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nalrp2001029.pdf139.36 kB
titleStudy of Scramjet Engine System
Author(jpn)苅田, 丈士
Author(eng)KANDA, Takeshi
Author Affiliation(jpn)航空宇宙技術研究所角田宇宙推進技術研究センターラムジェット推進研究部
Author Affiliation(eng)Ramjet Propulsion Research Division, Kakuda Research Center, National Aerospace Laboratory(NAL)
Issue Date2001
National Aerospace Laboratory(NAL)
Publication titleNAL RESEARCH PROGRESS 1998~2000
Start page72
End page73
Publication date2001-01
Description1. Introduction The scramjet engine for the single-stage-to-orbit (SSTO) aerospace plane has been studied in the ramjet propulsion research division. The problems of the scramjet are (1) combustion, (2) light structure, (3) startability of the inlet, (4) integration of engines, and (5) cooling. The construction of the cooling system is important for the scramjet engine, because of high heat flux during operation. Cooling is not only a problem for the engine itself, but also for the airframe. SSTO has a unique feature, i.e., staying in space after aerodynamic heating. Thus the heat management of the airframe in space will be a problem, as well as cooling in the ascent phase. The heat will be exhausted by radiation or by transporting to propellant. Thus, the engine and the airframe are integrated in the cooling system, as well as in the propulsive performance. The optimization of the airframe geometry for the engine performance is an important subject. Here, a cooling system for the scramjet engine is presented, as well as those of the airframe thermal protection system (TPS). The effect of the airframe geometry on the propulsive performance is also introduced.
Keywordsscramjet, aerospace plane, engine system, thermal protection system
Document TypeTechnical Report
JAXA Category航空宇宙技術研究所
Report NoNAL R.P.

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