CN212373076U - Aircraft tire structure capable of solving problem of thread exposure in tire - Google Patents
Aircraft tire structure capable of solving problem of thread exposure in tire Download PDFInfo
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- CN212373076U CN212373076U CN202021566598.8U CN202021566598U CN212373076U CN 212373076 U CN212373076 U CN 212373076U CN 202021566598 U CN202021566598 U CN 202021566598U CN 212373076 U CN212373076 U CN 212373076U
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- 230000007704 transition Effects 0.000 claims abstract description 14
- 239000011324 bead Substances 0.000 claims abstract description 11
- 239000011248 coating agent Substances 0.000 claims 1
- 238000000576 coating method Methods 0.000 claims 1
- 238000004073 vulcanization Methods 0.000 abstract description 8
- 239000003292 glue Substances 0.000 abstract 1
- 238000007759 kiss coating Methods 0.000 abstract 1
- 239000011159 matrix material Substances 0.000 abstract 1
- 239000004744 fabric Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 210000001161 mammalian embryo Anatomy 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 230000020169 heat generation Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
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Abstract
The utility model discloses an aviation tire structure that can solve the line problem that exposes in the child, aviation tire's specification is 1050X 400 type, tire section profile structure comprises several circular arcs, and the centre of a circle of the tire crown portion circular arc of tire is located tire section central line, and the centre of a circle of side wall portion circular arc is located tire section central horizontal axis, constitute between each circular arc of tire section and with the tire bead between slick and sly transition. The utility model discloses a special domes's outline design, the matrix ply is 1.2-1.4 mm's kiss-coating thickness, and the airtight layer is glued thickness and is 2.0-2.5mm to solve the tire child that the aircraft tire of 1050X 400 type specification appears in the vulcanization process and expose the line and the technological problem of scarce glue.
Description
Technical Field
The utility model relates to an aircraft tire technical field specifically is an aircraft tire structure that can solve the interior thread exposure problem of child.
Background
The model of the model 1050X 400 aviation tire belongs to a low-pressure and high-load aviation tire, the model outer contour dimension of the tire is designed in a table 1, wherein the standard values of the inflation outer diameter and the inflation section width are from GJB 684A-98 military aviation tire series.
TABLE 1 tire model outer contour dimensions
| Name (R) | Code number | Unit of | Size of model | Inflated size | Standard of merit |
| Outside diameter | D | mm | 985 | 1008 | 998～1018 |
| Width of cross section | B | mm | 363 | 384 | 378～390 |
| High section | H | mm | 308.0 | 318.75 | |
| Adhesion diameter | d | mm | 369.0 | 370.5 | |
| Diameter of wheel rim | DF | mm | / | 440 | |
| Width of the heel | C | mm | 295 | 295 |
As can be seen from Table 1, the outer profile of the tire is designed to be special, the outer diameter D of the tire is large (985mm), the adhesion diameter D is small (369mm), and in the tire forming process, in order to ensure that the tire can be taken out of the tire blank after the forming head is folded, the head diameter Dc must be designed to be 538mm, and the width thereof must be designed to be 805mm (the diameter of the cord fabric tube is small and the width thereof is large). Wherein:
D1＝Dc/δc＝538/1.035＝520(mm)
δ＝Dk/D1＝938/520＝1.804(mm)
in the formula: Dc-Molding nose diameter;
delta-total stretch of the cord fabric;
Dkmodel tire inside diameter (model outside diameter D-2X tire crown thickness T)C)；
D1-a semi-finished first inner diameter of the cloth tube;
δc-head stretching of the cord cylinder.
The design of the machine head leads the total stretch delta of the cord fabric of the tire blank in the vulcanization process to be as high as 1.804, which greatly exceeds the design range of 1.3-1.4, and the problems of line exposure and rubber shortage in the tire blank are easily caused during the vulcanization of the tire blank. Therefore, it is necessary to design and develop a special tire structure to solve the above-mentioned process problems.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an aircraft tire structure that can solve the tire lining and reveal the line problem to the tire lining that appears when the aircraft tire of solution 1050X 400 type specification vulcanizes reveals the line, lacks gluey problem.
Realize the utility model discloses the technical scheme of purpose is:
the aviation tire structure capable of solving the problem of tire cavity exposure is characterized in that the aviation tire is 1050 multiplied by 400 in specification, the tire section outline structure is composed of a plurality of arcs, the center of a tire crown part arc of the tire is located on the tire section central line, the center of a tire sidewall part arc is located on a tire section central horizontal shaft, and the arcs forming the tire section and the tire bead are in smooth transition, wherein the aviation tire structure is different from the prior art in that the outer diameter of the 1050 multiplied by 400 aviation tire is 985 +/-5 mm, the section width is 363 +/-3 mm, the bonding diameter is 369mm, and the bonding width is 295 mm;
the radius of the arc R1 of the tire crown part of the tire is 300 +/-10 mm, the center of the arc R1 is positioned on the center line of the section of the tire, and the arc length is 140 +/-5 mm;
the radius of the circular arc R3 of the tire side part is 205 +/-5 mm, the center of the circular arc R3 is positioned on the horizontal axis of the center of the tire section, and the arc length is 70 +/-3 mm;
the crown part and the sidewall part are in smooth transition connection by an arc R2 with the radius of 125 +/-5 mm, and the arc length is 95 +/-4 mm;
the tyre side part and the tyre bead are in smooth transition connection by an arc R4 with the radius of 235 plus or minus 5mm, and the arc length is 125 plus or minus 5 mm;
the design of the carcass ply is 1.2-1.4mm of rubberizing thickness, which can effectively avoid the phenomenon that the carcass ply is coated with rubber and becomes thin due to the excessive stretching of the tire blank, effectively reduce the friction between plies, reduce the shearing heat generation between layers and improve the durability of the tire.
