An aircraft propulsion system. The system comprises an internal combustion engine (6, 106) configured to drive a first propulsor (4, 110) and an electric generator (15, 115). The system further comprises an electric motor or motors (15, 115, 120) each configured to be powered by electric power provided by the generator (15, 115), and configured to drive the first propulsor (5, 110) and / or a second propulsor (121). An electrical energy storage unit (9, 109) is provided, and is configured to store electrical energy supplied from the generator (15, 115) and supply electrical power to the electric motor (15, 115, 120). At maximum take-off power, the electric motor (15, 115, 120) provides between 5% and 20% of total maximum aircraft propulsive take-off power.


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    Titel :

    Hybrid electric aircraft


    Erscheinungsdatum :

    2018-08-29


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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