An example hybrid aircraft propulsion system (2B) includes a plurality of electrical busses (4) comprising a propulsion bus (4A), a critical bus (4B), and a non-critical bus (4C); an electrical energy storage system (34B) coupled to each of the plurality of electrical busses (4); one or more power units (6) configured to generate and output electrical energy via the propulsion bus (4A); one or more electrical machines (14A, 14B) configured to drive respective propulsors (16A, 16B) using electrical energy received via the propulsion bus (4A); one or more hotel loads (50) configured to receive energy via the non-critical bus (4C); and one or more critical loads configured to receive energy via the critical bus (4B).


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    Title :

    ELECTRICAL ARCHITECTURE FOR HYBRID PROPULSION


    Additional title:

    ELEKTRISCHE ARCHITEKTUR FÜR HYBRIDANTRIEB
    ARCHITECTURE ÉLECTRIQUE POUR PROPULSION HYBRIDE


    Contributors:

    Publication date :

    2021-08-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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