Updated on 2024/03/14

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 3

  1. Electric space-propulsion

  2. Low temperature plasma

  3. Compressible fluid dynamics

Research Areas 4

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

  2. Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Fluid engineering  / 医療機器開発

  3. Energy Engineering / Fundamental plasma  / 低温プラズマ

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

Current Research Project and SDGs 3

  1. Research and Development of Electric Propulsion

  2. 大気汚染評価

  3. 医療機器開発

Research History 6

  1. 名古屋大学高等研究院(兼務)

    2021.4

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

    2018.10 - 2019.3

  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   Research associate

    2017.10

  5. Japan Society for the Promotion of Science   Research Fellowships for Young Scientists   DC2

    2016.4 - 2017.9

  6. NEC Corporation   staff

    2013.4 - 2014.3

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    Country:Japan

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Education 2

  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   Faculty of Engineering   Mechanical and Aerospace Engineering

    2007.4 - 2011.3

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    Country: Japan

Professional Memberships 2

  1. プラズマ・核融合学会   プラズマ応用部門編集委員

    2022.7

  2. The Japan Society for Aeronautical and Space Science

    2011.4

Committee Memberships 3

  1. 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

  2. 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

  3. 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

Awards 1

  1. 第18回わかしゃち奨励賞 応用研究部門 優秀賞

    2023.12   愛知県経済産業局、公益財団法人科学技術交流財団、公益財団法人日比科学技術振興財団、   局所アーク加熱で駆動する高速・ピンポイント粒子射出器

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    Award type:Award from publisher, newspaper, foundation, etc.  Country:Japan

 

Papers 22

  1. Operational demonstration and experimental characterisation of a central cathode electrostatic thruster equipped with a high temperature superconducting magnet Reviewed

    Chris R. Acheson, Jakub Glowacki, Ryota Nakano, Daiki Maeshima, Dominik Saile, Betina Pavri, Ryohei Takagi, Ryoyu Mori, Randy Pollock, Jamal R. Olatunji, Max Goddard-Winchester, Nicholas M. Strickland, Daisuke Ichihara, Stuart C. Wimbush, Kiyoshi Kinefuchi

    Journal of Electric Propulsion   Vol. 2 ( 1 )   2023.12

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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:Springer Science and Business Media LLC  

    Abstract

    Interplanetary transport of payloads of unprecedented mass, as envisaged beyond the lunar gateway, will require thrusters with high specific impulse as well as high thrust. To achieve this, innovations in propulsion are critical. Many classes of electric thruster utilise a magnetic applied field module to accelerate charged particles. Magnetoplasmadynamic thrusters exhibit improved performance with increasing field, at least up to the limit of around 0.5 T able to be provided by permanent magnets or copper electromagnets. However, superconducting magnets can generate much stronger magnetic fields. In this study, we utilised a space-relevant cryocooled high temperature superconducting magnet as the applied field module for a central cathode electrostatic thruster (CC-EST). A convex anode enabled ignition at high magnetic fields, and in this configuration the thruster’s performance was characterised in the power range of 1 kW to 2.5 kW and at steady applied fields ranging from 0.6 T to 0.8 T, representing a significant advance in achievable field strength. In combination, these operating parameters enabled the achievement of a magnet-inclusive thruster efficiency of 19%, while the cryocooled magnet was demonstrated to be thermally stable in the presence of the kW-scale plasma, demonstrating the viability of such a design for space flight applications.

    File: Operational demonstration and experimental characterisation of a central cathode electrostatic thruster equipped with a high temperature superconducting magnet.pdf

    DOI: 10.1007/s44205-023-00060-z

    Other Link: https://link.springer.com/article/10.1007/s44205-023-00060-z/fulltext.html

