Bias tire for aircraft

Abstract

To provide an aircraft bias tire capable of suppressing damage to an electronic device disposed in the tire.SOLUTION: An aircraft bias tire of the present invention comprises a carcass made of two or more carcass plies toroidally extending between a pair of bead parts. The two or more carcass plies are formed of organic fiber cords coated with rubber, and the organic fiber cords extend between adjacent carcass plies in mutually opposite inclinations with respect to the tire equatorial plane. The aircraft bias tire is provided with an electronic component, the electronic component having one or more antennas, and the antennas extend at an inclination angle of 32-90° with respect to the tire width direction.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present invention relates to a bias tire for an aircraft. [Background technology]

[0002] Conventionally, electronic components have been placed in tires. For example, an RF (Radio Frequency) ID tag can be cited as such an electronic component, and tire management and the like can be performed by storing information in the RFID tag via wireless communication and reading the stored information (for example, Patent Document 1). [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Laid-Open No. 2011-178388 Summary of the Invention [Problem to be solved by the invention]

[0004] When an aircraft bias tire is equipped with an electronic device (especially an RFID tag having an antenna, etc.), the electronic device may be damaged.

[0005] An object of the present invention is to provide a bias tire for aircraft that can prevent damage to electronic devices disposed in the tire. [Means for solving the problem]

[0006] The gist and configuration of the present invention are as follows. (1) a pair of bead portions; a pair of sidewall portions connected to the pair of bead portions; a tread portion extending between the pair of sidewall portions; A bias tire for an aircraft comprising: a carcass consisting of two or more carcass plies toroidally spanning between the pair of bead portions, The two or more carcass plies are made of rubber-coated organic fiber cords, the organic fiber cords extend between adjacent carcass plies at an inclination in opposite directions relative to the tire equatorial plane, The bias tire for an aircraft includes an electronic component, the electronic component has one or more antennas; The bias tire for aircraft, wherein the antenna extends at an angle of 32 to 90° with respect to the tire width direction.

[0007] (2) The bias tire for aircraft according to (1), wherein the antenna extends at an angle of 40 to 90° with respect to the tire width direction.

[0008] (3) The bias tire for an aircraft according to (1) or (2), wherein the electronic components are disposed on the surface of the bias tire for an aircraft.

[0009] (4) The bias tire for an aircraft according to any one of (1) to (3), wherein at least a part of the electronic component is covered with a cover rubber.

[0010] (5) The bias tire for aircraft according to any one of (1) to (4), wherein the electronic component is arranged in a central region of the tread width in the tire width direction. Here, "the central region of the tread width in the tire width direction" refers to the central 40% region between the tread edges when an aircraft bias tire is mounted on an applicable rim, inflated to the specified internal pressure, and no load is applied. "Tread edge" refers to the outermost point in the tire width direction of the surface that comes into contact with the road surface when an aircraft bias tire is mounted on an applicable rim, inflated to the specified internal pressure, and subjected to the maximum load.

[0011] In this specification, the term "applicable rim" refers to the industrial standard that is valid in the region where the tire is produced and used, and in Japan, the JATMA YEAR standard of the Japan Automobile Tire Manufacturers Association (JATMA). It refers to the standard rim (Measuring Rim in the ETRTO Standards Manual, Design Rim in the TRA Year Book) for the applicable size that is described or will be described in the future in the STANDARDS MANUAL of the ETRTO (The European Tyre and Rim Technical Organization) in Europe, or the YEAR BOOK of the TRA (The Tire and Rim Association, Inc.) in the United States (i.e., the above "rim" includes not only current sizes but also sizes that may be included in the above industry standards in the future. An example of a "size to be described in the future" is the size described as "FUTURE DEVELOPMENTS" in the 2013 edition of the ETRTO), but in the case of a size not described in the above industry standards, it refers to a rim with a width that corresponds to the bead width of the tire. In addition, "specified internal pressure" refers to the air pressure (maximum air pressure) corresponding to the maximum load capacity of a single wheel for the applicable size and ply rating as specified in the above JATMA etc. For sizes not specified in the above industry standards, "specified internal pressure" refers to the air pressure (maximum air pressure) corresponding to the maximum load capacity specified for each vehicle on which the tire is mounted. In addition, "maximum load" refers to the load corresponding to the above maximum load capacity. [Effects of the Invention]

[0012] According to the present invention, it is possible to provide an aircraft bias tire that can prevent damage to electronic devices disposed in the tire. [Brief explanation of the drawings]

