研究者業績
基本情報
- 所属
- 国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 宇宙飛翔工学研究系 教授総合研究大学院大学 先端学術院 宇宙科学コース 教授
- 学位
- 博士(工学)(1995年3月 東京大学)
- J-GLOBAL ID
- 200901056190267532
- researchmap会員ID
- 1000253787
- 外部リンク
研究キーワード
5研究分野
3主要な経歴
15-
2019年 - 現在
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2020年 - 2024年6月
学歴
2-
- 1995年
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- 1990年
委員歴
7-
2020年 - 2023年3月
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2022年 - 2023年
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2014年 - 2022年3月
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2014年 - 2015年
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2014年 - 2015年
受賞
3-
2014年
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2012年
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1999年
論文
329-
Journal of Evolving Space Activities 2026年 査読有り
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Journal of Electric Propulsion, 5, 6 2026年 査読有り
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Journal of Propulsion and Power 41(2) 164-177 2025年3月 査読有りThis paper explores the innovative direction control of rotating detonation waves in rotating detonation engines (RDEs) by adjusting the ignition location and employing helical combustors with a sinusoidal cross section. In our experimental setup, we conducted 25 combustion tests using two distinct combustor geometries, each featuring different helical profile directions. The following conclusion drawn from the results: when the ignition was positioned 30.6–46.0 mm from the inlet, the detonation wave direction was invariably influenced by the helical direction. This correlation was statistically significant, with an occurrence probability (assuming a random direction probability of 0.5) being [Formula: see text], far exceeding the 0.05 significance level. Furthermore, the helical combustors generated a measurable torque due to the pressure differentials created by shock waves within the combustor. This torque, recorded between [Formula: see text] at a mass flow rate of 28.5–29.0 g/s, indicates the potential of power extraction from the combustor. Notably, the torque direction was also controllable via the helical direction. This study presents a significant advancement in propulsion technology, demonstrating a novel method to control detonation wave direction and torque generation in RDEs through helical combustor design, paving the way for more efficient and controllable propulsion systems.
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Journal of Electric Propulsion 1-19 2025年3月 査読有り
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Journal of Spacecraft and Rockets, published online 2025年 査読有り
MISC
445-
2011 30th URSI General Assembly and Scientific Symposium, URSIGASS 2011 2011年
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日本物理学会講演概要集 66 239-239 2011年
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低温工学・超電導学会講演概要集 = Meetings of Cryogenics and Superconductivity,83, p. 248 2010年12月
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VACUUM 85(5) 574-578 2010年11月
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IEEE TRANSACTIONS ON ANTENNAS AND PROPAGATION 58(10) 3282-3288 2010年10月
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電子情報通信学会総合大会講演論文集 2010(1) SS_85-SS-86 2010年3月本文データは学協会の許諾に基づきCiNiiから複製したものである
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宇宙航空研究開発機構研究開発報告 9 46-57 2010年2月Electric thrusters, characterized with high specific impulse, are suited to long duration operations such as planetary missions. On the other hand, the performance of many of the conventional electric thrusters is severely limited by electrode wastage. In order to overcome this difficulty, some novel methods of electrodeless discharge and electromagnetic acceleration have been proposed by making use of a compact helicon plasma source. With this application in mind, we here discuss some basic elements on the behaviour of a collisional, cylindrical plasma, when it is driven by an external time-varying electromagnetic field. By introducing a linear response function, we argue that the external field can resonantly drive the plasma to large amplitude oscillations, which may be utilized for the next generation thrusters.
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宇宙航空研究開発機構研究開発報告 9 1-9 2010年2月Improvements have been made to the grid erosion evaluation code (JIEDI-1) to achieve robust convergence and to enhance the accuracies of grid life estimations. The major improved features of the code are 1) the use of Newton-Raphson method and the ICCG solver, 2) modifications of the inlet boundary conditions, 3) incorporation of the differential sputtering yield and redeposition effect of the grid material, and 4) solution-adaptive mesh generation. The last feature is realized by the commercial mesh generation software "pro-STAR". Numerical code prediction of grid mass loss showed good agreement with that of μ10 ion engine life test, with robust convergence and improved simulation time by a factor of 3〜4 in comparison with the previous code.
