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Thrust Measurement of a Multicycle Partially Filled Pulse Detonation Rocket Engine
http://hdl.handle.net/2241/116681
http://hdl.handle.net/2241/116681b4b98017-2c8d-437e-8a8c-526fe73b7036
名前 / ファイル | ライセンス | アクション |
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JPP_25-6.pdf (1.6 MB)
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Item type | Journal Article(1) | |||||
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公開日 | 2012-03-21 | |||||
タイトル | ||||||
タイトル | Thrust Measurement of a Multicycle Partially Filled Pulse Detonation Rocket Engine | |||||
言語 | ||||||
言語 | eng | |||||
資源タイプ | ||||||
資源 | http://purl.org/coar/resource_type/c_6501 | |||||
タイプ | journal article | |||||
著者 |
Kasahara, Jiro
× Kasahara, Jiro× Hirano, Masao× Matsuo, Akiko× Daimon, Yu× Endo, Takuma |
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著者別名 |
笠原, 次郎
× 笠原, 次郎 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | In the present research, we experimentally verified the partial-fill effect in a multicycle pulse detonation rocket engine. The intermittent thrust of a pulse detonation rocket engine was measured by using a spring-damper mechanism that smoothed this intermittent thrust in the time direction. The intermittent mass flow rates were assessed by gas cylinder pressure or mass difference measurement. The maximum specific impulse was 305 9 s at an ethylene and oxygen propellant fill fraction of 0:130 0:004. When the fill fraction was greater than 0.130, the specific impulse was increased as the partial-fill fraction was decreased. When the fill fraction was less than 0.130, the specific impulse was sharply decreased as the partial-fill fraction was decreased. This decrease was due to diffusion between propellant and purge gases and the short length of the transition from deflagration to detonation. The multicycle pulse detonation rocket engine had a partial-fill effect that may have been mainly due to the suctioned air and was consistent with the single-cycle partial-fill model of Endo et al. |
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書誌情報 |
Journal of propulsion and power 巻 25, 号 6, p. 1281-1290, 発行日 2009-11 |
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ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0748-4658 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA10459896 | |||||
DOI | ||||||
識別子タイプ | DOI | |||||
関連識別子 | 10.2514/1.42224 | |||||
権利 | ||||||
権利情報 | ©2009 by University of Tsukuba. Published by the American Institute of Aeronautics and Astronautics, Inc. | |||||
著者版フラグ | ||||||
値 | author | |||||
出版者 | ||||||
出版者 | American Institute of Aeronautics and Astronautics | |||||
URI | ||||||
識別子 | http://hdl.handle.net/2241/116681 | |||||
識別子タイプ | HDL |