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System Analysis of a Hydrocarbon-Fueled RBCC Engine Applied to a TSTO Launch Vehicle
https://jaxa.repo.nii.ac.jp/records/22508
https://jaxa.repo.nii.ac.jp/records/2250865ed338d-0006-4ec8-afd8-e1df7d82d4df
Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2020-01-22 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | System Analysis of a Hydrocarbon-Fueled RBCC Engine Applied to a TSTO Launch Vehicle | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | RBCC Engines | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | TSTO Launch Vehicle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | System Analysis | |||||
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 |
Tomioka, Sadatake
× Tomioka, Sadatake× Hiraiwa, Tetso× Saito, Toshihito× Kato, Kanenori× Kodera, Masatoshi× Tani, Koichiro |
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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) | ||||||
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_91-Pa_99, 発行日 2014-12-26 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Engine system analysis upon a Rocket-Based Combined Cycle (RBCC) engine for the booster stage of a TSTO launch vehicle was conducted, to evaluate the benefits of hypersonic air-breathing technology upon the performance of the launch vehicle. Hydrocarbon fuel (namely ethanol) and LOx was selected as the propellant of the vehicle to enable easy handling and good packaging of high-density fuel into the airplane-like vehicle shape. First, parametric study on the ramjet-duct portion of the RBCC engine was conducted for fixed embedded rocket engine parameters. Then the rocket engine parameters were varied for the fixed ramjet-duct parameters to attain best performance with a fixed ramjet-duct projected area. The analysis method and primary results are herein reported. | |||||
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_91 | |||||
関連名称 | info:doi/10.2322/tastj.12.Pa_91 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: PA1510007000 |