研究者業績
基本情報
研究キーワード
12経歴
1-
2022年8月 - 現在
受賞
10主要な論文
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Science and Technology of Energetic Materials : journal of the Japan Explosive Society 73(5) 147-152 2012年12月31日 査読有り筆頭著者
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航空宇宙技術(Web) 9 15-21 2010年 査読有り筆頭著者The educational hybrid-rocket was successfully launched and it also landed within the predicted area. Aerodynamic characteristics of the rocket designed by students of Tsukuba University were evaluated by the wind tunnel testing with the support of Tokai University. The flight path affected by the environmental condition, especially wind direction and velocity, was simulated with the original calculation program. The altitude of the rocket was measured with the optical equipment and the apex was 123 m although the calculation indicated 198 m. We expected that the insufficient filling or the volatilization of Nitrous oxide as an oxidizer led to this result. And then, the apex was verified with a function of the oxidizer filling ratio. The results showed that 81.2 % of the oxidizer volume in comparison with the firing test condition was accumulated in the tank at the launch.
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Science and Technology of Energetic Materials : journal of the Japan Explosive Society 67(6) 187-192 2006年12月31日 査読有り筆頭著者
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火薬学会誌 = Journal of the Japan Explosives Society : explosion, explosives and pyrotechnics 60(2) 83-90 1999年4月30日 査読有り筆頭著者
MISC
140講演・口頭発表等
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2014 ASIA-PACIFIC INTERNATIONAL SYMPOSIUM ON AEROSPACE TECHNOLOGY, APISAT2014 2015年 ELSEVIER SCIENCE BVAs an alternative to hydrazine, ammonium dinitramide-based ionic liquid propellant (ADN-based ILP) was developed. It is mixture of the solid powders: ammonium dinitramide, monomethylamine nitrate, and Urea. It has a feature to be able to adjust the performance of monopropellant by change of the compositions because the constituents have different role: oxidizer, fuel, and freezing point depressant. By adjusting the components, it has high specific impulse and fuel rich and low freezing point comparing to hydrazine. The basic combustion characteristics of ADN-based ILP were investigated in the strand burner tests for application to thruster. The self-sustainable combustion, the linear burning rates, and the flame temperatures were shown in the results. The features of the ADN-based ILP were discussed on the basis of the results. As a problem of the thruster application, the ignition in vacuum was also discussed. (C) 2015 Published by Elsevier Ltd.
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平成26年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2014 2015年 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)平成26年度宇宙輸送シンポジウム（2015年1月15日-16日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県資料番号: SA6000036007レポート番号: STCP-2014-007
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第47回月・惑星シンポジウム = Proceedings of the 47th ISAS Lunar and Planetary Symposium 2014年8月 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)第47回月・惑星シンポジウム (2014年8月4日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県形態: カラー図版あり資料番号: SA6000033030
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Proc. 29th International Symposium on Space Technology and Science 2013年6月
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Proc. of 16th International Seminar New Trends in Research of Energetic Materials 2013年4月
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48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 2012年12月1日A new small solid launcher named Epsilon is currently under development in JAXA. The Epsilon launch vehicle is normally three stage rocket system and can be added an optional liquid propulsion system to the third stage for the missions requiring precision orbit insertion. The SRB-A motor boosting the H-IIA vehicle and the H-IIB vehicle will be shared as the first stage motor. Upper-stage motors are inherited from the fifth M-V launch vehicle, from the viewpoints of development cost reduction, performance increase, and advanced technology succession. The solid motor side jet (SMSJ) system, which is used for the roll control during the first stage powered flight and the three-axis control after the SRB-A burnout, will be newly developed based on the technology of the SMSJ for the M-V vehicle. A maiden flight of the first Epsilon is scheduled in the summer of 2013. A successive concept of the advanced propulsion technologies for next-gen Epsilon are also described in the present paper. There are many technical challenges, such as new propellants and mass reduction of nozzle liner, to be tackled with for the next couple of year. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
