Updated on 2021/05/29

写真a

 
ITOYAMA Noboru
 
Organization
Nagoya University Institute of Materials and Systems for Sustainability Division of Systems Research (DS) Designated assistant professor
Title
Designated assistant professor

Degree 1

  1. 博士(工学) ( 2020.3   東京大学 ) 

Research Interests 7

  1. Catalyst engineering

  2. Combustion engineering

  3. Propulsion engineering

  4. Reaction engineering

  5. Analytical chemistry

  6. Laser applied engineering

  7. Satefy engineering

Research Areas 6

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

  2. Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Thermal engineering

  3. Social Infrastructure (Civil Engineering, Architecture, Disaster Prevention) / Safety engineering

  4. Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Chemical reaction and process system engineering

  5. Nanotechnology/Materials / Energy chemistry

  6. Nanotechnology/Materials / Analytical chemistry  / 機器分析化学

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Current Research Project and SDGs 1

  1. 高エネルギ反応場の化学的制御

Research History 2

  1. Nagoya University   Institute of Materials and Systems for Sustainability Division of Systems Reserch   Designated assistant professor

    2020.4

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    Country:Japan

  2. Japan Society for Promotion of Science   Research Fellowship for Young Scientist

    2018.4 - 2020.3

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    Country:Japan

Education 1

  1. The University of Tokyo   The Graduate School of Engineering   Department of Chemical System Engineering

    2016.4 - 2020.4

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    Country: Japan

Professional Memberships 3

  1. 日本燃焼学会

    2020.4

  2. 日本航空宇宙学会

    2020.4

  3. Japan Explosive Society

    2016.4

Awards 4

  1. 2020年 『美しい炎』の写真展 最優秀作品賞

    2020.12   日本燃焼学会   デトネーションエンジン宇宙へ(Detonation Engine to Space)

    笠原次郎, 松山行一, 松岡健, 川﨑央, 渡部広吾輝, 伊東山登, 後藤啓介, 石原一輝, ブヤコフバレンティン, 野田朋之, 松尾亜紀子, 船木一幸, 羽生宏人, 竹内伸介, 荒川聡, 増田純一, 前原健次, 和田明哲, 岩崎祥大, 中村秀一, 豊永慎治, 原田修, 河野秀文, 山本文孝, 川本昌司, 東野和幸, 中田大将, 内海政春, 味田直也, 神藤博実, 堂山一郎, 加藤辰哉

  2. Japan Explosive Society Award

    2019.5   Japan Explosive Society   Investigation for real-time analysis of HAN-decomposed gas with/without Ir-based catalyst by MPI/TOF-MS

    Noboru Itouyama

  3. Best Poster Award on The 6th International Symposium on Energetic Materials and their Applications (ISEM2017)

    2017.11   Japan Explosive Society  

    Noboru Itouyama, Mamoru Hayata, Yu-ichiro Izato, Atsumi Miyake, Hiroto Habu

  4. Best Presentation Award on the 2017's conference of JES

    2017.5   Japan Explosive Society   Evaluation of direct ignition energy input method to electric conductive liquid propellant

    Noboru Itouyama, Hiroto Habu

 

Papers 17

  1. 将来宇宙利用に向けた高エネルギーイオン液体推進剤の研究 Reviewed

    松永浩貴, 伊東山登, 塩田謙人, 伊里友一朗, 勝身俊之, 羽生宏人, 野田賢, 三宅淳巳

    宇宙航空研究開発機構研究開発報告: 高エネルギー物質研究会令和2年度研究成果報告書   Vol. JAXA-RR-20-007   page: 1 - 4   2021.2

  2. 超小型探査機搭載に向けた革新的超小型推進系技術に関する研究 Reviewed

    和田 明哲, 渡邊 裕樹, 伊東山 登, 月崎 竜童, 池田 知行, 飯塚 俊明, 佐原 宏典, 各務 聡, 松永 浩貴, 伊里 友一朗, 塩田 謙人, 松本 幸太郎, 勝身 俊之, 三宅 淳巳, 笠原 次郎, 志田 真樹, 船瀬 龍, 船木 一幸, 羽生 宏人

    宇宙航空研究開発機構研究開発報告:将来深宇宙探査に向けた革新的超小型推進系研究グループ 2020年度研究成果報告書   Vol. JAXA-RR-20-008   page: 1 - 5   2021.2

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    Publishing type:Research paper (conference, symposium, etc.)  

