Meridian aircraft tire bead structure for large sink

Abstract

The present application relates to the technical field of meridian aviation tire, in particular to a meridian aviation tire bead structure for large deflection, which comprises a circular cross-section steel ring, a triangular cross-section filler, a body ply and a body material layer, wherein the triangular cross-section filler is further divided into an inner filler part and an outer filler part, the dividing line between the inner filler part and the outer filler part of the triangular cross-section filler is a line segment L, and the line segment L is tangent to the outermost point of the circular cross-section of the circular cross-section steel ring in the horizontal direction. The present application can solve the problem of delamination and bulging of the bead position of the meridian aviation tire with large deflection, meet the use requirements of the meridian aviation tire, optimize the bead structure, improve the performance and reliability of the aviation tire, reduce the maintenance cost and use risk of the tire, and provide strong guarantee for aviation safety.

Description

Technical Field

[0001] The invention relates to the technical field of radial aircraft tires, in particular to a bead structure of a radial aircraft tire with large subsidence. Background Art

[0002] Aircraft tires are critical aircraft components, demanding the ability to withstand high internal pressures, high loads, high speeds, and extreme impact loads. Due to their structural characteristics, radial aircraft tires experience approximately 30% sidewall deformation and sinking when carrying heavy loads. This significant sinking causes the bead to undergo passive deformation. When sinking reaches 32%, the rubber in the bead generates heat due to its inherent viscoelastic properties, leading to a temperature increase. This process is repeated during tire rotation, resulting in extremely high temperatures in the bead area. High temperatures, coupled with repeated flexing deformation, significantly reduce the life of the bead material and can easily create gaps at the interface between the carcass ply and adjacent bead material. This can lead to severe delamination and bulging, which can compromise carcass strength and potentially cause explosion.

[0003] Therefore, in order to meet the harsh operating conditions, improving the durability of the tire bead is an important research direction for aviation tires. Summary of the Invention

[0004] In view of the above problems, an object of the present invention is to provide a radial aircraft tire bead structure for large subsidence.

[0005] The object of the present invention is achieved through the following technical solutions:

[0006] A bead structure for a radial aircraft tire with a large amount of subsidence, comprising a circular-section steel rim, a triangular-section filling rubber, a carcass ply, and a carcass material layer. The carcass ply is coated on the outside of the integral structure formed by the circular-section steel rim and the triangular-section filling rubber. The carcass material layer is divided into a bead protection rubber layer and a support rubber layer, which are respectively located on the outside of the carcass ply. The bead protection rubber layer is used to connect with the rim of the corresponding radial aircraft tire. The support rubber layer is located on a side of the carcass ply that is adjacent to a wheel flange of the corresponding radial aircraft tire.

[0007] The triangular cross-section filling glue is divided into an inner filling glue part and an outer filling glue part that are connected to each other. The dividing line segment in the cross section between the inner filling glue part of the triangular cross-section filling glue and the outer filling glue part of the triangular cross-section filling glue is line segment L, and the line segment L is tangent to the outermost point of the circular cross-section of the circular cross-section steel ring in the horizontal direction.

[0008] The highest point of the inner filling glue portion of the triangular cross-section filling glue in the vertical direction is point A, and point A is located on the line segment L;

[0009] The outermost endpoint of an adjacent wheel flange of the corresponding radial aircraft tire is point X, the boundary point between the wheel flange of the wheel flange and the wheel flange itself is point O, and a projection arc S is drawn around point X with a line segment connecting point X and point O as a radius. The height position of point A is no higher than the height position of the intersection of the projection arc S and the straight line on which the line segment L is located.

[0010] The intersection of a straight line parallel to the horizontal plane passing through point A and the outer side surface of the carcass material layer is point C. The horizontal distance between point C and point A is 1-1.5 times the radius of the circular cross-section of the circular cross-section steel ring.

[0011] The intersection of the side surface of the supporting rubber layer close to the carcass cord layer and the projection arc S is point B. The thickness of the upper part of the carcass material layer located at an adjacent wheel flange of the rim of the corresponding radial aircraft tire measured through point B is 0.5-1 times the radius of the circular cross-section of the circular cross-section steel ring.

[0012] The thickness of the carcass material layer at the upper side of an adjacent wheel flange of the corresponding radial aircraft tire measured through point B is equal to the length of the line segment connecting point B and point C.

