Faculty Profiles - ICHIHARA Daisuke

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

Contact information

Homepage

http://akagi.nuae.nagoya-u.ac.jp/en/

Degree 1

Doctor(Engineering) （ 2017.9 Nagoya University ）

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Research Interests 3

Low temperature plasma
Electric space-propulsion
Compressible fluid dynamics

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Research Areas 3

Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering) / Aerospace engineering / Aerospace Engineering
Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Fluid engineering / 医療機器開発
Energy Engineering / Fundamental plasma / 低温プラズマ

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Current Research Project and SDGs 3

Research and Development of Electric Propulsion
大気汚染評価
医療機器開発

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Research History 5

名古屋大学高等研究院(兼務)

2021.4
Nagoya University Institute for Space-Earth Environmental Research Center for Orbital and Suborbital Research Researcher

2018.10 - 2019.3
Graduate School of Engineering, Nagoya University Department of Aerospace Engineering Assistant Professor

2017.10

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Country：Japan
Japan Society for the Promotion of Science Research Fellowships for Young Scientists DC2

2016.4 - 2017.9
NEC Corporation staff

2013.4 - 2014.3

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Country：Japan

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Education 2

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

2014.10 - 2017.9

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Country： Japan
Nagoya University Faculty of Engineering Mechanical and Aerospace Engineering

2007.4 - 2011.3

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Country： Japan

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Professional Memberships 2

プラズマ・核融合学会プラズマ応用部門編集委員

2022.7
The Japan Society for Aeronautical and Space Science

2011.4

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Committee Memberships 2

The Japan Society of Plasma Science and Nuclear Fusion Research. editorial board member(Applied Plasma Physics)

2022.7 - 2024.6

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Committee type：Academic society
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

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Papers 19

Development and numerical investigation of Mach probe model in a hypersonic, low-temperature flowing plasma Reviewed

D. Ichihara, H. Sumi

Physics of Plasmas Vol. 30 ( 9 ) 2023.9

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Authorship：Lead author,　Corresponding author Publishing type：Research paper (scientific journal) Publisher：AIP Publishing

This study conducted a numerical simulation around a Mach probe under hypersonic low-temperature plasma. The Mach probe has three ion collection planes: front, side, and back. Under a hypersonic flowing plasma, the front and side planes are practical ion collection areas, and the backplane collects no ion flux. The collected ion current density on the front plane is almost identical to that of the mainstream ion flux. By contrast, the ion current collected on the side plane is affected by the concentration of the electric field at the probe edge. As this edge effect has a different influence on the front and side planes, the ion current density ratio of the side to the front planes is dominated by a non-dimensional parameter—the ratio of electrostatic to kinetic flow energy. Based on this non-dimensional parameter, the calculated ion current density ratio can be fitted using a simple mathematical formula. Therefore, the proposed Mach probe model with non-dimensional parameters extends the conventional Mach probe model validated in sub-to-supersonic high-temperature plasma to hypersonic low-temperature flowing plasma, which is commonly observed in electric propulsions.

DOI： 10.1063/5.0160945
Energetic ion and plasma oscillation measurements during plume mode operation of a hollow cathode Reviewed

Atsuya Suzuki, Kiyoshi Kinefuchi, Daisuke Ichihara, Shinatora Cho, Hiroki Watanabe, Kenichi Kubota

Physics of Plasmas Vol. 30 ( 7 ) 2023.7

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Publishing type：Research paper (scientific journal) Publisher：AIP Publishing

Hollow cathodes are important devices used for spacecraft electric propulsion. The hollow cathode has two operational modes. One mode is a stable mode called the spot mode, and the other is an unstable mode called the plume mode. Operation in plume mode should be avoided since the instability causes high-energy ions that sputter-erode the cathode parts. In this study, the relationship between discharge oscillations and ion energy distribution in plume mode was investigated using a triple Langmuir probe and retarding potential analyzer for a 40-A class xenon hollow cathode with a lanthanum hexaboride emitter. The triple probe can measure unsteady electron temperature and plasma density oscillations. The electron temperature was not so high, 1 to 2 eV. Some instabilities were observed in the plume mode. The ionization instability with a low frequency oscillation of 30 kHz was the dominant mode. A broad spectrum around 330 kHz due to ion acoustic turbulence was observed. In addition, in the downstream plume region, oscillations around 120 kHz were observed owing to temporal change in anomalous resistivity. The 95% ion population voltage found to be 20 and 30 eV in spot and plume modes, respectively. The magnitude of the low frequency ionization oscillation was found to be inversely proportional to ion energy in plume mode. This indicates that the resonant energy transfer from the oscillation to the ion energy through Landau damping probably plays an important role in high energy ion generation in plume mode. A clear correlation between discharge current and electron temperature waveforms was found. The larger the electron temperature fluctuation, the stronger the correlation between discharge current and electron temperature, and the larger the phase difference deviation from 180°.

