Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Operating 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.
スペースプレーン用複合サイクルエンジンの概念検討
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