrid ion acceleration for high-thrust-density operation

    Ichihara D., Nakano R., Nakamura Y., Kinefuchi K., Sasoh A.

    JOURNAL OF APPLIED PHYSICS   Vol. 130 ( 22 )   2021.12

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    Language:Japanese   Publisher:Journal of Applied Physics  

    To achieve high-thrust-density operation, we propose electrostatic-magnetic hybrid ion acceleration in which the empirical thrust density limit of the electrostatic acceleration is surpassed without violent plasma oscillation by combing the collisional momentum transfer mechanism, which is the ion acceleration mechanism of the electromagnetic acceleration. To achieve hybrid ion acceleration, we experimentally obtained two design criteria: one near anode propellant injection and another at the on-axis hollow cathode location. The thrust characteristics of three thrusters composed of a slowly diverging magnetic field between an on-axis hollow cathode and a coaxially set ring anode were examined. By injecting xenon propellant along the anode inner surface, the electron impact ionization process was enhanced, and generated ions are electrostatically accelerated through the radial-inward potential gradient perpendicular to the axial magnetic lines of force. The hybrid ion acceleration characteristics were obtained only if these two criteria were satisfied and the obtained thrust was consistent with the thrust formula derived for steady-state, quasi-neutral plasma flows. In addition to the criteria, strengthening the magnetic field and enhancing the propellant mass flux were effective for improving thrust density without deteriorating thrust efficiency. Among the experimental conditions in this study, the maximum thrust density was 70 N/m2 with an anode specific impulse of 1200 s, which cannot be achieved in a purely electrostatic thruster with thrust density 6.3 times than that of a typical Hall thruster.

    DOI: 10.1063/5.0066083

    Web of Science

    Scopus

  2. Energy conversion efficiency of electrical exploding foil accelerators

    Ichihara D., Fukushima G., Kuwabara D., Sasoh A.

    AIP ADVANCES   Vol. 11 ( 9 )   2021.9

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    Language:Japanese   Publisher:AIP Advances  

    We evaluate the energy conversion efficiency of an electrical exploding foil accelerator that accelerates a thin dielectric foil (called the flyer) to more than 1 km/s, which is propelled by electrically exploded bridge material. The effective flyer mass ejected from the accelerator is estimated by impulse measurements obtained using a gravity pendulum as well as by time-resolving flyer velocity measurements obtained using a photonic Doppler velocimetry system. For two different bridge sizes (0.2 and 0.4 mm), the flyer velocity and impulse increase with the input energy at the bridge section. The maximum flyer velocity and impulse, that is, 4.0 km/s and 67 µN s, respectively, are obtained by supplying 0.33 J of input energy. Upon increasing the input energy, the effective flyer mass also increases and exceeds the designed-bridge mass for both bridge sizes. The energy conversion efficiency from input electrical energy to flyer kinetic energy is calculated based on the effective flyer mass, velocity, and input energy. Both bridge sizes show comparable efficiencies: 27% and 30% for 0.2 and 0.4 mm bridges, respectively. The efficiency increases with increasing specific input energy at least up to 15 MJ/kg for the 0.4 mm bridge, whereas the efficiency of the 0.2 mm bridge above 30 MJ/kg decreases. This is owing to the excessively high input energy density in the 0.2 mm bridge, which causes the effective flyer mass to increase by including surrounding materials. These results indicate that the specific input energy should be optimized for obtaining maximum efficiency.

    DOI: 10.1063/5.0061699

    Web of Science

    Scopus

  3. Modelling of a 1 T High-Temperature Superconducting Applied Field Module for a Magnetoplasmadynamic Thruster

    Olatunji J.R., Strickland N.M., Goddard Winchester M.R., Kinefuchi K., Ichihara D., Long N.J., Wimbush S.C.

