JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
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Other TitleConceptual study of a combined cycle engine for an aerospace plane
Author(jpn)苅田 丈士; 工藤 賢司
Author(eng)Kanda, Takeshi; Kudo, Kenji
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
Author Affiliation(eng)Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Issue Date2004-03-25
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication date2004-03-25
AbstractOperating conditions and performance of a fixed-geometry combined cycle engine for a Single-Stage-to-Orbit aerospace plane were calculated with a simple simulation model. The cooling requirement of the engine and pitching moment of the plane were investigated using the calculated flow conditions. The engine was composed of an ejector-jet mode, a ramjet mode, a scramjet mode and a rocket mode. The engine had a fixed geometry in its operation. Subsonic combustion was conducted with no second throat in the combustor under the ejector-jet mode and ramjet mode. Propellants were liquid hydrogen and liquid oxygen. The coolant flow rate became larger than the fuel flow rate. The excessive flow rate reduced the specific impulse above Mach 9, and restricted application of the airbreathing engine mode up to Mach 11. The pitching moment of the plane would be balanced even in the space in the configuration with the combined cycle engine mounted on the windward surface.
DescriptionJAXA Research and Development Report
Keywordscombined cycle engine; aerospace plane; performance test; pitching moment; specific impulse; SSTO; air breathing engine; engine performance; 複合サイクルエンジン; スペースプレーン; 性能試験; ピッチングモーメント; 比推力; SSTO; エアブリージングエンジン; エンジン性能
Document TypeTechnical Report
JAXA Category研究開発報告
Report NoJAXA-RR-03-013

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