  3. 高エネルギー物質の気相爆轟に関する基礎検証 Reviewed

    伊東山登

    宇宙航空研究開発機構研究開発報告: 高エネルギー物質研究会令和2年度研究成果報告書   Vol. JAXA-RR-20-007   page: 30 - 32   2021.2

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    Authorship:Lead author   Language:Japanese  

  4. Characterization of Continuous-Wave Laser Heating Ignition of Ammonium Dinitramide-Based Ionic Liquids with Carbon Fibers Reviewed

    Noboru Itouyama, Hiroki Matsunaga, Hiroto Habu

    PROPELLANTS EXPLOSIVES PYROTECHNICS   Vol. 45 ( 6 ) page: 988 - 996   2020.6

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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:WILEY-V C H VERLAG GMBH  

    Ammonium dinitramide-based energetic ionic liquid propellants (ADN-EILPs) exhibit the advantages of high energy density, low toxicity, and handling safety, and are therefore promising monopropellants. Herein, we characterized the ignition of ADN-EILPs induced by CW laser heating in the presence of carbon fibers, clarifying the effect of laser power and suggesting that ignition reproducibility is influenced by the difference of ADN-EILP osmotic state in carbon fibers or carbon fiber configuration. The observed ignition behavior allowed one to conclude that (i) high-power CW laser heating causes the formation of bubbles on the surface, which disturbs further heating; and (ii) an Arrhenius-type relationship exists between ignition delay and heating rate, suggesting that the strategy of foreshortening ADN-EILP ignition delay by increasing CW laser power has certain limits.

    DOI: 10.1002/prep.201900352

    Web of Science

  5. CWレーザ加熱されたカーボン吸光材の液中分散評価 Reviewed

    伊東山登, 羽生宏人

    宇宙航空研究開発機構研究開発報告: 高エネルギー物質研究会令和元年度研究成果報告書   Vol. JAXA-RR-19-003   page: 23 - 26   2020.2

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    Authorship:Lead author  

  6. 超小型宇宙機搭載に向けた一液式推進系のトレードオフ評価 Reviewed

    和田明哲, 伊東山登, 羽生宏人

    宇宙航空研究開発機構研究開発報告: 高エネルギー物質研究会令和元年度研究成果報告書   Vol. JAXA-RR-19-003   page: 11 - 16   2020.2

  7. 高エネルギーイオン液体推進剤の点火システムの研究開発 Reviewed

    松永浩貴, 伊東山登, 和田明哲, 松本幸太郎, 塩田謙人, 伊里友一朗, 勝身俊之, 羽生宏人, 野田賢, 三宅淳巳

    宇宙航空研究開発機構研究開発報告: 高エネルギー物質研究会令和元年度研究成果報告書   Vol. JAXA-RR-19-003   page: 1 - 10   2020.2

  8. Construction and validation of a detailed gas-phase chemical reaction model for ammonium-dinitramide based ionic liquids

    Noboru Itouyama, Yu-ichiro Izato, Atsumi Miyake, Hiroto Habu

    SCIENCE AND TECHNOLOGY OF ENERGETIC MATERIALS   Vol. 81 ( 2 ) page: 53 - 66   2020

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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:JAPAN EXPLOSIVES SOC  

    Ammonium dinitramide (ADN)-based energetic ionic liquid propellants (ADN-EILPs) are promising monopropellants with high energy density, high thermal/chemical stability, and low toxicity. To predict the ignition and combustion characteristics of ADN-EILPs, this study aimed to construct a detailed reaction model of ADN-EILPs in the gas phase by combining conventional thermal decomposition models of the components in ADN-EILPs, the NO2 chain-growth reaction cycle, and additional reactions based on hydrogen abstraction between component species of ADN-EILPs and two radicals, NO2 and OH. The additional reactions were computed using quantum chemistry calculations. The structures of the reactants, products, and transition states were optimized at the omega B97XD/6-311G++(d,p) level of theory, and the total electron energies of these optimized structures were determined at the CBS-QB3 level. The simulated results with the constructed detailed chemical reaction model (EILPs-G-01 model) agreed with the experimental results at approximately 1.2 MPa. The EILPs-G-01 model revealed that the gas-phase combustion of ADN-EILPs has three reaction cycles depending on the radical-related reactions. Moreover, the EILPs-G-01 model clarifies the relationships between the pressure deflagration limit of ADN-EILPs and the weight ratio of methylamine nitrate in the ADN-EILPs.