    IEEE Region 10 Annual International Conference, Proceedings/TENCON   Vol. 2021-December   page: 173 - 178   2021

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    Language:Japanese   Publisher:IEEE Region 10 Annual International Conference, Proceedings/TENCON  

    Magnetoplasmadynamic thrusters are a form of electric propulsion for space applications that use magnetic and electric fields to accelerate plasma from a spacecraft to generate thrust. It has been shown experimentally and theoretically that applying a strong magnetic field to an MPD thruster can improve thrust and efficiency and lower the required discharge current. This work presents concept design and modelling of a 1 T high-Temperature superconducting applied field module cooled by a miniaturised cryocooler targeting an existing thruster. Using a 3D finite element modelling approach, thermal and electromagnetic predictions of the mechanical assembly are performed, which include temperature dependent thermal properties of the mechanical components and temperature and field dependent critical current anisotropy of the superconductor. The model was used to generate design curves to determine the operational temperature required to achieve central fields up to 2.5 T.

    DOI: 10.1109/TENCON54134.2021.9707308

    Scopus

  4. Thrust Density Enhancement in an Electrostatic-Magnetic Hybrid Thruster

    Ichihara Daisuke, Oka Koichiro, Higo Ayumi, Nakamura Yusuke, Kinefuchi Kiyoshi, Sasoh Akihiro

    JOURNAL OF PROPULSION AND POWER   Vol. 37 ( 6 ) page: 973 - 976   2021

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    Language:Japanese   Publisher:Journal of Propulsion and Power  

    DOI: 10.2514/1.B38480

    Web of Science

    Scopus

  5. Central and External Cathode Operations in a Diverging-Magnetic-Field Electrostatic Thruster

    Ichihara Daisuke, Nakagawa Yoshiya, Iwakawa Akira, Sasoh Akihiro

    JOURNAL OF PROPULSION AND POWER   Vol. 36 ( 1 ) page: 68-77   2020

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

    DOI: 10.2514/1.B37636

    Web of Science

  6. High-Specific-Impulse Electrostatic Thruster with Argon Propellant

    Ichihara Daisuke, Matsuba Toshihiro, Iwakawa Akira, Sasoh Akihiro

    JOURNAL OF PROPULSION AND POWER   Vol. 36 ( 2 ) page: 256 - 263   2020

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    Language:Japanese   Publishing type:Research paper (scientific journal)  

    DOI: 10.2514/1.B37675

    Web of Science

    Scopus

  7. Boundary Effect on the Laser-ablation Impulse Characteristics of a Flat-Head Cylinder

    Katagiri Yusuke, Ichihara Daisuke, Tsuruta Hisashi, Sasoh Akihiro

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES   Vol. 63 ( 3 ) page: 109 - 112   2020

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    Language:Japanese   Publishing type:Research paper (scientific journal)   Publisher:THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

    DOI: 10.2322/tjsass.63.109

    Web of Science

    Scopus

    CiNii Research

  8. Similar Thrust Performance in Diverging-Magnetic-Field Electrostatic Thruster with Monoatomic Propellants

    Ichihara Daisuke, Sasoh Akihiro

    JOURNAL OF PROPULSION AND POWER   Vol. 35 ( 1 ) page: 236 - 238   2019.1

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    Language:Japanese   Publishing type:Research paper (scientific journal)  

    DOI: 10.2514/1.B37294

    Web of Science

    Scopus

  9. Electrostatic-magnetic-hybrid thrust generation in central-cathode electrostatic thruster (CC-EST)

    Sasoh Akihiro, Kasuga Hayato, Nakagawa Yoshiya, Matsuba Toshihiro, Ichihara Daisuke, Iwakawa Akira

    ACTA ASTRONAUTICA   Vol. 152   page: 137 - 145   2018.11

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    Language:Japanese   Publishing type:Research paper (scientific journal)  

    DOI: 10.1016/j.actaastro.2018.07.052

    Web of Science

    Scopus

  10. Effects of magnetic field profile near anode on ion acceleration characteristics of a diverging magnetic field electrostatic thruster Reviewed

    D. Ichihara, A. Iwakawa, A. Sasoh

    Journal of Applied Physics   Vol. 122   2017.7

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    Authorship:Lead author   Language:English   Publishing type:Research paper (scientific journal)  

