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Combustion Phenomena within a RBCC Engine under Scramjet-mode Operation
https://jaxa.repo.nii.ac.jp/records/22444
https://jaxa.repo.nii.ac.jp/records/22444821db189-0349-4c9e-bf69-164a5696805c
Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Combustion Phenomena within a RBCC Engine under Scramjet-mode Operation | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | RBCC Engines; Hypersonic Flight Regime; Combustion Enhancement | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | journal article | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
著者 |
小室, 智幸
× 小室, 智幸× 富岡, 定毅× Takagi, Shohei× 高橋, 政浩× 植田, 修一× 伊藤, 勝宏× Komuro, Tomoyuki× Tomioka, Sadatake× Takagi, Shohei× Takahashi, Masahiro× Ueda, Shuichi× Itoh, Katsuhiro |
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著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
出版者 | ||||||
出版者 | 日本航空宇宙学会(JSASS) | |||||
出版者(英) | ||||||
出版者 | The Japan Society for Aeronautical and Space Sciences (JSASS) | |||||
書誌情報 |
en : Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan 巻 12, 号 ists29, p. Pa_71-Pa_77, 発行日 2014-07 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Combination of a scramjet (supersonic combustion ramjet) flow-pass with embedded rocket engines (the combinedsystem termed as Rocket Based Combined Cycle engine) are expected to be the most effective propulsion system forBooster stage of space launch vehicles. At hypersonic regime, it will be operated at rather high rocket engine output forfinal acceleration with some Isp gains due to air-breathing effects. In this regime, attaining thrust at this high-speedregime becomes very difficult, so that parallel injection of the fuel for scramjet combustion is favorable as the momentumof the injection can contribute to the thrust production. Thus, embedded rocket chamber was supposed to the operated asfuel rich gas generator at very high output. This configuration was tested at simulated flight Mach number of 11 at HighEnthalpy Shock Tunnel (HIEST) with detonation tube as the source of the simulated rocket exhaust. However,combustion of the residual fuel in the rocket exhaust with airflow could not be attained in the past study, so thatmodification was carried out. Combustion was attained within the combustor, however, insufficient mixing was found toresponsible for the rather low combustion efficiency, finding being from complementary mixing test at a blow-down typetunnel. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1884-0485 | |||||
DOI | ||||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.2322/tastj.12.Pa_1 | |||||
関連名称 | info:doi/10.2322/tastj.12.Pa_1 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: PA1410085000 |