    Web of Science

  9. Continuous-wave Laser Ignition of Non-solvent Ionic Liquids Based on High Energetic Salts with Carbon Additives

    Noboru Itouyama, Hiroto Habu

    PROPELLANTS EXPLOSIVES PYROTECHNICS   Vol. 44 ( 9 ) page: 1107 - 1118   2019.9

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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:WILEY-V C H VERLAG GMBH  

    The ignition system for ammonium dinitramide-based non-solvent ionic liquids (ADN-EILPs) with a continuous-wave (CW) laser was investigated. The efficiency of conversion from CW laser power to ignition energy for ADN-EILPs is important, and carbon additives are expected to enhance the efficiency of conversion. The impact of additive shapes on ADN-EILP ignition by CW lasers is discussed herein by comparing the results of the ignition behavior observation using a high-speed infrared camera. The shapes of the carbon additives are of two different types: fine fiber mass, called carbon wool, and powder of graphite. The ignition delay of carbon wool mixed ADN-EILPs is shorter than that of the sample with graphite powder. The difference in these results might depend on the low dispersibility in ADN-EILPs of carbon wools and the presence of local heat spots owing to the CW laser. The addition of carbon wools in ADN-EILPs is expected to facilitate their ignition by CW laser heating.

    DOI: 10.1002/prep.201900063

    Web of Science

  10. Study for Ignition of ADN-based Ionic Liquid with Carbon-absorption/CW Laser heating method

    伊東山登, 伊東山登, 羽生宏人

    宇宙航空研究開発機構研究開発報告 JAXA-RR-(Web)   ( 18-006 )   2019

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  11. Construction of detailed chemical reaction model for ADN-EILPs in gas-phase

    伊東山登, 伊東山登, 伊里友一朗, 伊里友一朗, 三宅淳巳, 三宅淳巳, 羽生宏人

    宇宙航空研究開発機構研究開発報告 JAXA-RR-(Web)   ( 18-006 )   2019

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  12. Research and development of thruster with high energetic ionic liquid and laser ignition

    松永浩貴, 伊東山登, 塩田謙人, 伊里友一朗, 伊里友一朗, 勝身俊之, 羽生宏人, 羽生宏人, 野田賢, 三宅淳巳

    宇宙航空研究開発機構研究開発報告 JAXA-RR-(Web)   ( 18-006 )   2019

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  13. Real-time analysis of decomposed gas from HAN(aq.) with/without Ir-based catalyst by thruster-simulation/MPI/TOF-MS

    Noboru Itouyama, Totaro Imasaka, Keiichi Hori

    SCIENCE AND TECHNOLOGY OF ENERGETIC MATERIALS   Vol. 79 ( 3-4 ) page: 102 - 107   2018

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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:JAPAN EXPLOSIVES SOC  

    Using multiphoton ionization/time-of-flight mass spectrometry, we evaluated the validity of the conventional mechanism for thermal decomposition of hydroxylammonium nitrate (HAN) and investigated the corresponding catalytic reaction to determine the decomposed gases in real time, through a pathway that models a real thruster. HAN with a hot catalyst can provide a low-toxicity, high-performance alternative to hydrazine for use in thruster systems. Our results show that the decomposition of HAN mostly follows the conventional model, but some further reactions need to be considered. We found that the catalyst facilitated the reaction of NH2OH with HONO in the catalytic reaction of HAN and propose a new decomposition pathway.