    DOI: 10.1063/1.4995286

  11. Power matching between plasma generation and electrostatic acceleration in helicon electrostatic thruster Reviewed

    D. Ichihara, Y. Nakagawa, A. Uchigashima, A. Iwakawa, A. Sasoh

    Acta Astronautica   Vol. 139   page: 157-164   2017.7

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    Authorship:Lead author   Language:English   Publishing type:Research paper (scientific journal)  

    DOI: 10.1016/j.actaastro.2017.06.032

  12. Ten-Ampere-Level, Applied-Field-Dominant Operation in Magnetoplasmadynamic Thrusters

    Daisuke Ichihara, Tomoki Uno, Hisashi Kataoka, Jaehun Jeong, Akira Iwakawa, Akihiro Sasoh

    JOURNAL OF PROPULSION AND POWER   Vol. 33 ( 2 ) page: 360 - 369   2017.3

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    Language:Japanese   Publishing type:Research paper (scientific journal)   Publisher:AMER INST AERONAUTICS ASTRONAUTICS  

    In this paper, applied-field magnetoplasmadynamic thrusters were operated with a discharge current lower than 20A and an argon propellant flow rate under 4.0mg/s by using a thermionic electron emission-type hollow cathode. Both axisymmetric and rectangular channel configurations were examined. The characteristic value of the ratio of the applied-field electromagnetic thrust to the self-field electromagnetic thrust, which was a maximum of approximately 50 in previous research, increased to more than 800 in this study, whereas the specific power was in approximately the same range as in previous studies. The trends of thrust and discharge voltage were explained by referring to the swirl acceleration model. Such operation could be useful for near-future high-power electric propulsion applications.

    DOI: 10.2514/1.B36179

    Web of Science

    Scopus

  13. Electrostatic ion acceleration across a diverging magnetic field Reviewed

    D. Ichihara, A. Uchigashima, A. Iwakawa, A. Sasoh

    Applied Physics Letters   Vol. 109   2016.8

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    Authorship:Lead author   Language:English   Publishing type:Research paper (scientific journal)  

    DOI: 10.1063/1.4960363

  14. Anode Geometry Effects on Ion Beam Energy Performance in Helicon Electrostatic Thruster Reviewed

    Akira Uchigashima, Teruaki Baba, Daisuke Ichihara, Akira Iwakawa, Akihiro Sasoh, Takuya Yamazaki, Shota Harada, Matsutaka Sasahara, Tomoji Iwasaki

    IEEE TRANSACTIONS ON PLASMA SCIENCE   Vol. 44 ( 3 ) page: 306-313   2016.3

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

    DOI: 10.1109/TPS.2016.2522079

  15. 矩形断面形状を有する定常・外部磁場印加MPDスラスターの作動特性 Reviewed

    市原大輔,原田翔太,片岡久志,横田茂,佐宗章弘

    日本航空宇宙学会論文集   Vol. 63 ( 2 ) page: 37-44   2015.3

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    Authorship:Lead author   Language:Japanese   Publishing type:Research paper (scientific journal)  

    DOI: 10.2322/jjsass.63.37

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Presentations 10

  1. Effects of magnetic field configuration on thrust performance of a diverging magnetic field electrostatic thruster (DM-EST)

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    Event date: 2018.1

    Language:Japanese   Presentation type:Oral presentation (general)  

    Country:Japan  

  2. RF vs. Acceleration Power Distribution in Helicon Electrostatic Thruster International conference

    Daisuke Ichihara, Yoshiya Nakagawa, Akira Iwakawa, Akihiro Sasoh, Takuya Yamazaki

    The 35th International Electric Propulsion Conference 

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    Event date: 2017.10

    Language:English   Presentation type:Oral presentation (general)  

    Venue:Georgia Institute of Technology   Country:United States  

  3. Operation Characteristics of Diverging Magnetic Field Electrostatic Thruster International conference

    Daisuke Ichihara, Akira Iwakawa, Akihiro Sasoh

    The 35th International Electric Propulsion Conference 

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    Event date: 2017.10

    Language:English   Presentation type:Oral presentation (general)  

