Nagoya University Center for Integrated Research in Science and Engineering
Nagoya University
出版者
宇宙航空研究開発機構宇宙科学研究本部
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
雑誌名
宇宙輸送シンポジウム 平成15年度
雑誌名(英)
Proceedings of Space Transportation Symposium FY2003
ページ
101 - 104
発行年
2004-04
抄録（英）
The performances of pulse detonation engine (PDE) were numerically estimated with detailed chemical reaction model. Flight altitude, flight Mach number, PDE-tube length and fuel-injection forms, i.e. equivalence ratio and distribution of equivalence ratio were altered as operational parameters. In consequence the following possibilities were suggested: The PDE-operation in the lower fuel quantity than stoichiometric mixture gave the higher performances; thrust per mass flowrate of fuel and specific impulse on fuel density, than those in stoichiometric mixture. Moreover, the partial fuel-injection PDE-operation under optimizing fuel-injection form; the equivalence ratio of the head-end side phi(sub closed) = 1.0, that of the open-end side phi(sub open) = 0.0 and the mean equivalence ratio in PDE-tube phi = 0.1, was anticipated to giving the highest-performances for various flight altitudes, and flight Mach numbers. In the same way thrust per mass flowrate of oxidizer, specific impulse on oxidizer, and thrust per unit area of PDE-tube were estimated.
Pulse detonation engineの高効率飛行条件