    Web of Science

  14. Investigation for Ignition of ADN-based Ionic Liquid with Visible Pulse Laser

    Noboru ITOUYAMA, Hiroto HABU

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   Vol. 16 ( 3 ) page: 291 - 298   2018

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    Publishing type:Research paper (scientific journal)   Publisher:Japan Society for Aeronautical and Space Sciences  

    DOI: 10.2322/tastj.16.291

  15. Chemical kinetics evaluation of ionic liquid propellant composition

    伊東山登, 伊里友一朗, 伊里友一朗, 三宅淳巳, 羽生宏人

    宇宙航空研究開発機構研究開発報告 JAXA-RR-(Web)   ( 17-008 )   2018

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  16. Study for Ignition of ADN-based Solvent-free Ionic Liquid with Pulse Laser

    伊東山登, 羽生宏人

    宇宙航空研究開発機構研究開発報告 JAXA-RR-(Web)   ( 16-006 )   2017

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  17. Research of Conductive Ionic Liquid Propellant with Electric Ignition

    伊東山登, 羽生宏人

    宇宙航空研究開発機構研究開発報告 JAXA-RR-(Web)   ( 16-006 )   2017

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MISC 16

  1. Propulsive performane of cylindrical rotating detonation engine with propellant injection cooing

    Keisuke Goto, Kosei Ota, Akira Kawasaki, Hiroaki Watanabe, Noboru Itouyama, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

    AIAA Scitech 2021 Forum     page: 1 - 7   2021

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    © 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. An engine cooling concept for cylindrical rotating detonation engine which had an injector surface on the combustor side wall has been tested with three combustor length of 21, 30, and 6 mm. Thrust measurement of the cylindrical RDE (24-mm-diameter) was conducted with monitoring K-type thermocouples inserted in combustor wall. Single rotating detonation wave was observed with the combustor length of 30 and 69 mm in this study. Cooling effect due to the propellant injection was confirmed as the nearly saturated temperature response in the combustor side wall. when the chamber length is more than 30 mm, the specific impulse maintained more than 80% of theoretical value assuming sonic condition at the chamber exit. The result indicated that modest combustor length as an efficient thruster exists in the range of 30 to 69 mm.

    Scopus

  2. Prospects for research of high energetic materials

    松永浩貴, 伊東山登, 和田明哲, 松本幸太郎, 塩田謙人, 伊里友一朗, 勝身俊之, 羽生宏人, 羽生宏人, 野田賢, 三宅淳巳

    火薬学会春季研究発表会講演要旨集   Vol. 2020   2020

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  3. Investigation for the mono-propulsion with a high-energy-density ionic liquid

    伊東山登, 和田明哲, 松永浩貴, 笠原次郎, 羽生宏人

    宇宙科学技術連合講演会講演集(CD-ROM)   Vol. 64th   2020

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  4. Demonstration Study of Pulse Detonation Engine System for Sounding Rocket S-520-31

    BUYAKOFU Valentin, 野田朋之, 澤田悟, JOSEPH Victoria, 後藤啓介, 石原一輝, 渡部広吾輝, 伊東山登, 川崎央, 松岡健, 松山行一, 笠原次郎, 中田大将, 内海政春, 松尾亜紀子, 船木一幸, 竹内伸介, 和田明哲, 岩崎祥大, 羽生宏人

    宇宙科学技術連合講演会講演集(CD-ROM)   Vol. 64th   2020

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  5. Research on high energetic materials with a view to using micro-propulsion system for deep space explorations

    松永浩貴, 伊東山登, 和田明哲, 塩田謙人, 伊里友一朗, 松本幸太郎, 勝身俊之, 早田葵, YU Xiuchao, 久保田一浩, 野副克彦, 羽生宏人, 野田賢, 三宅淳巳

    宇宙科学技術連合講演会講演集(CD-ROM)   Vol. 64th   2020

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  6. Considerations of Innovative Micro Propulsion Systems for Future Deep Space Explorations

    和田明哲, 渡邊裕樹, 伊東山登, 池田知行, 月崎竜童, 飯塚俊明, 佐原宏典, 各務聡, 松永浩貴, 伊里友一朗, 塩田謙人, 松本幸太郎, 勝身俊之, 三宅淳巳, 笠原次郎, 志田真樹, 船瀬龍, 船木一幸, 羽生宏人

    宇宙科学技術連合講演会講演集(CD-ROM)   Vol. 64th   2020

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  7. Study on the ignition of high-energy ionic liquid propellant by laser radiant heating

    伊東山登, 笠原次郎, 羽生宏人

    火薬学会春季研究発表会講演要旨集   Vol. 2020   2020

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  8. Cylindrical rotating detonation engine cooling by means of propellant injection