    Venue:Georgia Institute of Technology   Country:United States  

  4. Applied-Field MPD Thruster with Magnetic-Contoured Anodes International conference

    Tatsuya Kimura, Kohei Kojima, Masaaki Yasui, Daisuke Ichihara, Tomoki Uno, Hisashi Kataoka, Akira Iwakawa, Akihiro Sasoh, Shigeru Yokota

    34th International Electric Propulsion Conference 

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    Event date: 2015.7

    Language:English   Presentation type:Oral presentation (general)  

    Venue:Hyogo-Kobe, Japan   Country:Japan  

  5. Electric Propulsion System using a Helicon Plasma Thruster International conference

    Takuya Yamazaki, Shota Harada, Matsutaka Sasahara, Tomoji Iwasaki, Akira Uchigashima, Daisuke Ichihara, Akira Iwakawa, Akihiro Sasoh

    34th International Electric Propulsion Conference 

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    Event date: 2015.7

    Language:English   Presentation type:Oral presentation (general)  

    Venue:Hyogo-Kobe   Country:Japan  

  6. Development of Helicon Electrostatic Thruster (HEST) International conference

    Akira Uchigashima, Teruaki Baba, Daisuke Ichihara, Akira Iwakawa, Akihiro Sasoh, Shota Harada, Takuya Yamazaki, Matsutaka Sasahara, Tomiji Iwasaki

    34th International Electric Propulsion Conference  

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    Event date: 2015.7

    Language:English   Presentation type:Oral presentation (general)  

    Venue:Hyogo-Kobe,   Country:Japan  

  7. Operation Characteristics of Small-DC-Current, Applied-Field MPD Thruster International conference

    Daisuke Ichihara, Tomoki Uno, Hisashi Kataoka, Akira Iwakawa, Akihiro Sasoh

    34th International Electric Propulsion Conference 

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    Event date: 2015.7

    Language:English   Presentation type:Oral presentation (general)  

    Venue:Hyogo-Kobe   Country:Japan  

  8. Operation Characteristics of Diverging Magnetic Field Electrostatic Thruster

    Daisuke Ichihara, Akira Iwakawa, Akihiro Sasoh

    The 35th International Electric Propulsion Conference  2017.10.8 

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    Language:English   Presentation type:Oral presentation (general)  

    Venue:Georgia Institute of Technology  

  9. Effects of magnetic field configuration on thrust performance of a diverging magnetic field electrostatic thruster (DM-EST) International conference

    2018.1.18 

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    Language:Japanese   Presentation type:Oral presentation (general)  

  10. RF vs. Acceleration Power Distribution in Helicon Electrostatic Thruster

    Daisuke Ichihara, Yoshiya Nakagawa, Akira Iwakawa, Akihiro Sasoh, Takuya Yamazaki

    The 35th International Electric Propulsion Conference  2017.10.8 

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    Language:English   Presentation type:Oral presentation (general)  

    Venue:Georgia Institute of Technology  

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Research Project for Joint Research, Competitive Funding, etc. 8

  1. Middle-Atmosphere Pollution Assessment and Scientific-Governance Recommendation for Sustainable Space Development

    2022.4 - 2028.3

    Japan Science and Technology Agency  Strategic Professional Development Program for Young Researchers 

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    Authorship:Principal investigator  Grant type:Competitive

  2. 偽関節治療を進化させる小侵襲体内衝撃波療法の開発

    Grant number:A154  2022.4 - 2023.3

    「橋渡し研究プログラム」研究費支援シーズA 

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    Authorship:Coinvestigator(s)  Grant type:Competitive

  3. 100W 級電気推進機における電子ビームを活用した推進剤電離手法の確立

    2020.5 - 2021.11

    令和2年度研究助成 

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    Authorship:Principal investigator  Grant type:Competitive

    Grant amount:\1000000 ( Direct Cost: \1000000 )

