A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.


    Access

    Download


    Export, share and cite



    Title :

    HYBRID ELECTRIC PROPULSION SYSTEM AND METHOD OF OPERATION


    Additional title:

    SYSTEME DE PROPULSION HYBRIDE ELECTRIQUE ET SA METHODE DE FONCTIONNEMENT


    Contributors:

    Publication date :

    2020-03-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



    Hybrid electric propulsion system and method of operation

    LATULIPE ERIC / FREER RICHARD | European Patent Office | 2022

    Free access

    Hybrid electric propulsion system and method of operation

    LATULIPE ERIC / FREER RICHARD | European Patent Office | 2023

    Free access

    HYBRID ELECTRIC PROPULSION SYSTEM AND METHOD OF OPERATION

    LATULIPE ERIC / FREER RICHARD | European Patent Office | 2022

    Free access

    HYBRID ELECTRIC PROPULSION SYSTEM AND METHOD OF OPERATION

    LATULIPE ERIC / FREER RICHARD | European Patent Office | 2022

    Free access

    HYBRID ELECTRIC PROPULSION SYSTEM AND METHOD OF OPERATION

    LATULIPE ERIC / FREER RICHARD | European Patent Office | 2022

    Free access