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2007/2008年度 宇宙関連プラズマ研究会論文集 9 58-66 2010年2月 査読有りA low aspect ratio, high-density helicon plasma has been produced using a flat spiral antenna in the Large Helicon Plasma Device (LHPD) at Institute of Space and Astronautical Science / Japan Aerospace Exploration Agency (ISAS / JAXA). The experimental method employed and some examples of the experimental results are presented. We describe in detail the behavior of the electron density as a function of the radio frequency (rf) input power. In particular, we focus on the behavior of the threshold power, which strongly depends on the magnetic field strength near the antenna, for the discharge mode transition from Inductively Coupled Plasma (ICP) to Helicon Wave Plasma (HWP). The spatial profiles of the rf wave structures for ICP and HWP are also presented in detail.
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2007/2008年度 宇宙関連プラズマ研究会講演集 9 1-10 2010年2月 査読有りOne of the promising candidates for long life electric propulsions in the future is an electrodeless thruster without using any discharge electrodes. The electrodeless plasma acceleration was investigated from the viewpoint of electromagnetic acceleration being different from VASIMR magnetic nozzle expansion. A proposal of continuous electromagnetic acceleration "Lissajous" was attempted. A few preliminary experiments for plasma production and acceleration were performed as the proof-of-concept.
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航空原動機・宇宙推進講演会講演論文集(CD-ROM) 50th ROMBUNNO.AJCPP2010-135 2010年
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Transactions of the Japan Society for Aeronautical and Space Sciences 53(180) 84-90 2010年
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 8(27) Vol. 8, (2010) pp.-Pb_38 2010年An experimental study on coaxial laser-electromagnetic hybrid thrusters was conducted. The laser-electromagnetic hybrid thruster, consisting of a coaxial electrode configuration with an annular copper anode and carbon fiber rod cathode was used to produce laser-induced plasmas, which were further accelerated by electromagnetic force to improve thrust performance. Experimental measurement of impulse bit and mass shot was conducted. From the measurement, thrust performance showed impulse-bit of 2 ∼ 45 μNsec, momentum coupling coefficient of 5 ∼ 14 μNsec/J, specific impulse of 1000 ∼ 1400 sec and thrust efficiency of 3 ∼ 5 % for charge energies 0 ∼ 8.6 J and a laser pulse energy of 120 mJ. In addition, a significant improvement of thrust performance, could be obtained with the use of alumina propellant, which were an impulse-bit (Ibit) of 60 μNsec, a specific impulse (Isp) of 6,000 sec, and a thrust efficiency of 20% at charge energy of 8.6 J.
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 8(27) Pb_19-Pb_25-Pb_25 2010年Magnetic Sail is a propellantless propulsion system proposed for an interplanetary space flight. The propulsive force is produced by the interaction between the magnetic field artificially generated by a hoop coil equipped with the magnetic sail and the solar wind. Three-dimensional hybrid particle-in-cell simulations are performed to reproduce the plasma flow structure around the magnetic sail and to measure the propulsive force of the magnetic sail with two different coil currents. We report the characteristics of the magnetosphere, such as the profile of the magnetic field and the predicted thrust values obtained by simulations, which agree well with laboratory experiments, when simulations are carried out by considering the ion-neutral collision effect. The hybrid particle-in-cell simulation carried out without considering the collisional effect gave a thrust value of 2.3∼3.5 N, which can be applied to the thrust evaluation of the magnetic sail in a magnetosphere with size of 250∼300 km in a collisionless interplanetary space.
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Advances in Applied Plasma Science 7 107-110 2009年8月20日
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日本物理学会講演概要集 64 255-255 2009年 査読有り
主要な書籍等出版物
6講演・口頭発表等
687共同研究・競争的資金等の研究課題
31-
日本学術振興会 科学研究費助成事業 2023年11月 - 2030年3月
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日本学術振興会 科学研究費助成事業 2023年4月 - 2028年3月
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日本学術振興会 科学研究費助成事業 2023年4月 - 2026年3月
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日本学術振興会 科学研究費助成事業 基盤研究(S) 2020年8月 - 2025年3月
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日本学術振興会 科学研究費助成事業 特別推進研究 2019年4月 - 2024年3月