A combined cycle propulsion system for a flight vehicle includes a compressor-fed combustion engine, and a multi-mode supersonic engine. The multi-mode supersonic engine includes an adjustable inlet section, a combustion section arranged downstream of the adjustable inlet section and including a first combustor portion having at least one rotating detonation combustor and a second combustor portion having a supersonic combustion type combustor, and an adjustable exhaust nozzle section arranged downstream of the combustion section. The at least one rotating detonation combustor functions as a pilot for the supersonic combustion type combustor.


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    Title :

    COMBINED CYCLE PROPULSION SYSTEM FOR HYPERSONIC FLIGHT



    Publication date :

    2023-10-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT






    Hypersonic and Combined Cycle Propulsion for Civil Applications

    Timnat, Y. M. / Gany, A. / International Astronautical Federation | British Library Conference Proceedings | 1995


    Terrestrial hypersonic flight propulsion

    Foreman, K.M. | Engineering Index Backfile | 1963