Crown Reinforcement For An Aircraft Tire

Patent metadata

Field	Value
Publication number	US-2016288576-A1
Application number	US-201415036608-A
Country	US
Kind code	A1
Filing date	Nov 6, 2014
Priority date	Nov 15, 2013
Publication date	Oct 6, 2016
Grant date	—

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 (L 1 , L 2 ), from first axial end (I 1 , I 2 ) 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 (L 1 , L 2 ) of the radially superposed working bi-plies ( 21, 22 ) is at least equal to 2×(W+(R−W/2)−(1−cos A)).

First claim

1 . An aircraft tire comprising:
a working reinforcement radially on the inside of a tread and radially on the outside of a carcass reinforcement; the working reinforcement comprising at least two working bi-plies which are radially superposed and respectively have an axial width, from a first axial end to a second axial end; each said working bi-ply comprising at least in part two working layers that are radially superposed and respectively made up of an axial juxtaposition of portions of a strip; the strip, of axial width W, extending circumferentially in a periodic curve that forms, in the equatorial plane of the tire and with the circumferential direction of the tire, a non-zero angle A and has a radius of curvature R at its extrema; the strip being made up of reinforcers coated in an elastomeric compound; wherein the difference DL between the respective axial widths of the at least two radially superposed working bi-plies is at least equal to 2×(W+(R−W/2)×(1−cos A)).

2 . The aircraft tire according to claim 1 , wherein the axial width W of the strip is at least equal to 2 mm.

3 . The aircraft tire according to claim 1 , wherein the axial width W of the strip is at most equal to 20 mm.

4 . The aircraft tire according to claim 1 , wherein the ratio R/W between the radius of curvature R, at the extrema of the periodic curve of the strip, and the width W of the strip is at least equal to 13.

5 . The aircraft tire according to claim 1 , wherein the angle A formed by the periodic curve of the strip in the equatorial plane and with the circumferential direction is at least equal to 3°.

6 . The aircraft tire according to claim 1 , wherein the angle A, formed by the periodic curve of the strip in the equatorial plane and with the circumferential direction is at most equal to 35°.

7 . The aircraft tire according to claim 1 , wherein the reinforcers of the strip are made of a textile material.

8 . The aircraft tire according to claim 1 , wherein the reinforcers of the strip are made of an aliphatic polyamide.

9 . The tire according to claim 1 , wherein the reinforcers of the strip are made of an aromatic polyamide.

10 . The aircraft tire according to claim 1 , wherein the reinforcers of the strip are made of a combination of an aliphatic polyamide and of an aromatic polyamide.

11 . Method of manufacturing an aircraft tire according to claim 1 , comprising a step of manufacturing the working reinforcement, wherein the at least two working bi-plies that are radially superposed and respectively have an axial width, from a first axial end to a second axial end, are obtained by circumferential zigzag winding of the strip, of axial width W, on the lateral surface of a tire building drum of radius R f and having as its axis the axis of rotation of the tire, with the periodic curve forming, in the equatorial plane and with the circumferential direction, the non-zero angle A and having the radius of curvature R at its said extrema such that the difference DL between the respective axial widths of the at least two radially superposed working bi-plies is at least equal, in terms of absolute value, to 2×(W+(R−W/2)×(1−cos A)).

12 . The aircraft tire according to claim 1 , wherein the axial width W of the strip is at least equal to 6 mm.

13 . The aircraft tire according to claim 1 , wherein the axial width W of the strip is at most equal to 14 mm.

14 . The aircraft tire according to claim 1 , wherein the angle A formed by the periodic curve of the strip in the equatorial plane and with the circumferential direction is at least equal to 5°.

15 . The aircraft tire according to claim 1 , wherein the angle A, formed by the periodic curve of the strip in the equatorial plane and with the circumferential direction is at most equal to 25°.

Assignees

• Michelin & Cie
• Michelin Rech Tech

Inventors

• Romero De La Osa Marc
• Delacroix Serge

Classifications

• B60C9/2003 Primary

  characterised by the materials of the belt cords · CPC title

• B29K2713/02

  coated · CPC title

• B60C9/02

  Carcasses · CPC title

• B29K2277/10

  Aromatic polyamides [Polyaramides] or derivatives thereof · CPC title

• B60C9/2204

  obtained by circumferentially narrow strip winding · CPC title