Crown reinforcement for an airplane tyre
A technology for aircraft tires and reinforcements, applied in aircraft tires, reinforcement layers of pneumatic tires, tire parts, etc., can solve the problems of centrifugal expansion profile control damage, accelerated tread wear, and tire cornering stiffness reduction, etc., to reduce The effect of exposed risk
Active Publication Date: 2016-12-14
MICHELIN & CO CIE GEN DES ESTAB MICHELIN
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Problems solved by technology
[0028] Optimizing the geometrical profile of the second intermediate element, which is located axially inside the protective reinforcement and axially outside the working reinforcement, but this may lead to said second intermediate element following the tread premature exposure of the surface of the tread due to wear, thereby leading to the risk of accelerated tread wear;
[0029] The use of circumferential reinforcements for the working plies, in other words the reinforcements form a zero angle to the circumferential direction, which can lead to a decrease in the cornering stiffness of the tire and impairment of its centrifugal expansion profile control
Method used
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Embodiment Construction
[0054] figure 1 shows, in a proceeding plane YZ passing through the axis of rotation YY' of the tire, a view of one half of the cross-section of the crown of an aircraft tire 1 of the prior art, comprising radially inside the tread 3 and reinforced in the carcass The working reinforcement 2 on the radially outer side of the piece 4. In the example given, the working reinforcement 2 comprises 5 working double plies 21, the radially innermost working double ply having a maximum axial width L measured between its two axial ends T . figure 1 Only the half width L between the axial end E of the radially innermost working double ply 21 and the equatorial plane XZ is shown T / 2. Each working double ply 21 consists at least partially of two radially superimposed working layers (211, 212) (cf. image 3 ). Each working layer (211, 212) comprises a textile reinforcement of the aliphatic polyamide type coated in an elastomeric material. The carcass reinforcement 4 comprises a radi...
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The invention relates to a tyre (1) for an airplane, which includes a tread (3), a working reinforcement (2) including at least one working bilayer (21) which has the largest axial width (LT) and includes two axial ends (E), a carcass reinforcement (4) including at least one carcass layer (41), and a binding reinforcement (7) including at least one binding layer (71), which is radially inside the working bilayer (21) and has an axial width (LF) which is at least 0.8 times the axial width (LT). The distance D between an axial end (E) of the working bilayer (21) and the orthogonal projection (I) thereof onto the radially outermost carcass layer (41) is at least 7 mm and the distance D' between the point (F) of the working bilayer (21), located axially inside the axial end (E) at a distance L of 25 mm, and the orthogonal projection (J) thereof onto the carcass layer (41) at least 4 mm and no greater than the distance D.
Description
technical field [0001] The present invention relates to aircraft tires and, in particular, to aircraft tire crown reinforcements. Background technique [0002] Hereinafter, the circumferential, axial and radial directions denote directions tangential to the tread surface of the tire, directions parallel to the rotational axis of the tire, and directions perpendicular to the rotational axis of the tire, respectively, in the rotational direction of the tire. "Radially inside or radially outside" means "closer to or farther from the axis of rotation of the tire", respectively. "Axially inboard or axially outboard" means "closer to or away from, respectively, the equatorial plane of the tire," which is the plane passing through the middle of the tire's tread surface and perpendicular to the tire's axis of rotation. [0003] In general, a tire comprises a tread intended to come into contact with the ground through a tread surface connected by two sidewalls to two beads intended ...
Claims
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Patent Timeline
Login to View More IPC IPC(8): B60C9/20B60C9/26B60C9/28
CPCB60C9/2009B60C9/263B60C9/28B60C2009/2032B60C2200/02B60C9/0007B60C9/0042B60C9/1807B60C2009/0021
InventorV·艾蒂安E·茹利纳
OwnerMICHELIN & CO CIE GEN DES ESTAB MICHELIN