Crown reinforcement of an aircraft tire comprises a working reinforcement (2) radially inside of tread (3) and radially outside of carcass reinforcement (4). Working reinforcement (2) comprises two working bi-plies (21, 22) radially superposed with respective axial widths (L1, L2), from first axial end (I1, I2) to second axial end (I′1, I′2). Each working bi-ply (21, 22) comprises two working layers (211, 212; 221, 222) radially superposed and respectively made up of axially juxtaposed portions of strip (5) of axial width W extending circumferentially in periodic curve (6) that forms, in the equatorial plane (XZ) of the tire and with the circumferential direction (XX′) of the tire, a non-zero angle A and has a radius of curvature R at its extrema (7). The difference DL between the respective axial widths (L1, L2) of the radially superposed working bi-plies (21, 22) is at least equal to 2×(W+(R−W/2)−(1−cos A)).


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    Titel :

    Crown Reinforcement For An Aircraft Tire


    Beteiligte:

    Erscheinungsdatum :

    06.10.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B60C VEHICLE TYRES , Fahrzeugreifen / B29D PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE , Herstellen besonderer Gegenstände aus Kunststoff oder aus Stoffen in plastischem Zustand



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