Provided is a flight efficiency improving system for a compound helicopter (1) comprising a rotor (3) and fixed wings (4). In forward flight of the compound helicopter (1), the flight efficiency improving system does not perform a cyclic pitch control of the rotor (3) so as to allow a difference in lift generated by the rotor (3) between an advancing side and a retreating side of the rotor (3), or the flight efficiency improving system performs the cyclic pitch control to an extent that does not completely eliminate the difference. The fixed wings (4) are provided respectively on left and right sides of a body (2) and are asymmetric to each other so that influence of an aerodynamic interference between the rotor (3) and the fixed wings (4) is reduced.


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    Titel :

    FLIGHT EFFICIENCY IMPROVING SYSTEM FOR COMPOUND HELICOPTER


    Weitere Titelangaben:

    FLUGEFFIZIENZVERBESSERUNGSSYSTEM FÜR EINEN VERBUNDHUBSCHRAUBER
    SYSTÈME D'AMÉLIORATION DE L'EFFICACITÉ DE VOL D'UN HÉLICOPTÈRE COMBINÉ


    Beteiligte:
    KOBAYASHI WATARU (Autor:in) / HAYASHI HIROTAKA (Autor:in) / NAKAMURA MIZUKI (Autor:in) / SASAKI MASAFUMI (Autor:in) / TANABE YASUTADA (Autor:in) / KOBIKI NOBORU (Autor:in)

    Erscheinungsdatum :

    2024-03-20


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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