| 摘要 |
The present invention relates to an aircraft tyre, and in particular the crown reinforcement for an aircraft tyre. An aircraft tyre (1) comprises a working reinforcement (2) radially inside a tread (3) and radially outside a carcass reinforcement (4). The working reinforcement (2) comprises at least two working bilayers (21, 22), which are radially superimposed and respectively have an axial width (L1, L2) from a first axial end (I1, I2) to a second axial end (I'1, I'2). Each working bilayer (21, 22) at least partially comprises two working layers (211, 212; 221, 222), which are radially superimposed and respectively made up of an axial juxtaposition of band portions (5). The band (5), with axial width W, extends circumferentially along a periodic curve (6), forming a non-zero angle A in the equatorial plane (XZ) of the tyre and with the circumferential direction of the tyre (XX') and having a radius of curvature R at its extrema (7). The inventors' aim was to improve the endurance of the working reinforcement of an aircraft tyre by making the axial end overthicknesses of the working layers less sensitive to cracking. According to the invention, the difference DL between the respective axial widths (L1, L2) of the at least two radially superimposed working bilayers (21, 22) is at least equal to 2*(W+(R-W/2)*(1-cosA)). |