[0013] The bead protection rubber layer has an extending portion extending to the outer side of the supporting rubber layer.

[0014] The height position of the lowest point of the inner layer filling rubber part of the triangular cross-section filling rubber in the vertical direction is not lower than the height position of the outermost point of the circular cross-section of the circular cross-section steel ring in the horizontal direction.

[0015] Adhesive is provided between the triangular cross-section filling glue as a whole and the circular cross-section steel ring.

[0016] The elastic modulus of the inner filling rubber portion of the triangular cross-section filling rubber, the elastic modulus of the outer filling rubber portion of the triangular cross-section filling rubber, the elastic modulus of the carcass ply, and the elastic modulus of the supporting rubber layer decrease in sequence;

[0017] The Shore A hardness of the inner filling rubber part of the triangular cross-section filling rubber, the Shore A hardness of the outer filling rubber part of the triangular cross-section filling rubber, the Shore A hardness of the carcass cord layer and the Shore A hardness of the support rubber layer decrease in sequence.

[0018] The Shore A hardness of the inner filling rubber portion of the triangular cross-section filling rubber is 75-85 degrees, and the Shore A hardness of the outer filling rubber portion of the triangular cross-section filling rubber is 69-75 degrees.

[0019] The advantages and positive effects of the present invention are:

[0020] The bead structure for radial aircraft tires with large subsidence proposed in the present invention can solve the problems of delamination and bulging easily occurring at the bead position of radial aircraft tires with large subsidence, meet the use requirements of radial aircraft tires, optimize the bead structure, improve the performance and reliability of aircraft tires, reduce the maintenance cost and use risk of tires, and provide strong protection for aviation safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 The diagram is a partial cross-sectional structural diagram of a radial aircraft tire corresponding to the present invention.

[0022] In the figure: 1 is a circular cross-section steel ring, 2 is a triangular cross-section filling rubber, 201 is an inner filling rubber part, 202 is an outer filling rubber part, 3 is a carcass cord layer, 4 is a carcass material layer, 401 is a bead protective rubber layer, and 402 is a supporting rubber layer;

[0023] 001 is the rim and 0011 is the flange. DETAILED DESCRIPTION

[0024] The following is combined with Figure 1 The present invention is described in further detail.

[0025] A radial aircraft tire bead structure for large sinkage, such as Figure 1 As shown, this embodiment includes a circular-section steel rim 1, a triangular-section filling rubber 2, a carcass ply 3, and a carcass material layer 4. The carcass ply 3 is coated on the outside of the integral structure formed by the circular-section steel rim 1 and the triangular-section filling rubber 2. The carcass material layer 4 is divided into a bead protection rubber layer 401 and a support rubber layer 402. The bead protection rubber layer 401 and the support rubber layer 402 are respectively located on the outside of the carcass ply 3. The bead protection rubber layer 401 is used to connect with the rim 001 of the corresponding radial aircraft tire. The support rubber layer 402 is located on a side of the carcass ply 3 adjacent to a wheel flange 0011 of the corresponding radial aircraft tire rim 001. The basic arrangement of the circular-section steel rim 1, the triangular-section filling rubber 2, the carcass ply 3, the carcass material layer 4, and the rim 001 in this embodiment is based on the prior art.

[0026] In the radial aircraft tire bead structure for large subsidence proposed by the present invention, the triangular cross-section filler 2 is divided into an inner filler portion 201 and an outer filler portion 202, which are connected to each other. The dividing line segment between the inner filler portion 201 of the triangular cross-section filler 2 and the outer filler portion 202 of the triangular cross-section filler 2 in the cross section is a line segment L. The line segment L and the outermost point of the circular cross section of the circular cross section of the steel rim 1 in the horizontal direction are aligned. Figure 1The line segment L is tangent to the horizontal plane at point E in the figure.

[0027] Specifically, in this embodiment, the highest point of the inner filling glue portion 201 of the triangular cross-section filling glue 2 in the vertical direction is point A, and point A is located on the line segment L.

[0028] The outermost endpoint of an adjacent rim 0011 of the corresponding radial aircraft tire rim 001 is point X, the boundary point between the rim 0011 of the rim 001 and the rim 001 itself is point O, and a projection arc S is drawn around point X with the line segment connecting point X and point O as the radius.