    Keisuke Goto, Kosei Ota, Akira Kawasaki, Hiroaki Watanabe, Noboru Itouyama, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

    AIAA Propulsion and Energy 2020 Forum     page: 1 - 9   2020

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    © 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. An engine cooling concept for cylindrical rotating detonation engine which had an injector surface on the combustor side wall has been tested and demonstrated. Thrust measurement of the cylindrical RDE (24-mm-diameter) was conducted with monitoring K-type thermocouples inserted in combustor wall. Single rotating detonation wave was observed in the testing conditions ranging from 31 to 59 g/s in this study. Combustion tests for 4.0 ~ 4.9 s were successfully done, and all injector side wall temperature increases were suppressed compared to that of combustor base plate, which had no cooling structure. This could be due to the cooling effect by the heat exchange of propellant injection. In the 4.9 s combustion test with 31 g/s, all thermocouples inserted in the combustor side wall which had the propellant injector surface showed a temperature decreasing 2.5 s after ignition even though the combustion was continuing, and implied the combustion mode shift.

    DOI: 10.2514/6.2020-3855

    Scopus

  9. 高エネルギー物質研究の実績と今後について

    羽生宏人, 羽生宏人, 羽生宏人, 松永浩貴, 塩田謙人, 伊里友一朗, 勝身俊之, 山田泰之, 山田泰之, 松本幸太郎, 岩崎祥大, 伊東山登, 中村太郎, 中村太郎, 三宅淳巳

    火薬学会春季研究発表会講演要旨集   Vol. 2019   2019

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  10. Simplified Performance Analysis of Discharge Plasma Thruster with a High Energetic Ionic Liquid Propellant

    和田明哲, 伊東山登, 羽生宏人

    宇宙科学技術連合講演会講演集(CD-ROM)   Vol. 63rd   2019

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  11. 硝酸ヒドロキシルアミン系一液推進薬の実験的化学反応分析に関する研究

    伊東山登

    火薬学会春季研究発表会講演要旨集   Vol. 2019   2019

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  12. アンモニウムジニトラミド系イオン液体推進薬の気相領域における燃焼機構

    伊東山登, 伊里友一朗, 三宅淳巳, 羽生宏人

    火薬学会春季研究発表会講演要旨集   Vol. 2019   2019

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  13. Research and Development of Ionic Liquid Propellant with High Energetic Materials

    松永浩貴, 伊東山登, 塩田謙人, 伊里友一朗, 勝身俊之, 羽生宏人, 野田賢, 三宅淳巳

    宇宙科学技術連合講演会講演集(CD-ROM)   Vol. 62nd   2018

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  14. 連続光レーザ/浸透式インジェクタを用いたイオン性液体推進薬の着火制御

    伊東山登, 羽生宏人

    火薬学会春季研究発表会講演要旨集   Vol. 2018   2018

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  15. アンモニウムジニトラミド系イオン性液体の気相詳細反応モデル構築と妥当性評価

    伊東山登, 伊里友一朗, 三宅淳巳, 羽生宏人

    火薬学会春季研究発表会講演要旨集   Vol. 2018   2018

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  16. パルスレーザ/ブレイクダウンによる高エネルギーイオン液体推進薬への着火応用

    伊東山登, 羽生宏人

    火薬学会年会講演要旨集   Vol. 2017   2017

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Presentations 21

  1. 観測ロケット S-520 31号機プロジェクト :デトネーションエンジンシステムの宇宙実証

    松岡健, 笠原次郎, 松山行一, 川﨑央, 伊東山登, 渡部広吾輝, 後藤啓介, ブヤコフバレンティン, 石原一輝, 秋元雄希, 野田朋之, 松尾亜紀子, 船木一幸, 中田大将, 内海 政春, 羽生宏人, 竹内伸介, 荒川聡, 増田純一, 前原健次, 山田和彦, 和田明哲

    第3回観測ロケットシンポジウム  2021.3.24 

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    Event date: 2021.3

    Language:Japanese   Presentation type:Oral presentation (general)  

  2. 観測ロケットS-520を用いた液体推進剤デトネーションキックモーター飛行実証実験

    笠原次郎, 松山行一, 松岡健, 川﨑央, 伊東山登, 渡部広吾輝, 後藤啓介, 石原一輝, 松尾亜紀子, 船木一幸, 中田大将, 内海 政春, 羽生宏人, 竹内伸介, 荒川聡, 増田純一, 前原健次, 山田和彦, 和田明哲