  4. 電気推進機による小型宇宙機の動力航行に向けた電子Hall効果に基づく推力ベクトル偏向手法の確立

    2020.4 - 2021.3

    木下記念事業団 学術研究助成事業 

    市原大輔

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    Grant type:Competitive

    近年,小型宇宙機を用い た 惑星間軌道や高高度地球周回軌道の探査商業利用が注目されている.小型宇宙機に電気推進機 電気エネルギーを運動エネルギーに変換し推力を得る推進機 を搭載する場合,推力ベクトルを宇宙機 の 重心方向に一致させることは難しく,不要なトルクが発生する.そのため,宇宙機重量や運用環境に依らない 新たな 推力ベクトル偏向手法が求められる.そこで本研究では,電気推進機内で生成するプラズマの素過程に注目し,対向する矩形放電室を用いて電子Hall効果を活用した推力ベクトル偏向手法を提案する.対向する放電室を同時に使用することで正味のトルク方向推力を相殺する.さらに本提案手法を発展させ,各放電
    室にて発生するトルク方向推力を能動制御し宇宙機に任意のトルクを作用させることもできる.本提案手法は 従来の機械式回転台が不要かつ宇宙機の運用環境に依存しない点で,小型宇宙機において特に有用な推力ベクトルの偏向手法であり,その実証を目標とする本研究テーマの意義は大きい.

  5. エアロバリスティックレンジを用いた火星着陸用超音速パラシュートの自由飛行特性評価

    2019.12 - 2020.12

    日東学術振興財団研究助成 

    市原大輔

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    Grant type:Competitive

    火星着陸用超音速パラシュートに関して,火星大気の主成分である二酸化炭素雰囲気中での超音速自由飛行特性の取
    得を目的とする.エアロバリスティックレンジを用いてパラシュート模型を超音速まで加速し,測定部内に充填した二酸
    化炭素雰囲気中を自由飛行させる.パラシュートの開傘から減速にかけての一連の挙動を高速度カメラで撮影し,各画像
    間の相互相関係数から開傘時間,傘の安定性,模型減速度の3点に注目した解析を実施する.

  6. 宇宙太陽光発電の実用化に向けた環状発散磁場型アルゴンプラズマ推進機の開発

    2019.10 - 2020.9

    第27回公益財団法人立松財団一般研究助成 

    市原大輔

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    Grant type:Competitive

  7. 陽極近傍電離を用いた電気推進機プラズマにおける電子-重粒子衝突の促進

    2019.4 - 2020.3

    公益財団法人市原国際奨学財団研究助成金 

    市原大輔

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    Grant type:Competitive

  8. 第36回International Electric Propulsion Conferenceへの参加

    2019.4 - 2020.3

    国際交流援助(海外渡航費援助) 

    市原大輔

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    Grant type:Competitive

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KAKENHI (Grants-in-Aid for Scientific Research) 12

  1. 印刷型ブラスト波源で実現する針なし注射

    2021.4 - 2024.3

    国立研究開発法人科学技術振興機構(JST)  創発的研究支援事業 

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    Authorship:Principal investigator  Grant type:Competitive

    Grant amount:\20000000

  2. 光ヘテロダイン干渉法の活用による変調衝撃波の内部構造と状態量遷移過程との関係解明

    2022.4 - 2025.3

    日本学術振興会  科学研究費補助金 基盤C 

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    Authorship:Principal investigator  Grant type:Competitive

  3. Shock Wave Moderation by Fore-Flow Nudge: Proof of Principle and Applications

    Grant number:21H04589  2021.4 - 2025.3

    Grants-in-Aid for Scientific Research  Grant-in-Aid for Scientific Research (A)

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    Authorship:Coinvestigator(s) 

  4. 多価イオンの静電・電磁複合加速による電気推進機の大推力化

    2020.4 - 2022.3

    日本学術振興会  科学研究費助成事業  若手研究

    市原大輔

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    Grant type:Competitive

    電気推進機を利用した宇宙機の運用において,軌道遷移に長時間を要することが課題である.そこで本研究ではこれまで不要とされていた「多価イオン」に注目する.申請者が独自に見出した静電・電磁複合加速方式を採用し,従来の静電加速に加えて,多価イオン生成に伴う自由電子を利用した電磁加速推力の増強とこれによる電気推進機の大推力化を目的とする.そのため,①多価イオン生成に必要な推進機の作動条件を特定すること,②電場による無衝突静電加速と電子-イオン間の衝突散乱を介した電磁加速とに対して,発散角損失を最小化する最適静電・電磁加速比を見出し電気推進機の大推力を実証することの2つを到達目標とする.