  2. Electrical microparticle acceleration by high-speed membrane deformation Reviewed

    D. Ichihara, R. Takata

    AIP Advances   Vol. 13 ( 12 )   2023.12

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

    In this study, we conducted experiments to explore the potential of a low-power exploding foil initiator for accelerating microparticles through high-speed membrane deformation. This involved the use of a conductive layer with a conversion section known as a “bridge,” which was positioned between the substrate and the cover layer. The application of pulsed electrical energy led to Joule heating at the bridge, while the vaporized gas generated impulsive loading, resulting in the deformation of the cover layer. According to the principles of energy conservation, 8.7% of the electrical input energy was converted into kinetic energy for the membrane. This deformation process achieved a velocity of 800 m/s, with a corresponding strain rate of 1.6 × 107 s−1. The applied impulse predominantly induced extension stresses in the cover layer rather than bending stresses. Under these conditions, a 17.5-µm radius polylactic acid bead was propelled and subsequently captured by a silicone gel layer, resembling human dermic skin. Considering factors such as particle clustering and deceleration due to air resistance during supersonic flight, assuming a normal incident angle, it was estimated that approximately half of the ejected particles could reach the human dermic layer, located 200 µm beneath the skin surface. These findings suggest that pulse discharge is a promising method for inducing high-speed membrane deformation, and the electrical microparticle accelerator holds potential for applications in needle-free drug delivery.

    File: Electrical microparticle acceleration by high-speed membrane deformation.pdf

    DOI: 10.1063/5.0179237

    Web of Science

    Scopus

  3. 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

    Web of Science

    Scopus

  4. 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

    Web of Science

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  5. 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

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    Scopus

    CiNii Research

  6. 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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    Other Link: https://link.springer.com/article/10.1007/s00193-022-01079-1/fulltext.html

  7. 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

    Web of Science

    Scopus

  8. 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

    Web of Science

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  9. 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   2021.11

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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

    Web of Science

    Scopus

  10. 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.

    File: Energy conversion efficiency of electrical exploding foil accelerators.pdf

    DOI: 10.1063/5.0061699

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

    Jamal R. Olatunji, Nicholas M. Strickland, Max R. Goddard Winchester, Kiyoshi Kinefuchi, Daisuke Ichihara, Nicholas J. Long, Stuart C. Wimbush

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

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    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

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  12. 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   2020.3

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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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  13. 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

  14. 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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    CiNii Research

  15. 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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  16. 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)   Publisher:Elsevier {BV}  

    DOI: 10.1016/j.actaastro.2018.07.052

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  17. 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

  18. 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

  19. 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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  20. 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

  21. 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

  22. 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 2

  1. 衝撃波で薬剤を注入ー針を使わぬ「貼る注射器」 Invited

    市原大輔

    化学   Vol. 79 ( 2 ) page: 72 - 73   2024.2

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    Authorship:Lead author, Corresponding author   Language:Japanese   Publishing type:Article, review, commentary, editorial, etc. (trade magazine, newspaper, online media)  

  2. 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

Presentations 12

  1. 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  

  2. 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  

  3. 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  

  4. 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  

  5. 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  

  6. 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  

  7. 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  

  8. 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  

  9. 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  

  10. 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  

  11. 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)  

  12. 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  

▼display all

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 

      More details

    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 

      More details

    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 

      More details

    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

      More details

    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

      More details

    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

      More details

    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

      More details

    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

      More details

    Grant type:Competitive

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KAKENHI (Grants-in-Aid for Scientific Research) 15

