Experimental investigation of momentum and heat transfer in pulse detonation rockets

J. Kasahara; Y. Tanahashi; M. Hirano; T. Numata; A. Matsuo; T. Ende

Experimental investigation of momentum and heat transfer in pulse detonation rockets

J. Kasahara, Y. Tanahashi, M. Hirano, T. Numata, A. Matsuo, T. Ende

機械工学科

研究成果: Paper › 査読

3 被引用数 (Scopus)

抄録

The thrust performance and heat transfer in an ethylene-oxygen single tube pulse detonation rocket (PDR), were analyzed. The thrust data were obtained by two measurement devices including, a laser displacement sensor and a load cell. The time average thrusts were 122.2 N (10 Hz) and 130.3 N (12.5 Hz), which were corresponding to 293.7 and 321.2 seconds of effective specific impulses, respectively. It was found that the total heat flux in the wall of the PDR tubes was 400 kW/m².

本文言語	English
ページ	11158-11167
ページ数	10
出版ステータス	Published - 2004 7 1
イベント	42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States 継続期間: 2004 1 5 → 2004 1 8

Other

Other	42nd AIAA Aerospace Sciences Meeting and Exhibit
Country	United States
City	Reno, NV
Period	04/1/5 → 04/1/8

ASJC Scopus subject areas

Engineering(all)

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引用スタイル

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abstract = "The thrust performance and heat transfer in an ethylene-oxygen single tube pulse detonation rocket (PDR), were analyzed. The thrust data were obtained by two measurement devices including, a laser displacement sensor and a load cell. The time average thrusts were 122.2 N (10 Hz) and 130.3 N (12.5 Hz), which were corresponding to 293.7 and 321.2 seconds of effective specific impulses, respectively. It was found that the total heat flux in the wall of the PDR tubes was 400 kW/m2.",

author = "J. Kasahara and Y. Tanahashi and M. Hirano and T. Numata and A. Matsuo and T. Ende",

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T1 - Experimental investigation of momentum and heat transfer in pulse detonation rockets

AU - Kasahara, J.

AU - Tanahashi, Y.

AU - Hirano, M.

AU - Numata, T.

AU - Matsuo, A.

AU - Ende, T.

PY - 2004/7/1

Y1 - 2004/7/1

N2 - The thrust performance and heat transfer in an ethylene-oxygen single tube pulse detonation rocket (PDR), were analyzed. The thrust data were obtained by two measurement devices including, a laser displacement sensor and a load cell. The time average thrusts were 122.2 N (10 Hz) and 130.3 N (12.5 Hz), which were corresponding to 293.7 and 321.2 seconds of effective specific impulses, respectively. It was found that the total heat flux in the wall of the PDR tubes was 400 kW/m2.

AB - The thrust performance and heat transfer in an ethylene-oxygen single tube pulse detonation rocket (PDR), were analyzed. The thrust data were obtained by two measurement devices including, a laser displacement sensor and a load cell. The time average thrusts were 122.2 N (10 Hz) and 130.3 N (12.5 Hz), which were corresponding to 293.7 and 321.2 seconds of effective specific impulses, respectively. It was found that the total heat flux in the wall of the PDR tubes was 400 kW/m2.

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