  5. 多価イオンの静電・電磁複合加速による電気推進機の大推力化

    Grant number:20K14950  2020.4 - 2022.3

    科学研究費助成事業  若手研究

    市原 大輔

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    Authorship:Principal investigator 

    Grant amount:\4160000 ( Direct Cost: \3200000 、 Indirect Cost:\960000 )

    電気推進機を利用した宇宙機の運用において,軌道遷移に長時間を要することが課題である.そこで本研究ではこれまで不要とされていた「多価イオン」に注目する.申請者が独自に見出した静電・電磁複合加速方式を採用し,従来の静電加速に加えて,多価イオン生成に伴う自由電子を利用した電磁加速推力の増強とこれによる電気推進機の大推力化を目的とする.そのため,①多価イオン生成に必要な推進機の作動条件を特定すること,②電場による無衝突静電加速と電子-イオン間の衝突散乱を介した電磁加速とに対して,発散角損失を最小化する最適静電・電磁加速比を見出し電気推進機の大推力を実証することの2つを到達目標とする.
    発散磁場中でのイオン加速に関して推進剤流束を向上させた際の推力密度を評価した.中心軸上の陰極と同軸上に配した陽極との間に発散磁場を印加し,陽極近傍のみからキセノン推進剤を供給した.測定された推力は静電加速および電磁加速特性を共に満足する静電・電磁複合加速特性を示した.また得られた推力密度は最新の静電加速型電気推進機に対して最大6.3倍に達しており,電磁加速型電気推進機に対しては2.5倍の向上を確認できた.本手法により従来の静電加速型・電磁加速型では達しえない高い推力密度を達成できたことは電気推進機の大推力化に対して大きく貢献できる成果である.
    COVID-19のアウトブレイクによる研究中断期間が長く,当初の予定よりも遅れている.さらに実験装置の移動・改修とその後の復旧作業に時間を要したことも要因である.
    感染状況にもよるが,基本的には当初想定した研究項目を進めていく.当初より6か月間の調整期間を設けていたため研究期間内には一定の成果を見込む.

  6. 電気推進機による小型宇宙機の動力航行に向けた電子Hall効果に基づく推力ベクトル偏向手法の確立

    2020.4 - 2021.3

    公益財団法人木下記念事業団  木下記念事業団 学術研究助成事業 

    市原大輔

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    Grant type:Competitive

    近年,小型宇宙機を用い た 惑星間軌道や高高度地球周回軌道の探査商業利用が注目されている.小型宇宙機に電気推進機 電気エネルギーを運動エネルギーに変換し推力を得る推進機 を搭載する場合,推力ベクトルを宇宙機 の 重心方向に一致させることは難しく,不要なトルクが発生する.そのため,宇宙機重量や運用環境に依らない 新たな 推力ベクトル偏向手法が求められる.そこで本研究では,電気推進機内で生成するプラズマの素過程に注目し,対向する矩形放電室を用いて電子Hall効果を活用した推力ベクトル偏向手法を提案する.対向する放電室を同時に使用することで正味のトルク方向推力を相殺する.さらに本提案手法を発展させ,各放電
    室にて発生するトルク方向推力を能動制御し宇宙機に任意のトルクを作用させることもできる.本提案手法は 従来の機械式回転台が不要かつ宇宙機の運用環境に依存しない点で,小型宇宙機において特に有用な推力ベクトルの偏向手法であり,その実証を目標とする本研究テーマの意義は大きい.