  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 

      More details

    Authorship:Principal investigator  Grant type:Competitive

  2. 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

  3. 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 

    市原大輔

      More details

    Authorship:Principal investigator  Grant type:Competitive

    Grant amount:\20000000

  4. 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

  5. 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.
    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.
    今年度は申請者の提案する光ヘテロダイン干渉法を応用した密度場の非定常測定手法に関して、衝撃波管内に発生する平面衝撃波背後の密度場測定に取り組み本提案原理の実証実験を展開した。衝撃波管内にファイバーレーザー光を導入し平面衝撃波がレーザー光を通過する際の屈折率変化量を光Doppler式速度計で測定する。実験に先立ちレーザービーム径の空間変化をビームプロファイラで取得した。コリメートレンズを通過したレーザービームは約600nmのビーム径(1/e2)を200mmにわたって維持していることが分かった。衝撃波管は62mmx62mmの矩形流路を有していることを考えると測定領域全体にわたって一様なビーム径が期待できる。次に、実際に平面衝撃波を発生させ衝撃波通過に伴う屈折率変化量を取得した。測定には広帯域オシロスコープを用い時間分解能0.65マイクロ秒を達成している。光Doppler式速度計による見かけの速度は最大で5.0m/sであった。見かけの速度は屈折率の時間変化率に比例しおおよそ80.6s-1に対応する。さらに、Gladstone-Daleの式に基づくと密度の時間変化率350g/cm3/sが得られる。衝撃波の伝搬速度と前述のレーザービーム径とから600nmのレーザービームを横切るのに要する時間を算出し上記密度の時間変化率を積分した結果、表撃破の通過による密度増加量は約0.17kg/m3と算出される。これは衝撃波管の関係式から見積もられる密度変化量とよく一致しており本提案手法の妥当性が示された。
    先述の通り今年度は本提案手法の妥当性を平面衝撃波を用いて検証することができた。特に、密度場の算出に重要な測定ビーム径に関してビームプロファイラによる実測が重要であった。その結果、既定のWork Distance内では一様なビーム径を維持しているのに対し、これ以遠ではビーム径が線形に増加することも明らかとなっている。本結果は測定光路長の上限値を決める重要な知見である。ビーム径にはFWHMや1/e2など複数の定義がありうる。本測定において各定義に応じたビーム径分布も同時に取得しており密度場を算出するにあたり最も有用なビーム径の定義についても議論できるようになった。以上の理由から本研究は現時点で「おおむね順調に進展している」と言える。
    次年度以降も研究計画書に記載の実験計画に沿って進める。具体的には円柱後流の時間変動成分測定を進める。擾乱源である円柱後流の変動特性を取得すべく,流速および圧力の時間履歴を測定する.衝撃波管内に設置した円柱に対して平面衝撃波を入射すると衝撃波背後に誘起された流れ場が円柱を通過する際に円柱後流が発生する.圧力測定には前述の壁面圧力計を用いる.流速測定には時間応答性に優れた熱線流速計(熱した金属線の温度変化から流速を算出する装置)を用いる.取得した流速及び圧力の時間履歴に関して各時間平均値に対する標準偏差の割合を変動特性と定義し,入射衝撃波の強度と変動特性との関係を取得する.

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

    Grant number:21H04589  2021.4 - 2025.3

    Japan Society for the Promotion of Science  Grants-in-Aid for Scientific Research  Grant-in-Aid for Scientific Research (A)

      More details

    Authorship:Coinvestigator(s) 

  7. 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 )

  8. 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.

  9. 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

      More details

    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.

  10. 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

      More details

    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.

  11. 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

      More details

    Authorship:Principal investigator  Grant type:Competitive

  12. 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

  13. 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

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

    Grant number:18K13925  2018.4 - 2020.3

    Japan Society for the Promotion of Science  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.

  15. 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。

Teaching Experience (Off-campus) 2

  1. 航空宇宙機創造設計

    2018.4 Nagoya University)

  2. 数学I及び演習

    2017.10 Nagoya University)

 

Social Contribution 2

  1. Researcher+シンポジウム2022

    Role(s):Panelist, Informant

    文部科学省人材育成補助事業「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

  2. 音速を超えた世界の主役 「衝撃波」の科学

    Role(s):Lecturer

    Common-S. サカエ大学(運営:松坂屋名古屋店)  名大カフェ'Science, and Me'  2022.10

Media Coverage 4

  1. 衝撃波で注入する針なし注射器 Newspaper, magazine

    日経サイエンス社  日経サイエンス  SCOPE  2024.3

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    Author:Other 

  2. ローカルビジネスサテライト TV or radio program

    テレビ愛知  5時スタ  2024.2

  3. 名大、針なしの注射器開発 衝撃波を駆使、体内に薬剤注入 Newspaper, magazine

    日経新聞社  日経産業新聞  2023.12

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    Author:Other 

  4. 将来的には予防接種にも?針なしの「貼る注射器」を名古屋大学が開発…どうやって薬剤を注入するのか研究者に聞いた Internet

    フジテレビジョン  FNNプライムオンライン  ライフ > 医療・健康  2023.12

Academic Activities 1

  1. 名大発「アカデミックフラッシュ」

    Role(s):Planning, management, etc., Panel moderator, session chair, etc.

    名古屋大学 学術研究・産学官連携推進本部、アカデミックフラッシュ実行委員会  2022.9

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    Type:Competition, symposium, etc.