A rotor (17, 17') is described, comprising a motor element (16) with an output shaft (18) rotatable around a first axis (C) and controllable with an acceleration (a); a hub (19, 19') connected to the output shaft (18); two blades (25) rotatable around a first axis (C); two connection members (21, 21') connected to the blades (25) and operable for adjusting the angles of attack (α, β, γ; α, β) of the blades (25); a controlling element (20, 20') connected to the connection members (21, 21') and rotatable around a first axis (C); and constraining means (23) adapted to constrain the hub (19, 19') and the controlling element (20, 20'); the constraining means (23, 23') keep the controlling element and the hub (20, 19; 20', 19') angularly integral with one another around the first axis (C) and in a first/second relative position with respect to one another, when the absolute value of the acceleration (a) is smaller/greater than a threshold value (Ta), so that the angles of attack (α, β, γ; α, β) assume first values; the constraining means (23, 23') allow the relative rotation between the controlling element and the hub (20, 19; 20', 19') between the first and second positions when the absolute value of the acceleration (a) reaches the threshold value (Ta).


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    Titel :

    ROTOR FOR AN AIRCRAFT CAPABLE OF HOVERING AND METHOD OF ADJUSTMENT OF ROTOR BLADE ANGLE PITCH


    Weitere Titelangaben:

    ROTOR FÜR EIN SCHWEBEÄHIGES FLUGZEUG UND VERFAHREN ZUR EINSTELLUNG DER ROTORBLATTWINKEL
    ROTOR POUR AÉRONEF APTE À SURVOLER ET PROCÉDÉ DE RÉGLAGE DU PAS DE PALE DE ROTOR


    Beteiligte:

    Erscheinungsdatum :

    02.07.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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