  7. エアロバリスティックレンジを用いた火星着陸用超音速パラシュートの自由飛行特性評価

    2019.12 - 2020.12

    日東学術振興財団  日東学術振興財団研究助成 

    市原大輔

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    Authorship:Principal investigator  Grant type:Competitive

    火星着陸用超音速パラシュートに関して,火星大気の主成分である二酸化炭素雰囲気中での超音速自由飛行特性の取
    得を目的とする.エアロバリスティックレンジを用いてパラシュート模型を超音速まで加速し,測定部内に充填した二酸
    化炭素雰囲気中を自由飛行させる.パラシュートの開傘から減速にかけての一連の挙動を高速度カメラで撮影し,各画像
    間の相互相関係数から開傘時間,傘の安定性,模型減速度の3点に注目した解析を実施する.

  8. 宇宙太陽光発電の実用化に向けた環状発散磁場型アルゴンプラズマ推進機の開発

    2019.10 - 2020.9

    公益財団法人立松財団  第27回公益財団法人立松財団一般研究助成 

    市原大輔

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    Authorship:Principal investigator  Grant type:Competitive

  9. 第36回International Electric Propulsion Conferenceへの参加

    2019.4 - 2020.3

    中部電気利用基礎研究振興財団  国際交流援助(海外渡航費援助) 

    市原大輔

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    Grant type:Competitive

  10. 陽極近傍電離を用いた電気推進機プラズマにおける電子-重粒子衝突の促進

    2019.4 - 2020.3

    公益財団法人市原国際奨学財団  公益財団法人市原国際奨学財団研究助成金 

    市原大輔

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    Authorship:Principal investigator  Grant type:Competitive

  11. Large-thrust operation of electric propulsion by using electrostatic/magnetic hybrid ion acceleration

    Grant number:18K13925  2018.4 - 2020.3

    Grant-in-Aid for Early-Career Scientists

    Ichihara Daisuke

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    Authorship:Principal investigator 

    Grant amount:\4160000 ( Direct Cost: \3200000 、 Indirect Cost:\960000 )

    Electric propulsion have a capability of high-exhaust velocity operation than that of the chemical propulsion operation. However, due to the small thrust, it takes much longer time to orbit rising. In this research, the electrostatic/magnetic hybrid ion acceleration method under the diverging magnetic field was investigated to achieve a large-thrust operation of electric propulsion. Through this research, we have hound that even with external cathode operation, the hybrid ion acceleration method was effective by keeping high electron Hall parameter. By increasing magnetic field strength, multiple ionization process was enhanced. As as result, the specific impulse exceeded 3800 s and more than 30% of thrust efficiency was achieved with argon propellant.

  12. 電子圧力勾配による静電加速電気推進機の推力性能向上

    2016.4 - 2017.9

    日本学術振興会  科学研究費助成事業  特別研究員奨励費

    市原大輔

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    Authorship:Principal investigator  Grant type:Competitive

    Grant amount:\1300000 ( Direct Cost: \1300000 )

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Industrial property rights 1

  1. 送風機およびそれを 送風機およびそれを 送風機およびそれを 送風機およびそれを 用いた空調装置 用いた空調装置 用いた空調装置

    伊藤功治,小田修三,酒井雅晴,前田登,佐宗章弘,岩川輝,市原大輔

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    Applicant:株式会社デンソー,株式会社日本自動車部品総合研究所,国立大学法人名古屋大学

    Application no:特願2014-244196  Date applied:2014.12

    Announcement no:特開2016-107175  Date announced:2016.6

    Country of applicant:Domestic  

 

Teaching Experience (On-campus) 3

  1. 数学I及び演習

    2019

  2. 航空宇宙創造設計

    2019

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    集中講義方式で実施する.はじめに航空機,ロケット,人工衛星の概論的な解説を行い,その内容を参考に設計するテーマを決めて設計を行う.設計結果は設計報告書にまとめるとともに,発表会で発表する.

  3. 機械・航空工学科実験第1

    2019

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    講義で習得した原理や法則を体験的に理解し、実験装置や各種測定機器の作動原理、操作法など実験の方法を修得する。また、実験結果の整理、分析を通して科学技術報告書の作成法を学ぶ。