JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
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Other TitleConceptual study of a rocket-ramjet combined-cycle engine for an aerospace plane
Author(jpn)苅田 丈士; 谷 香一郎; 工藤 賢司
Author(eng)Kanda, Takeshi; Tani, Koichiro; Kudo, Kenji
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部 角田宇宙センター; 宇宙航空研究開発機構 総合技術研究本部 角田宇宙センター; 宇宙航空研究開発機構 総合技術研究本部 角田宇宙センター
Author Affiliation(eng)Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology; Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology; Japan Aerospace Exploration Agency Kakuda Space Center, Institute of Aerospace Technology
Issue Date2007-03-30
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication date2007-03-30
AbstractOperating conditions of a rocket-ramjet combined cycle engine for a single-stage-to-orbit aerospace plane were studied. The operation modes of the engine included an ejector-jet mode, a ramjet mode, a scramjet mode and a rocket mode. Characteristics of the engine operating conditions were studied analytically. Study of the effective impulse function revealed that a higher specific impulse was preferable in supersonic flight, whereas a greater thrust coefficient was preferable in hypersonic flight. These characteristics were examined by simulating an engine operating in an aerospace plane flight. A comparison was made between several engines with different combinations of thrust and specific impulse when used for the transportation of a mass into orbit. The mass that could be carried into orbit was larger with a ramjet mode of higher specific impulse and with a scramjet mode of greater thrust. In the present study, the thrust augmentation effect of the ejector-jet mode was also found to be small at low subsonic speeds and to increase with increasing flight Mach number.
DescriptionJAXA Research and Development Report
Keywordsrocket-ramjet combined-cycle engine; ejector jet engine; computerized simulation; specific impulse; hypersonic flight; supersonic flight; flight simulation; Mach number; aerospace plane; SSTO; ロケットラムジェット複合エンジン; エジェクタジェットエンジン; 計算機シミュレーション; 比推力; 極超音速飛行; 超音速飛行; 飛行シミュレーション; マッハ数; スペースプレーン; SSTO
Document TypeTechnical Report
JAXA Category研究開発報告
Report NoJAXA-RR-06-022

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