An aircraft (800) comprising a hybrid electric aircraft propulsion system (200). The system (200) comprises a first sub-assembly (1502A) having a first electric propulsor assembly (808A) and a first thermal propulsor assembly (810A), the first thermal propulsor assembly (810A) having a first thermal engine (201A), a first generator (202A) and a first rotating structure (206C), the first electric propulsor assembly (808A) attached to the aircraft (800) at a first location and the first thermal propulsor assembly (810A) attached to the aircraft (800) at a second location. The system (200) also comprises a second sub-assembly (1502B) having a second electric propulsor assembly (808B) and a second thermal propulsor assembly (810B), the second thermal propulsor assembly (810B) having a second thermal engine (201B), a second generator (202B) and a second rotating structure (206F), the second electric propulsor assembly (808B) attached to the aircraft (800) at a third location and the second thermal propulsor assembly (810B) attached to the aircraft (800) at a fourth location.


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    Titel :

    HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM


    Weitere Titelangaben:

    HYBRIDES ELEKTRISCHES FLUGZEUGANTRIEBSSYSTEM
    SYSTÈME DE PROPULSION D'AÉRONEF ÉLECTRIQUE HYBRIDE


    Beteiligte:
    LATULIPE ERIC (Autor:in) / FREER RICHARD (Autor:in)

    Erscheinungsdatum :

    11.03.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / H02P CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS , Steuern oder Regeln von elektrischen Motoren, elektrischen Generatoren, dynamoelektrischen Umformern



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