A hover-capable aircraft (1) is described comprising a transmission unit (9) with a first module (11) and a lubrication system (25'); the first module (11) comprises a casing (20) and movable members (17); the lubrication system (25') comprises a header (26), a nozzle (27) fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing (20) of the first module (11), a collection tank (100') for the lubricating fluid injected by the nozzle (27), and recirculation means (35) designed to cause the recirculation of the lubricating fluid from the collection tank (100') to the feed header (26); the first module (11) comprises a valve (60') available in a first configuration, in which it enables the outflow of said lubricating fluid from said module (11) to the recirculation means (35) when the pressure of the lubricating fluid inside the header (26) is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module (11) from the recirculation means (35) when the pressure of the lubricating fluid inside the header (26) is less than the threshold value.


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    Titel :

    HOVER-CAPABLE AIRCRAFT


    Weitere Titelangaben:

    SCHWEBEFÄHIGES FLUGZEUG
    AÉRONEF APTE À EFFECTUER UN VOL STATIONNAIRE


    Beteiligte:
    PISANI PAOLO (Autor:in) / MONTAGNA FEDERICO (Autor:in) / REGONINI ROBERTO (Autor:in) / PODDA DANIELE (Autor:in)

    Erscheinungsdatum :

    15.02.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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