A hybrid electric system for a rotorcraft can include a first thermal engine (103a), a second thermal engine (103b), and an electrical machine (105). The first thermal engine (103a) can be sized to produce a maximum first thermal engine power that is below a one-or-more-engine-inoperative (OEI) requirement power and the second thermal engine (103b) can be sized to produce a maximum second thermal engine power that is below the OEI requirement power. The electrical machine (105) can be sized to provide at least a remaining power needed to reach the OEI requirement power in an OEI state.


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    Title :

    HYBRID ELECTRIC SYSTEMS FOR ROTORCRAFT


    Additional title:

    ELEKTRISCHE HYBRIDSYSTEME FÜR DREHFLÜGELFLUGZEUG
    SYSTÈMES ÉLECTRIQUES HYBRIDES POUR GIRAVION


    Contributors:

    Publication date :

    2022-09-21


    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 / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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