[0029] In this embodiment, the height of point A is no higher than the intersection of the projected arc S and the line segment L. In this embodiment, the vertical lowest point of the inner layer of the filler 201 of the triangular cross-section filler 2 is no lower than the horizontal outermost point (point E) of the circular cross-section of the steel rim 1.

[0030] In this embodiment, the intersection of a straight line parallel to the horizontal plane passing through point A and the outer side surface of the carcass material layer 4 is point C. The horizontal distance d1 between point C and point A is 1-1.5 times the radius R of the circular cross-section of the circular cross-section steel ring 1.

[0031] The intersection of the side surface of the supporting rubber layer 402 adjacent to the carcass cord layer 3 and the projected arc S is point B. The thickness d2 of the carcass material layer 4 located above a flange 0011 adjacent to the rim 001 of the corresponding radial aircraft tire, as measured through point B, is 0.5-1 times the radius R of the circular cross-section of the circular-section steel rim 1. In this embodiment, the thickness d2 of the carcass material layer 4 located above a flange 0011 adjacent to the rim 001 of the corresponding radial aircraft tire, as measured through point B, is exactly equal to the length of the line segment connecting points B and C, facilitating design and testing. For different tires, the length of the line segment connecting points B and C may differ from the aforementioned thickness d2. In this embodiment, the bead guard rubber layer 401 has an extension portion extending to the outside of the supporting rubber layer 402. Therefore, the thickness d2 mentioned above includes the thickness of the portion of the supporting rubber layer 402 passing through point B and the thickness of the corresponding extension portion extending to the outside of the supporting rubber layer 402. For different tires, the bead guard rubber layer 401 may not have an extension portion extending to the outside of the supporting rubber layer 402. In this case, the thickness d2 mentioned above only includes the thickness of the portion of the supporting rubber layer 402 passing through point B.

[0032] Specifically, in this embodiment, an adhesive is provided between the entire triangular-section filling adhesive 2 and the circular-section steel ring 1 to strengthen the connection between the entire triangular-section filling adhesive 2 and the circular-section steel ring 1. The adhesive formulation in this embodiment can be based on existing technologies, with one end of the adhesive molecule containing a polar group that physically adheres to the circular-section steel ring 1, and the other end containing a non-polar group that covalently bonds with the rubber. The elastic modulus of the adhesive is between that of the circular-section steel ring 1 and the triangular-section filling adhesive 2, thereby reducing stress concentration when subjected to force.

[0033] Specifically, in this embodiment, the elastic modulus of the inner filler portion 201 of the triangular cross-section filler 2, the elastic modulus of the outer filler portion 202 of the triangular cross-section filler 2, the elastic modulus of the carcass ply 3, and the elastic modulus of the support rubber layer 402 decrease in sequence. The Shore A hardness of the inner filler portion 201 of the triangular cross-section filler 2, the Shore A hardness of the outer filler portion 202 of the triangular cross-section filler 2, the Shore A hardness of the carcass ply 3, and the support rubber layer 402 decreases in sequence. The Shore A hardness of the inner filler portion 201 of the triangular cross-section filler 2 is 75-85 degrees, and the Shore A hardness of the outer filler portion 202 of the triangular cross-section filler 2 is 69-75 degrees.

[0034] In a specific comparative experimental example, a tire with a triangular cross-section filler 2 formed as a single piece was subjected to a CTSO-C62e dynamic test. The tire completed 61 dynamic simulation tests, including 47 normal takeoff tests, 3 long-distance takeoff tests, 8 normal taxiing tests, 2 overload taxiing tests, and 1 overload takeoff test. After the 31st normal takeoff test, the tire bead eventually cracked due to delamination and bulging. However, a tire using the triangular cross-section filler 2 proposed in the present invention, which is divided into an inner filler layer 201 and an outer filler layer 202, remained intact after the same test conditions. The experiments show that the tire bead structure for radial aircraft tires with high subsidence can solve the problem of delamination and bulging in the bead of radial aircraft tires with high subsidence, and can meet the requirements of radial aircraft tires.

