Abstract: 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)).

Abstract: The working reinforcement (2) of an aircraft tire is made by the zigzag winding of a strip (5) having width W, with a periodic curve (7), corresponding to the mid-line of the strip, forming, with the circumferential direction (XX), a non-zero angle A. The circumferential distance (c) between the extrema (S51, S52, S53) of the respective mid-lines of two consecutive strip portions (51, 52, 53) is equal to the ratio W/sin A. For any set of three consecutive strip portions (51, 52, 53), made up of a first, a second and a third portion, the respective mid-lines of the first and third strip portions (51, 53) intersect at an intersection point (I), axially aligned with the extremum (S52) of the mid-line of the second strip portion (52) and axially on the inside of said extremum (S52) at an axial distance (a) at least equal to the width W.

Abstract: Crown reinforcement of an aircraft tire with improved mechanical strength in order to increase the burst pressure of the tire, during a standard pressure test. An aircraft tire comprises a working reinforcement made up of a strip (5) wound continuously in a zigzag, from a starting end (51) to an ending end (52), in a circumferential direction (XX?) of the tire, along a periodic curve (7) forming a non-zero angle A with the circumferential direction (XX?) of the tire and in an equatorial plane (XZ) of the tire. The starting end (51) and the ending end (52) of the strip (5) are positioned axially at a distance (DI, DF) at most equal to 0.25 times the axial width WT of the working reinforcement from an axial end (E1, E2) of the working reinforcement.

Abstract: Working reinforcement (2) of an aircraft tire, made by the zigzag winding of a strip (5) having width W, with a periodic curve (7), corresponding to the mid-line of the strip, forming, with the circumferential direction (XX?), a non-zero angle A. The circumferential distance (c) between the extrema (S51, S52, S53) of the respective mid-lines of two consecutive strip portions (51, 52, 53) is equal to the ratio W/sin A. For any set of three consecutive strip portions (51, 52, 53), made up of a first, a second and a third portion, the respective mid-lines of the first and third strip portions (51, 53) intersect at an intersection point (I), axially aligned with the extremum (S52) of the mid-line of the second strip portion (52) and axially on the inside of said extremum (S52) at an axial distance (a) at least equal to the width W.

Abstract: Aeroplane tire (1) comprises a working reinforcement (2) radially between tread (3) and carcass reinforcement (4). Working reinforcement (2) includes a working biply (21) comprised of the zigzag circumferential winding of strip (5) of width W onto a cylindrical laying surface (6) of radius R, with its axis of revolution being axis of rotation (YY?) of the tire, in a periodic curve (7) with period P and forming angle A with circumferential direction (XX?) of the tire in equatorial plane (XZ) of the tire. The winding of strip (5) comprises N periods P of curve (7) over T circumferences 2?R of surface (6). N is a whole number which satisfies the following conditions: (a) N*(W/sin A)=2?R, (b) N*P=2?R*T, where T is a whole number, (c) N*T is the lowest common multiple of N and T, and the ratio T/N is at least equal to 1.8 and at most equal to 2.2.

Abstract: 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)).

Abstract: Working layer (5) comprises a circumferential zigzag winding of a strip (6) on a cylindrical surface having as its axis the axis of rotation of the tire (1), with a periodic curve (7), the peak-to-peak amplitude of which defines the axial width L of the working layer (5) between a first and a second axial end (I, I?). The working layer (5) is made up, in any meridian plane (YZ) containing the axis of rotation of the tire (1), of an arrangement of portions of strip (6) extending axially from the first axial end (I) to the second axial end (I?) of the working layer (5), such that two consecutive portions of strip (6) overlap, at least in part, over a width of overlap e. The width of overlap e between two consecutive portions of strip (6) is constant over the entire axial width L of the working layer (5).

Abstract: An aircraft tire (1) comprises a working reinforcement (2) radially on the inside of a tread (3) and radially on the outside of a carcass reinforcement (4), comprising at least one working bi-ply (5) made up at least in part of two working layers (6, 7) and comprising, at each axial end, an axial-end additional thickness (51). Each working layer (6, 7) is made up of an axial juxtaposition of strips (8) of width W, a strip (8) having a mid-line (81) extending circumferentially along a periodic curve (9) forming, in the equatorial plane (XZ) and with the circumferential direction (XX?), a non-zero angle A and a radius of curvature R at its extrema (10). The ratio R/W is at most equal to N/(1?cosA)+½, such that each axial-end additional thickness (51) comprises at most (N+2) working layers.