A hybrid propulsion system (30; 40; 70) for a tiltrotor aircraft (10) comprises one or more engines (24a, 24b) that provide thrust whenever the tiltrotor aircraft is in a first forward flight mode, one or more electrical or hydraulic power sources (32; 42; 72), and two or more pylon assemblies (18a, 18b). Each pylon assembly houses one or more electric or hydraulic motors (34a, 34b; 44a, 44b; 74a, 74b) connected to the one or more electrical or hydraulic power sources and a proprotor (20a, 20b). All or part of each pylon assembly is rotatable. The proprotors provide lift whenever the tiltrotor aircraft is in a vertical takeoff and landing mode and a hover mode, and provide thrust whenever the tiltrotor aircraft is in a second forward flight mode.


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    Title :

    HYBRID PROPULSION SYSTEM FOR CONVERTIBLE AIRCRAFT


    Additional title:

    HYBRIDANTRIEBSSYSTEM FÜR EIN SCHWENKBARES FLUGZEUG
    SYSTÈME DE PROPULSION HYBRIDE POUR AÉRONEF CONVERTIBLE



    Publication date :

    2023-12-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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