DOI： 10.1063/5.0139089

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Scopus
Investigation on Applying an InGaN Photocathode with Negative Electron Affinity for Electric Propulsion Reviewed

Yusuke INOUE, Tomohiro NISHITANI, Anna HONDA, Daiki SATO, Haruka SHIKANO, Atsushi KOIZUMI, Yoshio HONDA, Daisuke ICHIHARA, Akihiro SASOH

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Vol. 66 ( 1 ) page： 10 - 13 2023

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Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：Japan Society for Aeronautical and Space Sciences

DOI： 10.2322/tjsass.66.10

Web of Science

Scopus

CiNii Research
Geometrical matching in remote in-tube shock compression by an unsteady jet Reviewed

D. Ichihara, D. Kuwabara, D. Moriyama, Y. Nakamura, A. Iwakawa, A. Sasoh

Shock Waves Vol. 32 ( 4 ) page： 373 - 381 2022.6

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Authorship：Lead author,　Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：Springer Science and Business Media LLC

DOI： 10.1007/s00193-022-01079-1

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Scopus

Other Link： https://link.springer.com/article/10.1007/s00193-022-01079-1/fulltext.html
Numerical and experimental study on the behavior of vortex rings generated by shock–bubble interaction Reviewed

K. Kitamura, Z. Yue, T. Fujimoto, H. Asai, A. Kubota, M. Myokan, D. Ichihara, A. Sasoh

Physics of Fluids Vol. 34 ( 4 ) page： 046105 - 046105 2022.4

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

In this study, three-dimensional numerical simulations and experiments of the interaction between a normal shock and bubbles generated by the repetitive energy depositions of a laser pulse in a Mach 1.92 flow was conducted. As a result of the shock–bubble interaction, a vortex ring, caused by a baroclinic effect, was generated. Owing to the self-induced velocity field, the advection velocity of the vortex rings decreased with increasing laser pulse energy. In the experiments, when interactions among the vortex rings became strong, separations in transverse directions between adjacent bubbles were induced. This was reproduced through numerical simulations by imposing an artificial disturbance in the initial positions of the bubbles, i.e., by 5% of the bubble diameter in a transversal direction. The asymmetric behaviors of a row of vortex rings were classified into three patterns based on the ratio of the distance between the vortex rings to the size of the vortex rings ( λ: inverse Strouhal number). In pattern 1, with λ >2.9, there was negligible interference between the vortex rings because the interval of the vortex rings was sufficiently large. In pattern 2, with λ = 0.97–1.2, separation in the vortex-ring rows appeared, and the separation angle increased as λ decreased. In pattern 3, with λ <0.62, the interference intensified, and the vortex rings collapsed, forming a turbulent flow behind the shock wave.

DOI： 10.1063/5.0083596

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Scopus
Electrostatic-magnetic hybrid ion acceleration for high-thrust-density operation Reviewed

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

Journal of Applied Physics Vol. 130 ( 22 ) 2021.12

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

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

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Scopus
Energy conversion efficiency of electrical exploding foil accelerators Reviewed

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

AIP Advances Vol. 11 ( 9 ) 2021.9

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

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

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Scopus
Thrust Density Enhancement in an Electrostatic–Magnetic Hybrid Thruster Reviewed

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

Journal of Propulsion and Power Vol. 37 ( 6 ) page： 973 - 976 2021

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Authorship：Lead author,　Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：American Institute of Aeronautics and Astronautics (AIAA)

DOI： 10.2514/1.B38480

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Scopus
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
High-Specific-Impulse Electrostatic Thruster with Argon Propellant Reviewed

Ichihara Daisuke, Matsuba Toshihiro, Iwakawa Akira, Sasoh Akihiro

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

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

DOI： 10.2514/1.B37675

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Scopus
Boundary Effect on the Laser-ablation Impulse Characteristics of a Flat-Head Cylinder Reviewed

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

DOI： 10.2322/tjsass.63.109

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Scopus

CiNii Research
Similar Thrust Performance in Diverging-Magnetic-Field Electrostatic Thruster with Monoatomic Propellants Reviewed

Ichihara Daisuke, Sasoh Akihiro

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

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

DOI： 10.2514/1.B37294

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Scopus
Electrostatic-magnetic-hybrid thrust generation in central-cathode electrostatic thruster (CC-EST) Reviewed

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

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Scopus
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
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
Ten-Ampere-Level, Applied-Field-Dominant Operation in Magnetoplasmadynamic Thrusters Reviewed