    第3回観測ロケットシンポジウム  2021.3.24 

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    Event date: 2021.3

    Language:Japanese   Presentation type:Oral presentation (general)  

  3. Propulsive Performance Analysis of Energetic Ionic Liquid Mono-Propulsion Systems for Micro-Spacecraft

    A. Wada, T. Iizuka, N. Itouyama, H. Sahara, H. Habu

    Space Propulsion 2020  2021.3.17 

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    Event date: 2021.3

    Language:English   Presentation type:Oral presentation (general)  

  4. Study on the Effect of the Difference between Detonation and Constant-pressure Combustion on Thrust Characteristics

    K. Ishihara, K. Yoneyama, S. Ito, H. Watanabe, N. Itouyama, A. Kawasaki, K. Matsuoka, J. Kasahara, A. Matsuo, I. Funaki

    The 10th Asian Joint Conference on Propulsion and Power  2021.3.3 

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    Event date: 2021.3

    Language:English   Presentation type:Oral presentation (general)  

  5. アディティブ・マニュファクチャリング回転デトネーションエンジンの研究

    服部花凜, 太田光星, 石原一輝, 後藤啓介, 伊東山登, 渡部広吾輝, 川﨑央, 松岡健, 笠原次郎, 松尾亜紀子, 船木一幸

    2020年度衝撃波シンポジウム 

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    Event date: 2021.3

    Language:Japanese   Presentation type:Oral presentation (general)  

  6. 水素・酸素及び炭化水素・酸素混合気におけるデトネーション回折時の特性長に対する当量比の影響調査

    孫涵,川﨑央, 伊東山登, 渡部広吾輝, 松岡健, 笠原次郎

    2020年度衝撃波シンポジウム 

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    Event date: 2021.3

    Language:Japanese   Presentation type:Oral presentation (general)  

  7. 拡大流路を有する単円筒回転デトネーションエンジンに関する研究

    中田耕太郎, 太田光星, 石原一輝, 後藤啓介, 伊東山登, 渡部広吾輝, 川﨑央, 松岡健, 笠原次郎, 松尾亜紀子, 船木一幸

    2020年度衝撃波シンポジウム 

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    Event date: 2021.3

    Language:Japanese   Presentation type:Oral presentation (general)  

  8. ラティス構造インジェクターを有する単円筒回転デトネーションエンジンに関する研究

    太田光星, 鈴木遼太郎, 中田耕太郎, 服部花凜, 伊藤志朗, 石原一輝, 後藤啓介, 伊東山登, 渡部広吾輝, 川﨑央, 松岡健, 笠原次郎, 松尾亜紀子, 船木一幸, 川島秀人, 松山新吾, 丹野英幸

    2020年度衝撃波シンポジウム 

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    Event date: 2021.3

    Language:Japanese   Presentation type:Oral presentation (general)  

  9. S-520-31号機によるデトネーションエンジン実験の進捗状況:デトネーションエンジンシステム

    川﨑央, 野田朋之, ブヤコフバレンティン, 石原一輝, 後藤啓介, 伊東山登, 渡部広吾輝, 松岡健, 松山行一, 笠原次郎, 松尾亜紀子, 船木一幸, 中田大将, 内海政春, 竹内伸介, 岩崎祥大, 和田明哲, 増田純一, 荒川聡, 羽生宏人, 山田和彦

    令和二年度宇宙輸送シンポジウム 

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    Event date: 2021.1

    Language:Japanese   Presentation type:Oral presentation (general)  

  10. S-520-31号機によるデトネーションエンジン実験の進捗状況:飛行経路および姿勢予測

    渡部広吾輝, 伊藤志朗, 伊東山登, 川﨑央, 松岡健, 松山行一, 笠原次郎, 松尾亜紀子, 船木一幸, 竹内伸介, 岩崎祥大, 和田明哲, 増田純一, 荒川聡, 羽生宏人, 山田和彦