Claims

1. A bead structure for a radial aircraft tire with a large amount of subsidence, comprising a round-section steel ring (1), a triangular-section filling rubber (2), a carcass cord layer (3), and a carcass material layer (4), wherein the carcass cord layer (3) is coated on the outer side of a whole formed by the round-section steel ring (1) and the triangular-section filling rubber (2), and the carcass material layer (4) is divided into a bead protection rubber layer (401) and a supporting rubber layer (402) connected to each other, the bead protection rubber layer (401) and the supporting rubber layer (402) being respectively located on the outer side of the carcass cord layer (3), the bead protection rubber layer (401) being used to connect with the rim (001) of the corresponding radial aircraft tire, and the supporting rubber layer (402) being located on a side of the carcass cord layer (3) adjacent to a wheel flange (0011) of the corresponding radial aircraft tire; The bead structure of the radial aircraft tire for large subsidence is characterized in that: the triangular cross-section filling rubber (2) is divided into an inner filling rubber portion (201) and an outer filling rubber portion (202) connected to each other, the dividing line segment between the inner filling rubber portion (201) of the triangular cross-section filling rubber (2) and the outer filling rubber portion (202) of the triangular cross-section filling rubber (2) in the cross section is a line segment L, the line segment L is tangent to the outermost point of the circular cross section of the circular cross section steel ring (1) in the horizontal direction, and the line segment L is perpendicular to the horizontal plane; The highest point of the inner filling glue portion (201) of the triangular cross-section filling glue (2) in the vertical direction is point A, and point A is located on the line segment L; The outermost end point of an adjacent wheel flange (0011) of the rim (001) of the corresponding radial aircraft tire is point X, the boundary point between the wheel flange (0011) of the rim (001) and the rim (001) itself is point O, the X point is projected around the O point with a line segment connecting the X point and the O point as a radius to form an arc S, and the height position of the A point is not higher than the height position of the intersection of the projection arc S and the straight line where the line segment L is located.

2. The radial aircraft tire bead structure for large subsidence according to claim 1, characterized in that: The intersection of a straight line drawn through point A and parallel to the horizontal plane and the outer side surface of the carcass material layer (4) is point C, and the horizontal distance between point C and point A is 1-1.5 times the radius of the circular cross-section of the circular cross-section steel ring (1).

3. The radial aircraft tire bead structure for large subsidence according to claim 2, characterized in that: The intersection of the side surface of the supporting rubber layer (402) close to the carcass cord layer (3) and the projection arc S is point B, and the thickness of the upper side portion of the carcass material layer (4) located at an adjacent wheel flange (0011) of the rim (001) of the corresponding radial aircraft tire measured through point B is 0.5-1 times the radius of the circular cross-section of the circular cross-section steel ring (1).

4. The radial aircraft tire bead structure for large subsidence according to claim 3, characterized in that: The thickness of the upper portion of the carcass material layer (4) located at an adjacent wheel flange (0011) of the rim (001) of the corresponding radial aircraft tire measured through point B is equal to the length of the line segment connecting point B and point C.

5. The radial aircraft tire bead structure for large subsidence according to claim 1, characterized in that: The bead protection rubber layer (401) has an extension portion extending to the outside of the supporting rubber layer (402).

6. The radial aircraft tire bead structure for large subsidence according to claim 1, characterized in that: The height position of the lowest point of the inner filling rubber portion (201) of the triangular cross-section filling rubber (2) in the vertical direction is not lower than the height position of the outermost point of the circular cross-section of the circular cross-section steel ring (1) in the horizontal direction.

7. The radial aircraft tire bead structure for large subsidence according to claim 1, characterized in that: An adhesive is provided between the entire triangular cross-section filling glue (2) and the circular cross-section steel ring (1).

8. The radial aircraft tire bead structure for large subsidence according to claim 1, characterized in that: The elastic modulus of the inner filling rubber portion (201) of the triangular cross-section filling rubber (2), the elastic modulus of the outer filling rubber portion (202) of the triangular cross-section filling rubber (2), the elastic modulus of the carcass cord layer (3), and the elastic modulus of the supporting rubber layer (402) decrease in sequence; The Shore A hardness of the inner filling rubber portion (201) of the triangular cross-section filling rubber (2), the Shore A hardness of the outer filling rubber portion (202) of the triangular cross-section filling rubber (2), the Shore A hardness of the carcass cord layer (3), and the Shore A hardness of the supporting rubber layer (402) decrease in sequence.

9. The radial aircraft tire bead structure for large subsidence according to claim 8, characterized in that: The Shore A hardness of the inner filling rubber portion (201) of the triangular cross-section filling rubber (2) is 75-85 degrees, and the Shore A hardness of the outer filling rubber portion (202) of the triangular cross-section filling rubber (2) is 69-75 degrees.

Images