The thickness of the inner liner rubber is designed to be 2.0-2.5mm, the problems of line exposure and rubber shortage in the tire inner tube caused by large stretching in the tire vulcanization process can be directly and effectively reduced, but the problems of uneven thickness of the inner liner at the tire crown part, the tire side part and the tire bead part are easy to occur.
Therefore, the optimal scheme for solving the problems of thread exposure and rubber shortage in the tire can be found by matching the reasonable design.
The utility model discloses a special domes's outline design, the tire child embryo more evenly stretches in the vulcanization process, can avoid the child embryo part to stretch too big and lead to the child in to reveal the line, lack gluey problem effectively.
The advantage of this structure: through trial production and test verification of tires, the problems of tire liner exposure and rubber shortage in the vulcanization process of 1050X 400 type aircraft tires are solved, the product quality is guaranteed, the product percent of pass is improved, and the production efficiency is improved.
Drawings
FIG. 1 is a schematic cross-sectional view of an aircraft tire arch according to an embodiment of the invention to solve the problem of tire cords;
FIG. 2 is a schematic diagram of material distribution of an arch structure of an aircraft tire in an embodiment, wherein part A is a finished tire material distribution diagram, and part B is a semi-finished tire material distribution diagram;
FIG. 3 is an enlarged view of portion C of FIG. 2;
fig. 4 is an enlarged view of a portion D in fig. 2.
In the figure, 1, a tire crown part 2, a tire side part 3, a tire bead 4, a section center line 5, a section center horizontal axis 6, a tire body ply 7 and an inner liner rubber.
Detailed Description
The present invention will be further described with reference to the following examples and drawings, it being understood that the examples described are only some, but not all, of the examples of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Example (b):
as shown in figure 1, the aviation tire structure capable of solving the problem of tire tread exposure is characterized in that the aviation tire has a specification of 1050 x 400 type, the tire section contour structure consists of a plurality of arcs, the center of the arc of the tire crown part 1 of the tire is positioned on the center line of the tire section, the center of the arc of the tire sidewall part 2 is positioned on the horizontal axis of the center of the tire section, the arcs forming the tire section are in smooth transition with each other and the tire bead 3,
the outer diameter of the 1050X 400 type aircraft tire is 985 +/-5 mm, the section width is 363 +/-3 mm, the adhesion diameter is 369mm, and the adhesion width is 295 mm;
the radius of the circular arc R1 of the tire crown part 1 is 300 +/-10 mm, the center of the circular arc R1 is positioned on the center line 4 of the section of the tire, and the arc length of the circular arc R1 is 140 +/-5 mm;
the radius of the arc R3 of the sidewall 2 is 205 +/-5 mm, the center of the arc R3 is positioned on the horizontal axis 5 at the center of the section of the tire, and the arc length of the arc R3 is 70 +/-3 mm;
the crown part 1 and the sidewall part 2 are in smooth transition connection by an arc R2 with the radius of 125 +/-5 mm, and the arc length of the arc R2 is 95 +/-4 mm;
the tyre side part 2 and the tyre bead 3 are in smooth transition connection by an arc R4 with the radius of 235 plus or minus 5mm, and the arc length of the arc R4 is 125 plus or minus 5 mm;
the reasonable design of the circular arcs R1, R2, R3 and R4 ensures that the green tire is stretched more uniformly in the vulcanization process, and can effectively avoid the problems of line exposure and rubber shortage in the tire due to over-large local stretching of the green tire.
The aircraft tire model 1050 x 400 has the material distribution characteristics shown in fig. 2-4, with a carcass ply 6 adjacent the outside of the tire and an innerliner 7 adjacent the inside.
The rubberizing thickness of the tire body ply 6 is 1.2-1.4 mm;
the thickness of the tire inner liner rubber 7 is 2.0-2.5 mm.