    令和二年度宇宙輸送シンポジウム 

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    Event date: 2021.1

    Language:Japanese  

  11. S-520-31号機によるデトネーションエンジン実験の進捗状況:回転デトネーションエンジン

    松岡健, 後藤啓介, ブヤコフバレンティン, 石原一輝, 野田朋之, 伊東山登, 川﨑央, 渡部広吾輝, 松山行一, 笠原次郎, 松尾亜紀子, 船木一幸, 中田大将, 内海政春, 竹内伸介, 岩崎祥大, 和田明哲, 増田純一, 荒川聡, 羽生宏人, 山田和彦

    令和二年度宇宙輸送シンポジウム 

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    Event date: 2021.1

    Language:Japanese   Presentation type:Oral presentation (general)  

  12. S-520-31号機によるデトネーションエンジン実験の進捗状況:パルスデトネーションエンジン

    伊東山登, ブヤコフバレンティン, 野田朋之, 石原一輝, 後藤啓介, 川﨑央, 渡部広吾輝, 松岡健, 松山行一, 笠原次郎, 松尾亜紀子, 船木一幸, 中田大将, 内海政春, 竹内伸介, 岩崎祥大, 和田明哲, 増田純一, 荒川聡, 羽生宏人, 山田和彦

    令和二年度宇宙輸送シンポジウム  2021.1.14 

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    Event date: 2021.1

    Language:Japanese  

  13. Propulsive Performance of Cylindrical Rotating Detonation Engine with Propellant Injection Cooing

    K. Goto, K. Ota, A. Kawasaki, H. Watanabe, N. Itouyama, K. Matsuoka, J. Kasahara, A. Matsuo, I. Funaki

    AIAA SciTech 2021 Forum 

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    Event date: 2021.1

    Language:English   Presentation type:Oral presentation (general)  

  14. 大インレット断面積を有する回転デトネーションエンジンの作動特性

    野田朋之, 松岡健, 川崎央, 渡部広吾輝, 伊東山登, 笠原次郎

    第58回燃焼シンポジウム  2020.12.3 

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    Event date: 2020.12

    Language:Japanese   Presentation type:Oral presentation (general)  

  15. 詳細化学反応を用いた高エネルギイオン液体推進薬の着火特性解析

    伊東山登, 伊里友一朗, 三宅淳巳, 笠原次郎, 羽生宏人

    第58回燃焼シンポジウム  2020.12.3 

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    Event date: 2020.12

    Presentation type:Oral presentation (general)  

  16. 矩形反射往復型デトネーションエンジンの推進性能評価

    田口知哉, 松岡健, 川崎央, 渡部広吾輝, 伊東山登, 笠原次郎

    第58回燃焼シンポジウム  2020.12.3 

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    Event date: 2020.12

    Language:Japanese   Presentation type:Oral presentation (general)  

  17. 気相デトネーションの反射点距離に与える希釈種の影響に関する実験的検討

    川崎央, 孫涵, 伊東山登, 渡部広吾輝, 松岡健, 笠原次郎

    第58回燃焼シンポジウム  2020.12.3 

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    Event date: 2020.12

    Language:Japanese   Presentation type:Oral presentation (general)  

  18. 将来深宇宙探査に向けた革新的超小型推進システムの検討

    和田明哲, 渡邊裕樹, 伊東山登, 池田知行, 月崎⻯童, 飯塚俊明, 佐原宏典, 各務聡, 松永浩貴, 伊里友一朗, 塩田謙人, 松本幸太郎, 勝身俊之, 三宅淳, 志田真樹, 船瀬龍, 船木一幸, 笠原次郎, 羽生宏人

    第64回宇宙科学技術連合講演会 

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    Event date: 2020.10

    Language:Japanese   Presentation type:Oral presentation (general)  

  19. 高エネルギーイオン液体の一液推進機応用に関する研究

    伊東山登, 和田明哲, 松永浩貴, 笠原次郎, 羽生宏人

    第64回宇宙科学技術連合講演会 

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    Event date: 2020.10

    Language:Japanese   Presentation type:Oral presentation (general)  

  20. 観測ロケットS-520-31号機搭載用パルスデトネーションエンジンのシステム実証研究

    ブヤコフバレンティン, 野田朋之, 澤田悟, ジョセフビクトリア, 後藤啓介, 石原一輝, 渡部広吾輝, 伊東山登, 川崎央, 松岡健, 松山行一, 笠原次郎, 中田大将, 内海政春, 松尾亜紀子, 船木一幸, 竹内伸介, 和田明哲, 岩崎祥大, 羽生宏人

