A hybrid-electric aircraft system is provided and includes first and second hybrid-electric engines, each of which includes an electric motor to drive operations thereof, and a supplemental power unit (SPU). The SPU is configured as a thermal engine paired with a generator and is configured to generate electrical power. The first and second hybrid-electric engines are operable normally and off, respectively, with electrical power generated by the SPU being diverted to the electric motor of the second hybrid-electric engine.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    HYBRID-ELECTRIC SINGLE ENGINE DESCENT FAILURE MANAGEMENT


    Beteiligte:

    Erscheinungsdatum :

    2023-05-04


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES



    Hybrid-electric single engine descent failure management

    MULDOON MARC J | Europäisches Patentamt | 2023

    Freier Zugriff

    HYBRID-ELECTRIC SINGLE ENGINE DESCENT FAILURE MANAGEMENT

    MULDOON MARC J | Europäisches Patentamt | 2023

    Freier Zugriff

    HYBRID-ELECTRIC SINGLE ENGINE DESCENT FAILURE MANAGEMENT

    MULDOON MARC J | Europäisches Patentamt | 2023

    Freier Zugriff

    HYBRID ELECTRIC SINGLE ENGINE DESCENT ENERGY MANAGEMENT

    AMARI MARTIN RICHARD / BAIG ZUBAIR AHMED | Europäisches Patentamt | 2023

    Freier Zugriff

    POWER MANAGEMENT IN A HYBRID-ELECTRIC PROPULSION SYSTEM DURING SINGLE ENGINE FAILURE AT DESCENT

    BAIG ZUBAIR AHMED / DUSHEK MATT / AMARI MARTIN RICHARD | Europäisches Patentamt | 2023

    Freier Zugriff