[0013] [Figure 1] 1 is a cross-sectional view in the tire width direction of an aircraft bias tire according to one embodiment of the present invention. [Figure 2] FIG. 10 is a diagram for explaining pantograph deformation. [Figure 3] 10A and 10B are diagrams for explaining a compressive force acting on an antenna of an electronic component. [Figure 4] FIG. 1 is a schematic plan view illustrating an example of an electronic component. [Figure 5] FIG. 2 is a schematic plan view showing the arrangement of electronic components. DETAILED DESCRIPTION OF THE INVENTION

[0014] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

[0015] Fig. 1 is a widthwise cross-sectional view of an aircraft bias tire according to one embodiment of the present invention. As shown in Fig. 1, this aircraft bias tire (hereinafter also simply referred to as "tire") 1 includes a pair of bead portions 2, a pair of sidewall portions 3 connected to the pair of bead portions 2, a tread portion 4 connected between the pair of sidewall portions 3, and a carcass 5 consisting of two or more carcass plies toroidally straddling the pair of bead portions 2. This tire is configured to function when inflated to an internal pressure of 145 psi or more when assembled on a rim.

[0016] In the illustrated example, three bead cores 2a to 2c are embedded in the bead portion 2. The number of bead cores is preferably set to correspond to the number of carcass plies, which is two or more.

[0017] In this example, the carcass 5 is made up of three carcass plies 5a to 5c. (a) is formed by rubber-coating organic fiber cords. The organic fiber cords are not particularly limited, but can be cords made of nylon, aramid, or the like. The organic fiber cords extend between adjacent carcass plies (between 5a and 5b and between 5b and 5c in the illustrated example) at an inclination in opposite directions (at the same angle with respect to the tire equatorial plane CL in this example) relative to the tire equatorial plane CL. As illustrated, carcass ply 5a has a carcass folded-up portion folded back around bead core 2a. Similarly, carcass ply 5b has a carcass folded-up portion folded back around bead core 2b, and carcass ply 5c has a carcass folded-up portion folded back around bead core 2c.

[0018] The tire 1 further includes an electronic component 6. In this example, the electronic component 6 is an RFID tag. In the illustrated example, the tire has the electronic component 6 disposed on the surface of the tire 1, more specifically, on the inner surface of an inner liner disposed on the inner surface of the tire. In the illustrated example, the electronic component 6 is disposed in a central region of the tread width in the tire width direction.

[0019] FIG. 4 is a schematic plan view showing an example of an electronic component (RFID tag) 6. As shown in FIG. 4, the electronic component (RFID tag) 6 has one or more antennas 6a, 6b (two in the illustrated example). The antennas 6a, 6b extend in a predetermined direction (linearly in the illustrated example). The antennas may also extend in a predetermined direction while bending in a wave-like manner, for example. The electronic component (RFID tag) 6 has a substrate 6c. An RFID chip and the like are built into the substrate 6c. Although not shown, the substrate 6c is preferably covered with an exterior body to protect the RFID chip and the like. At least a portion of the electronic component (RFID tag) 6 is preferably covered with a cover rubber in consideration of adhesion to tire rubber.

[0020] 5 is a schematic plan view showing the arrangement of electronic components (RFID tags) 6. Antennas 6a, 6b extend at an inclination angle of 32 to 90 degrees with respect to the tire width direction. It is more preferable that antennas 6a, 6b extend at an inclination angle of 40 to 90 degrees with respect to the tire width direction, and even more preferably that antennas 6a, 6b extend at an inclination angle of 90 degrees with respect to the tire width direction (i.e., extend without inclination with respect to the tire circumferential direction) as shown in the illustrated example. The effects of the aircraft bias tire of this embodiment will be described below.

[0021] The inventor investigated the causes of damage to electronic devices placed in aircraft bias tires and found that the compressive force caused by pantograph deformation of the carcass ply in aircraft bias tires, which are subject to high loads, can cause damage to the antenna. As shown in FIG. 2, when a tire is loaded, a tensile force is generated in the tire circumferential direction due to pantograph deformation, and when the tire internal pressure increases or the load is removed, a compressive force is generated in the tire width direction due to pantograph deformation. On the other hand, if the antenna extends in the tire width direction or extends at a small angle relative to the tire width direction, the compressive strain caused by the compressive force acts significantly on the antenna, causing damage such as breaking of the antenna, as shown in Fig. 3. This effect is particularly pronounced in aircraft tires, where the internal tire pressure is high and the load on the tire fluctuates greatly during takeoff and landing.