Specifically, the outer diameter of the tire is 985mm, the section width is 363mm, the adhesion diameter is 369mm, and the adhesion width is 295 mm;
the radius of the arc R1 of the tire crown part of the tire is 300mm, the center of the arc R1 is positioned on the center line of the section of the tire, and the arc length is 140 mm;
the radius of the circular arc R3 of the tire side part is 205mm, the center of the circular arc R3 is positioned on the horizontal axis of the center of the tire section, and the arc length is 70 mm;
the crown part and the sidewall part are in smooth transition connection by an arc R2 with the radius of 125mm, and the arc length is 95 mm;
the tyre side part and the tyre bead are in smooth transition connection by an arc R4 with the radius of 235mm, and the arc length is 125 mm;
the rubberizing thickness of the tire body ply 6 is 1.3 mm;
the thickness of the tire inner liner rubber 7 is 2.3 mm.
Multiple trial production and test verification of 1050X 400 type tires prove that the design of the outer contour of the special arch structure, the rubberizing thickness of the carcass ply and the thickness of the inner liner rubber can effectively solve the vulcanization process problems of tire liner exposure and rubber shortage.
Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art will understand that the present invention can be modified or replaced with other embodiments without departing from the spirit and scope of the present invention, which should be construed as limited only by the appended claims.
Claims (2)
1. An aviation tire structure capable of solving the problem of thread exposure in a tire, wherein the aviation tire is 1050 multiplied by 400 in specification, the tire section outline structure consists of a plurality of arcs, the center of a tire crown part arc of the tire is positioned on the center line of the tire section, the center of a tire sidewall part arc is positioned on a horizontal axis of the center of the tire section, and the arcs forming the tire section and the tire bead are in smooth transition, and the aviation tire structure is characterized in that the outer diameter of the 1050 multiplied by 400 aviation tire is 985 +/-5 mm, the section width is 363 +/-3 mm, the close diameter is 369mm, and the close width is 295 mm;
the radius of the arc R1 of the tire crown part of the tire is 300 +/-10 mm, the center of the arc R1 is positioned on the center line of the section of the tire, and the arc length is 140 +/-5 mm;
the radius of the circular arc R3 of the tire side part is 205 +/-5 mm, the center of the circular arc R3 is positioned on the horizontal axis of the center of the tire section, and the arc length is 70 +/-3 mm;
the crown part and the sidewall part are in smooth transition connection by an arc R2 with the radius of 125 +/-5 mm, and the arc length is 95 +/-4 mm;
the tyre side part and the tyre bead are in smooth transition connection by an arc R4 with the radius of 235 plus or minus 5mm, and the arc length is 125 plus or minus 5 mm;
the skim coating thickness of the tire body ply is 1.2-1.4 mm;
the thickness of the tire inner liner rubber is 2.0-2.5 mm.
2. An aircraft tire structure capable of solving the problem of thread exposure in the tire as in claim 1, wherein the tire has an outer diameter of 985mm, a section width of 363mm, a junction diameter of 369mm, and a junction width of 295 mm;
the radius of the arc R1 of the tire crown part of the tire is 300mm, the center of the arc R1 is positioned on the center line of the section of the tire, and the arc length is 140 mm;
the radius of the circular arc R3 of the tire side part is 205mm, the center of the circular arc R3 is positioned on the horizontal axis of the center of the tire section, and the arc length is 70 mm;
the crown part and the sidewall part are in smooth transition connection by an arc R2 with the radius of 125mm, and the arc length is 95 mm;
the tyre side part and the tyre bead are in smooth transition connection by an arc R4 with the radius of 235mm, and the arc length is 125 mm;
the rubberizing thickness of the tire body ply is 1.3 mm;
the thickness of the tire inner liner rubber is 2.3 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021566598.8U CN212373076U (en) | 2020-07-31 | 2020-07-31 | Aircraft tire structure capable of solving problem of thread exposure in tire |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021566598.8U CN212373076U (en) | 2020-07-31 | 2020-07-31 | Aircraft tire structure capable of solving problem of thread exposure in tire |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212373076U true CN212373076U (en) | 2021-01-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021566598.8U Withdrawn - After Issue CN212373076U (en) | 2020-07-31 | 2020-07-31 | Aircraft tire structure capable of solving problem of thread exposure in tire |
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| CN (1) | CN212373076U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111746200A (en) * | 2020-07-31 | 2020-10-09 | 中国化工集团曙光橡胶工业研究设计院有限公司 | Aircraft tire structure capable of solving problem of thread exposure in tire |
| CN111746200B (en) * | 2020-07-31 | 2024-06-28 | 中国化工集团曙光橡胶工业研究设计院有限公司 | Aviation tire structure capable of solving problem of tire liner exposed line |
-
2020
- 2020-07-31 CN CN202021566598.8U patent/CN212373076U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111746200A (en) * | 2020-07-31 | 2020-10-09 | 中国化工集团曙光橡胶工业研究设计院有限公司 | Aircraft tire structure capable of solving problem of thread exposure in tire |
| CN111746200B (en) * | 2020-07-31 | 2024-06-28 | 中国化工集团曙光橡胶工业研究设计院有限公司 | Aviation tire structure capable of solving problem of tire liner exposed line |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20210119 Effective date of abandoning: 20240628 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20210119 Effective date of abandoning: 20240628 |