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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Authorship：Lead author,　Corresponding author Language：English 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

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Scopus
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
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
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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MISC 1

高温超伝導マグネットによる強磁場印加プラズマ推進—Strong Applied Field Plasma Thruster Using High-temperature Superconducting Magnet

杵淵, 紀世志, 市原, 大輔, 中野, 僚太, 前島, 大輝, 高木, 涼平, ACHESON, Chris, OLATUNJI, Jamal, GODDARD-WINCHESTER, Max, POLLOCK, Randy, KINEFUCHI, Kiyoshi, ICHIHARA, Daisuke, NAKANO, Ryota, MAESHIMA, Daiki, TAKAGI, Ryohei

令和4年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2022 2023.1

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Language：Japanese Publisher：宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

令和4年度宇宙輸送シンポジウム（2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)) , 相模原市, 神奈川県
Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
High performance plasma thruster is required for the further space development and exploration. One of the possible candidates is applying strong magnetic field to improve the thrust efficiency and thrust density. In this study, a new plasma thruster with high-temperature superconducting magnet capable of generating high magnetic field was developed. The superconducting magnet was cooled by a cryocooler, and the thruster operation with an applied field of 0.8 T have been successfully carried out.
資料番号: SA6000184074
STEP-2022-022

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Presentations 12

ブラスト波で駆動する高速粒子射出器の作動特性

市原大輔

2022 年度衝撃波シンポジウム 2023.3.10 日本衝撃波研究会

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Event date： 2023.3

Language：Japanese Presentation type：Oral presentation (general)

Venue：産業技術総合研究所つくば中央 Country：Japan
超音速プラズマ流れにおけるMachプローブモデル式の提案

市原大輔

2022 年度宇宙輸送シンポジウム非化学推進部門 2023.1.13 宇宙科学研究所

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Event date： 2023.1

Language：Japanese Presentation type：Oral presentation (general)

Venue：宇宙科学研究所 Country：Japan
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
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
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
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
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
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
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
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
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)
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

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
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
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 ）
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．
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．
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
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
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) 14

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
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
超音速・低レイノルズ数流れにおける空気抵抗モデルの確立

2022.10 - 2023.9

公益財団法人立松財団研究助成

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Authorship：Principal investigator Grant type：Competitive
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

Grant number：22K04533 2022.4 - 2025.3

科学研究費助成事業基盤研究(C)

市原大輔

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Authorship：Principal investigator

Grant amount：\4030000 （ Direct Cost: \3100000 、 Indirect Cost：\930000 ）

近年，超音速旅客機の実現に向けた動きが国内外にて活発化する中で，衝撃波の発生に起因する空力性能の低下を改善すべく，衝撃波面の変調とそれに伴う状態量(密度・圧力・エントロピーなど)変化に関する深い理解が求められている．そこで本研究では衝撃波内部における粒子間衝突を介したエネルギー散逸課程に注目する．初めに光ヘテロダイン干渉法を活用した衝撃波内部の密度場測定手法を確立する．続いて時間変動する流れ場と衝撃波との干渉現象に関し，波面の変調を伴う衝撃波の内部構造，衝突パラメータ(衝突周波数・平均自由行程)及び背後状態量の関係を明らかとする．
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)
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

公益財団法人日比科学技術振興財団令和2年度研究助成

市原大輔

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Authorship：Principal investigator Grant type：Competitive

Grant amount：\1000000 （ Direct Cost: \1000000 ）
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．
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．
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．
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
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
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
Large-thrust operation of electric propulsion by using electrostatic/magnetic hybrid ion acceleration

Grant number：18K13925 2018.4 - 2020.3

Grants-in-Aid for Scientific Research Grant-in-Aid for Early-Career Scientists

Ichihara Daisuke

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Authorship：Principal investigator Grant type：Competitive

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.
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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To the head of KAKENHI (Grants-in-Aid for Scientific Research).▲

Industrial property rights 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

To the head of Industrial property rights.▲

Teaching Experience (On-campus) 3

数学I及び演習

2019
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．
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。

To the head of Teaching Experience (On-campus).▲

Teaching Experience (Off-campus) 2

航空宇宙機創造設計

2018.4 （Nagoya University）
数学I及び演習

2017.10 （Nagoya University）

To the head of Teaching Experience (Off-campus).▲

Social Contribution 2

Researcher+ シンポジウム2022

Role(s)：Panelist,　Informant

MEXT「世界で活躍できる研究者育成プログラム総合支援事業」 Researcher+ シンポジウム2022 2022.12
音速を超えた世界の主役-衝撃波の科学-

Role(s)：Lecturer

松坂屋名古屋店名大カフェ Sciencea, and Me 2022.10

To the head of Social Contribution.▲