[0022] In contrast to this, in the aircraft bias tire 1 of this embodiment, the antennas 6a and 6b extend at an inclination angle of 32 to 90° with respect to the tire width direction. As a result, the extending direction of the antennas 6a, 6b is inclined with respect to the tire width direction, which is the direction in which the compressive force acts, and therefore the compressive strain acting on the antennas 6a, 6b can be reduced. As described above, according to the aircraft bias tire 1 of this embodiment, it is possible to prevent the electronic device 6 disposed in the tire from being damaged.

[0023] For the same reasons as above, it is more preferable that the antennas 6a, 6b extend at an inclination angle of 40 to 90 degrees with respect to the tire width direction, and it is even more preferable that they extend at an inclination angle of 90 degrees with respect to the tire width direction.

[0024] On the other hand, if the tensile force acts on the end of the cover rubber of the electronic component 6, it may cause the electronic component 6 to peel off from the surface of the tire 1. Therefore, in order to ensure adhesion of the electronic component 6 to the tire 1 when the electronic component 6 is disposed on the tire surface, the antennas 6a, 6b are preferably inclined at an angle of 32° or more and less than 90° with respect to the tire width direction, and more preferably at an angle of 32° or more and 85° or less.

[0025] The electronic components 6 are preferably disposed on the surface of the bias tire 1 for aircraft. By disposing the electronic components 6 away from the carcass ply, the compressive force is less likely to act on the electronic components 6, and damage to the electronic devices 6 can be further suppressed. On the other hand, in the present disclosure, the electronic components 6 can also be disposed inside the bias tire 1 for aircraft. In this case, the problem of the electronic components 6 peeling off from the surface of the tire 1 does not occur.

[0026] It is preferable that at least a part of the electronic component 6 is covered with a cover rubber, since this facilitates adhesion to the tire rubber.

[0027] The electronic components 6 are preferably disposed in the central region of the tread width in the tire width direction. This is because bias tires generally have a cross-sectional shape with a large curvature, and therefore the electronic components 6 have a stronger adhesiveness to the tire in the central region of the tread width in the tire width direction.

[0028] Although the embodiments of the present invention have been described above, the present invention is not limited to the above-described embodiments. For example, the tire 1 may be provided with one or more reinforcing layers, such as a breaker layer, on the tire radial outer side of the carcass 5. In this case, the cords of the reinforcing layers, such as the breaker layer, are preferably non-metallic (for example, organic fiber) in consideration of the communication properties of the electronic components 6. Examples of the present invention will be described below, but the present invention is not limited to the following examples in any way. [Example]

[0029] To verify the effectiveness of the present invention, a test was conducted to evaluate antenna durability for an RFID tag having two antennas, using examples and comparative examples in which the inclination angle of the antenna relative to the tire width direction was varied. The test conformed to TSO-C62. The tire size was H44.5 x 16.5-21, the specified load was 20,280 kgf, and the specified internal pressure was 1,480 kPa. Table 1 shows the test results. Note that the "inclination angle" in Table 1 refers to the inclination angle of the antenna relative to the tire width direction.

[0030] [Table 1]

[0031] As shown in Table 1, in both Comparative Examples 1 and 2, the antenna broke, but in both Invention Examples 1 and 2, no failure was observed in the antenna, and good durability was demonstrated. [Explanation of symbols]

[0032] 1: Aircraft bias tires (tires), 2: Bead part, 2a to 2c: bead core, 3: Sidewall part, 4: Tread part, 5: Carcass, 5a to 5c: carcass ply, 6: Electronic components (RFID tags), 6a, 6b: antenna, 6c: Substrate

Claims

1. a pair of bead portions; a pair of sidewall portions connected to the pair of bead portions; a tread portion extending between the pair of sidewall portions; A carcass consisting of two or more carcass plies toroidally spanning the pair of bead portions, The two or more carcass plies are made of rubber-coated organic fiber cords, the organic fiber cords extend between adjacent carcass plies at an inclination in opposite directions relative to the tire equatorial plane, The bias tire for aircraft includes an electronic component, the electronic component has one or more antennas; The bias tire for aircraft is characterized in that the antenna extends at an inclination angle of 32 to 90 degrees with respect to the tire width direction.

2. 2. The bias tire for aircraft according to claim 1, wherein the antenna extends at an inclination angle of 40 to 90 degrees with respect to the tire width direction.

3. The bias tire for an aircraft according to claim 1 or 2, wherein the electronic components are disposed on a surface of the bias tire for an aircraft.

4. 3. The bias tire for an aircraft according to claim 1, wherein at least a part of the electronic component is covered with a cover rubber.

5. The bias tire for aircraft according to claim 1 or 2, wherein the electronic component is disposed in a central region in the tire width direction of the tread portion.

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