Jet Engine Technology Research Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA)
Department of Space Systems and Astronautics, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
Innovative Technology Research Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Jet Engine Technology Research Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Jet Engine Technology Research Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Jet Engine Technology Research Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Jet Engine Technology Research Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA)
Unmanned and Innovative Aircraft Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA)
Department of Space Systems and Astronautics, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
Jet Engine Technology Research Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Jet Engine Technology Research Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
The pre-cooled turbojet engine is one of the most promising candidates for the propulsion system of hypersonic transport. A notable feature of this engine is to use an air pre-cooling device using liquid hydrogen fuel as a coolant in order to protect the turbo-machinery from aerodynamic heating under hypersonic flight conditions. JAXA's recent model of the pre-cooled turbojet engine called "S-Engine" has 0.225 by 0.225 meters square cross section, a total length of 2.67 m, and a mass of 134 kg. It produces a thrust of 122 kgf by firing liquid hydrogen fuel in afterburner, its compressor rotational speed is 80,000 rpm and its compressor pressure ratio is six. This engine is developed for the flight test at Mach 2 condition integrated with a balloon-launched missile-like vehicle. This paper describes pre-flight verification test results of the engine control system including liquid hydrogen supplying system.
飛行実験用極超音速ターボジェットエンジン制御装置の開発
64349000.pdf
(8.28MB)
