JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
48456000.pdf5.89 MB
Other TitlePerformance analysis of pre-cooled turbojet engines for space planes
Author(jpn)田口 秀之; 二村 尚夫; 柳 良二; 舞田 正孝
Author(eng)Taguchi, Hideyuki; Futamura, Hisao; Yanagi, Ryoji; Maita, Masataka
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部
Author Affiliation(eng)Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Issue Date2005-03-31
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication date2005-03-31
AbstractThe performance of pre-cooled turbojet engines for space planes is analyzed in this study. A program that combines engine performance analysis, flight analysis, and mass estimation is used to determine the payload injection capability of the system. The payload injection capability is then compared to systems with other engines. The pre-cooled turbojet engine has a liquid hydrogen pre-cooler to chill the hot air at high flight Mach number. The engine is considered to be operational up to Mach 6 with existing technologies of supersonic turbojet engines. The engine features high specific impulse and small propellant mass because it uses the air as oxidant. However, both propellant mass and engine mass should be taken into account because the engine mass tends to be much larger than that of rocket engines. A space transportation system with air-breathing engines has a different optimal trajectory than a system with conventional rocket engines, so air-breathing engines and rocket engines cannot be compared in a simple way. It is established that a fuel-rich pre-cooled turbojet engine with an equivalence ratio of nearly 5 is appropriate for single-stage-to-orbit space planes. The combination of a pre-cooled turbojet and a scramjet is proved to provide a larger payload injection capability than the combination of a liquefied air cycle engine and a scramjet.
DescriptionJAXA Research and Development Report
Keywordsturbojet engine; hypersonic flight; numerical analysis; space transportation system; flight characteristic; propulsion system performance; air breathing engine; payload; propellant mass; specific impulse; performance analysis; combined engine; precooled turbojet engine; gas turbine propulsion; ターボジェットエンジン; 極超音速飛行; 数値解析; 宇宙輸送システム; 飛行特性; 推進システム性能; 空気吸込式エンジン; ペイロード; 推進薬質量; 比推力; 性能解析; 複合型エンジン; 予冷ターボジェットエンジン; ガスタービン推進
Document TypeTechnical Report
JAXA Category研究開発報告
Report NoJAXA-RR-04-039

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