    第64回宇宙科学技術連合講演会 

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    Event date: 2020.10

    Language:Japanese   Presentation type:Oral presentation (general)  

  21. 深宇宙探査用超小型推進システムを見据えた高エネルギー物質研究

    松永浩貴, 伊東山登, 和田明哲, 塩田謙人, 伊里友一朗, 松本幸太郎, 勝身俊之, 早田葵, 于秀超, 野副克彦, 久保田一浩, 羽生宏人, 野田賢, 三宅淳

    第64回宇宙科学技術連合講演会 

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    Event date: 2020.10

    Language:Japanese   Presentation type:Oral presentation (general)  

▼display all

Works 4

  1. 観測ロケットを用いたデトネーションエンジンの宇宙実証 (S-520-31号機)

    2020.4

  2. High-energy-density ionic liquid propellant

    2016.4

  3. Palm-size high propulsion-density system

    2016.4

  4. Green Propulsion with HEDMs

    2014.4

KAKENHI (Grants-in-Aid for Scientific Research) 3

  1. 高エネルギ物質およびこれを基材とする低毒・高性能液体推進薬の爆轟特性の基礎解明

    Grant number:20K22430  2020.9 - 2022.3

    日本学術振興会  科学研究費助成事業 研究活動スタート支援  研究活動スタート支援

    伊東山 登

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    Authorship:Principal investigator 

    Grant amount:\2860000 ( Direct Cost: \2200000 、 Indirect Cost:\660000 )

    本研究の意義は,高エネルギ物質および高エネルギ物質系液体推進薬の爆轟特性の基礎的な理解にある.アンモニウムジニトラミドや硝酸ヒドロキシルアミンといった高エネルギ物質やこれらを基材とする液体推進薬は自身の熱分解や燃焼によりその高い化学エネルギを瞬時に発揮する.しかし、高エネルギ密度ゆえ,これらの熱分解・燃焼は爆轟現象へ遷移する可能性がある.爆轟が発生した場合,衝撃波を伴うため,取扱時のハザードリスクが重大化する.そこで本研究では,高エネルギ物質および高エネルギ物質系液体推進薬の利用時の安全性を拡充すべく,気相領域を対象とした爆轟特性を理解し,爆轟現象を予測する関数の導出を目指す.

  2. Fundamental study on the catalytic ignition of low-toxicity and high performance monopropellants driven by laser radiation

    2020.4

    The Foundation for the Promotion of the Industrial Explosives Technology  Research Grant 

    Noboru Itouyama, Asato Wada, Hiroto Habu

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    Authorship:Principal investigator 

  3. Investigation of Ignition Mechanism and Control of Ignition Delay of Ionic Liquid Propellant Based on High Energy Salt

    Grant number:18J14397  2018.4 - 2020.3

    Japan Society for the Promotion of Science  Grants-in-Aid for Scientific Research Grant-in-Aid for JSPS Fellows  Grant-in-Aid for JSPS Fellows

    Noboru Itouyama

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    Authorship:Principal investigator 

    Grant amount:\1500000 ( Direct Cost: \1500000 )

Industrial property rights 4

  1. Low gas generator

    Noboru Itouyama

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    Application no:特願PCT/JP2017/019260 

  2. 低温ガス発生剤

    伊東山登

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    Application no:特願2016-114936 

  3. 噴射装置及び推進システム

    伊東山登, 羽生宏人

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    Application no:PCT/JP2018/044151 

  4. 噴射装置及び推進システム

    伊東山登, 羽生宏人

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    Application no:特願2018-048994 

 

Social Contribution 1

  1. 観測ロケットS-520-31号機の紹介

    Role(s):Appearance

    宇宙航空研究開発機構  2020年度JAXA相模原キャンパス特別公開  2021.3

Academic Activities 2

  1. 将来深宇宙探査に向けた革新的超小型推進系研究グループ

    Role(s):Planning, management, etc.

    2020.11

  2. 高エネルギー物質研究会

    Role(s):Planning, management, etc., Peer review

    2020.4

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    Type:Academic society, research group, etc.