Hideyuki TAGUCHI, Hidemi TAKAHASHI, Shunsuke IMAMURA, Sadatake TOMIOKA

DOI Number: 10.60853/2mq5-7e50

Conference number: HiSST-2024-00154

Conceptual design of hypersonic combined cycle engines is investigated. A pre-cooled turbojet engine and a scramjet engine are combined to a turbine-based combined cycle (TBCC) engine. The pre-cooled turbojet engine is assumed to be operated from Mach 0 to Mach 5. The scramjet engine is assumed to be operated from Mach 5 to Mach 6. The operating condition of the pre-cooled turbojet engine is confirmed using the results of propulsion wind tunnel test at Mach 4 flight simulating condition. A light weight mode change mechanism is proposed to change the engine cycle from the pre-cooled turbojet engine to the scramjet engine. A waverider shape airframe is designed and the flight performance is calculated for a hypersonic aircraft using the TBCC engine.

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In Categories: 1.Events, HiSST 2024, Propulsion Systems and Components
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