著者
笠原 次郎
出版者
一般社団法人 日本燃焼学会
雑誌
日本燃焼学会誌 (ISSN:13471864)
巻号頁・発行日
vol.55, no.174, pp.337-348, 2013 (Released:2018-01-26)
参考文献数
96

First of all in this paper, I show a brief history of a pulse detonation engine research. Thermodynamic analyses for detonation combustion were described, and it was shown that the thermal efficiency of the detonation combustion cycle is higher than the Brayton one. The typical pulse detonation engine operation and gasdynamics models for the simplified pulse detonation engine were illustrated. I also presented recent researches regarding heat and friction losses on a PDE tube wall. The partially-filling effect, ejector effect and nozzle effect on thrust argumentation for PDEs were introduced. As important technical issues of PDEs, I show a deflagration-to-detonation transition process control and gas supplying systems in PDEs. As recent applied researches for PDEs, an air-breathing PDE, a pulse detonation rocket engine, a pulse detonation turbine engine, a PDE thermal spray, and a micro PDE were reported. Finally a rotating detonation engine was introduced.
著者
秋元 雄希 山田 和彦 笠原 次郎 Akimoto Yuki Yamada Kazuhiko Kasahara Jiro
出版者
宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)
雑誌
観測ロケットシンポジウム2019 講演集 = Proceedings of Sounding Rocket Symposium 2019
巻号頁・発行日
2019-08

第2回観測ロケットシンポジウム(2019年8月5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
著者
中道 達也 松岡 健 笠原 次郎 松尾 亜紀子 船木 一幸
出版者
一般社団法人 日本航空宇宙学会
雑誌
航空宇宙技術 (ISSN:18840477)
巻号頁・発行日
vol.10, pp.107-112, 2011 (Released:2012-01-17)
参考文献数
23

We conducted multi-cycle combustion experiments of a coaxial-rotary-valve pulse detonation engine (PDE) system. This PDE system showed a stable operation at the valve rotating frequencies of 5.0, 10, 15, 20, and 33 Hz. We successfully measured propellant mass flow rates, thrusts, and specific impulses in the 2-sec operation duration. The maximum thrust was 32 N at the operation frequency of 33 Hz and at the supply pressure of 0.98 MPa. The maximum specific impulse was 250 sec at the operation frequency of 33 Hz and at the supply pressure of 0.69 MPa. The partial fill ratio was varied from 0.07 to 1.14. The partial fill effect was almost identical to the previous model calculations.
著者
山口 敬之 松岡 健 八桁 純 笠原 次郎
出版者
一般社団法人 日本航空宇宙学会
雑誌
日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences (ISSN:13446460)
巻号頁・発行日
vol.57, no.663, pp.141-147, 2009-04-05
参考文献数
22
被引用文献数
2

In the present study, a dynamics model of an inflow-drive valve for pulse detonation engines (PDEs) is proposed, in which system the inflow of the valve periodically drives the valve piston. Since the inflow-drive valve needs no energy source to drive the piston, the mass flow rate divided by the valve mass is relatively large, and the response time for the mass-flow-rate change can be short. Moreover, the inflow-state condition for the stable valve operation is not restricted. The two-cylinder three-fluid type inflow-drive valve was fabricated. The maximum mass flow rate for one valve was evaluated as 6.3g/s, in which system the mass of the piston, the spring constant, and the supplied pressure were 3.8kg, 9800N, and 1.0MPa, respectively. The total mass flow rate using propellant was evaluated as 12g/s. The PDE system was constructed by using these inflow-drive valves. This system was stably operated in the frequency of 17.52Hz.
著者
羽生 宏人 和田 英一 丹羽 崇博 近藤 靖雄 川村 尚史 丸山 信也 岡村 彩乃 山科 早英良 永井 康仁 中道 達也 上道 茜 田中 成明 小林 直樹 笠原 次郎 森田 泰弘
出版者
一般社団法人 日本航空宇宙学会
雑誌
航空宇宙技術 (ISSN:18840477)
巻号頁・発行日
vol.9, pp.15-21, 2010 (Released:2010-05-14)
参考文献数
6
被引用文献数
1

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.
著者
羽生 宏人 和田 英一 丹羽 崇博 近藤 靖雄 川村 尚史 丸山 信也 岡村 彩乃 山科 早英良 永井 康仁 中道 達也 上道 茜 田中 成明 小林 直樹 笠原 次郎 森田 泰弘
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
航空宇宙技術 (ISSN:18840477)
巻号頁・発行日
vol.9, pp.15-21, 2010
被引用文献数
1

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.
著者
笠原 次郎
巻号頁・発行日
2013

科学研究費助成事業(科学研究費補助金)研究成果報告書:基盤研究(B)2009-2011