Aeroplane tire with crown and carcass both having a concave portion

Patent metadata

Field	Value
Publication number	US-9731557-B2
Application number	US-201214361442-A
Country	US
Kind code	B2
Filing date	Nov 20, 2012
Priority date	Nov 29, 2011
Publication date	Aug 15, 2017
Grant date	Aug 15, 2017

Abstract

The tire comprises a tread, a crown reinforcement and at least one crown layer. The crown layer has an axial width (L 2 ) that is at least two-thirds of a maximum axial width (L 1 ) of the tire and has a concave portion with axial limits (M 2 , M′ 2 ) on either side of an equatorial plane (XZ). The tire further includes a carcass reinforcement which has at least one carcass layer with a concave portion that has axial limits (M 3 , M′ 3 ) on either side of the equatorial plane (XZ). The radial distance (d) between the respective concave portions is at a maximum in the equatorial plane (XZ) and decreases continuously from the equatorial plane (XZ) as far as the axial limits (M 2 , M′ 2 ) of the said concave portions axially closest to the equatorial plane (XZ), where it reaches a minimum value (d M ).

First claim

The invention claimed is:

1. An aeroplane tire comprising:
a tread,
a crown reinforcement radially on the inside of the tread and comprising at least one crown layer,
the radially interior crown layer having an axial width (L 2 ) at least equal to two-thirds of the maximum axial width (L 1 ) of the tire and comprising a concave portion of which the axial limits (M 2 , M′ 2 ), on either side of the equatorial plane, are the radially exterior points of the said radially interior crown layer,
two beads and two sidewalls connecting the tread to the beads,
a carcass reinforcement radially on the inside of the crown reinforcement and comprising at least one carcass layer, each carcass layer connecting the two beads,
the radially exterior carcass layer comprising a concave portion of which the axial limits (M 3 , M′ 3 ), on either side of the equatorial plane, are the radially exterior points of the radially exterior carcass layer,
wherein the radial distance (d) between the respective concave portions of the radially interior crown layer and of the radially exterior carcass layer is at a maximum in the equatorial plane and decreases continuously from the equatorial plane as far as the axial limits (M 2 , M′ 2 ) of the said concave portions axially closest to the equatorial plane, where it reaches a minimum value (d M ).

2. The aeroplane tire according to claim 1 , wherein the maximum radial distance (d C ) between the concave portions is at least equal to 1.75 times the minimum radial distance (d M ) between the concave portions.

3. The aeroplane tire according to claim 2 , wherein the maximum radial distance (d C ) between the concave portions is at least equal to 2.5 times the minimum radial distance (d M ) between the concave portions.

4. The aeroplane tire according to claim 1 , wherein the maximum radial distance (d C ) between the concave portions is at least equal to 2.3 mm.

5. The aeroplane tire according to claim 4 , wherein the maximum radial distance (d C ) between the concave portions is at least equal to 3.3 mm.

6. The aeroplane tire according to claim 1 , wherein the minimum radial distance (d M ) between the concave portions is at least equal to 1.3 mm and at most equal to 2.5 mm.

7. The aeroplane tire according to claim 1 , wherein an amplitude of concavity (a 2 ) of the radially interior crown layer, defined as being the radial distance between a point (C 2 ) positioned in the equatorial plane and one of the axial limits (M 2 , M′ 2 ) of the concave portion, is at least equal to 1 mm.

8. The aeroplane tire according to claim 1 , wherein an amplitude of concavity (a 3 ) of the radially exterior carcass layer, defined as being the radial distance between the point (C 3 ) positioned in the equatorial plane and one of the axial limits (M 3 , M′ 3 ) of the concave portion, is at least equal to 1 mm.

9. The aeroplane tire according to claim 1 , further comprising a hooping reinforcement comprising at least one hooping layer, each hooping layer having an axial width (L 4 ) at most equal to half the maximum axial width (L 1 ) of the tire and comprising reinforcing elements that are parallel to one another and inclined, with respect to a circumferential direction, by an angle of between +10° and −10°, wherein the hooping reinforcement is radially on the inside of the concave portion of the radially interior crown layer and radially on the outside of the concave portion of the radially exterior carcass layer.

10. The aeroplane tire according to claim 9 , wherein the hooping reinforcement comprises two of the hooping layers.

11. The aeroplane tire according to claim 9 , wherein the reinforcing elements of the at least one hooping layer are each made of aliphatic polyamides, aromatic polyamides, or a combination of aliphatic polyamides and of aromatic polyamides.

12. The aeroplane tire according claim 1 , wherein each crown layer comprises reinforcing elements that are parallel to one another and inclined, with respect to a circumferential direction, by an angle of between +20° and −20°, wherein the reinforcing elements of the at least one crown layer are each made of aliphatic polyamides, aromatic polyamides, or a combination of aliphatic polyamides and of aromatic polyamides.

13. The aeroplane tire according to claim 1 , wherein each carcass layer comprises reinforcing elements that are parallel to one another and perpendicular to a circumferential direction, wherein the reinforcing elements of the at least one carcass layer are each made of aliphatic polyamides, aromatic polyamides or a combination of aliphatic polyamides and of aromatic polyamides.

Assignees

• Michelin & Cie
• Michelin Rech Tech
• Michelin Rech Tech

Inventors

• Estenne Vincent
• Caffeau Charlotte

Classifications

• B60C9/28 Primary

  characterised by the belt or breaker dimensions or curvature relative to carcass (B60C9/30 takes precedence) · CPC title

• B60C19/00

  Tyre parts or constructions not otherwise provided for · CPC title

• B60C2200/02

  for aircrafts · CPC title

• B60C9/18 Primary

  Structure or arrangement of belts or breakers, crown-reinforcing or cushioning layers · CPC title

• B60C2009/283

  characterised by belt curvature · CPC title