CN101638037A - Meridian aircraft tyre - Google Patents
Meridian aircraft tyre Download PDFInfo
- Publication number
- CN101638037A CN101638037A CN200910114327A CN200910114327A CN101638037A CN 101638037 A CN101638037 A CN 101638037A CN 200910114327 A CN200910114327 A CN 200910114327A CN 200910114327 A CN200910114327 A CN 200910114327A CN 101638037 A CN101638037 A CN 101638037A
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- bracing ply
- carcass plies
- band bundle
- bundle carcass
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Abstract
The invention relates to a meridian aircraft tyre, in particular to a meridian aircraft tyre having a folding edge-belted layer structure. The meridian aircraft tyre comprises a belted layer formed bybonding at least one belted layer group. Curtain lines of the bundle layer and a tyre surface form an included angle of 10 DEG to 20 DEG in a circumferential direction, wherein the belted layer groupis formed by bonding three layers or four layers of belt curtain cloth layers. In the same group of belted layer group, both ends of the bottom belt curtain cloth layer are reversed upwards into turned edges; the turned edges cover both ends of other belt curtain cloth layers except the first belt curtain cloth layer in the belted layer group; the ends of the turned edges are respectively connected with both ends of the first belt curtain cloth layer; and connection positions are within the range of the belt curtain cloth layer or a tyre top layer above the first belt curtain cloth layer. Byadopting the meridian aircraft tyre with the belted layer structure, the bundle layer has good stability and can effectively avoid producing a peeled meridian aircraft tyre between the ends of the curtain lines and glue.
Description
Technical field
The present invention relates to a meridian aircraft tyre, be specifically related to have the meridian aviation tyre of folding bag limit belt structure.
Background technology
Meridian aviation tyre uses under pressure, the high-speed and big load condition in high, and the belt structure of existing meridian aviation tyre is provided with the multilayer carcass plies, to guarantee the intensity and the centrifugal force resistant of tire, satisfies the usage condition of meridian aviation tyre.In case the number of carcass plies is too much, when they fit together, because existing, the belt cord end blocks the termination freely, and the belt cord end is the severing mouth, because of truncated end head position stress concentration, under high-speed effect, easily produce between cord termination and the sizing material and peel off, cause the tire belt end to be destroyed.
Summary of the invention
The technical problem to be solved in the present invention provides a kind of belt structure good stability, can effectively prevent to produce between belt cord termination and the sizing material meridian aviation tyre of peeling off.
For achieving the above object, the present invention is by the following technical solutions:
One meridian aircraft tyre comprises bracing ply, and described bracing ply is fitted by at least one group of bracing ply group and formed, and the circumferential angle of belt cord and tyre surface is 10 °～20 °; Wherein,
Each bracing ply group is formed by three layers or quadriply belt bundle carcass building, in the same group of bracing ply group, the two ends of the orlop band bundle carcass plies reflexed that makes progress forms crimping, crimping encases the two ends of the band of other except that ground floor band bundle carcass plies bundle carcass plies in this group bracing ply group, the end of crimping joins with the two ends of ground floor band bundle carcass plies respectively, and interface is positioned at the band bundle carcass plies on this ground floor band bundle carcass plies or the coverage of crown layer.
Bracing ply is designed to said structure, because every layer of band bundle carcass plies or crown lamination of being with the termination of restrainting carcass plies all to be wrapped or being positioned on it lived, thereby can effectively prevent to peel off between cord termination and the sizing material generation of phenomenon, improve the stability of tire belt, and then improved the anti-high speed performance and the fatigue performance of tire.The circumferential angle of belt cord and tyre surface is designed to 10 °～20 °, can suppress the expansion of carcass on diametric(al) well and increase, and more helps raising speed.
In the said structure:
The circumferential angle of belt cord and tyre surface is preferably 12 °～17 °.
Adjacent two band bundle carcass pliess in the same bracing ply group, it is narrow to be positioned at the band bundle carcass plies that the width of the band bundle carcass plies on upper strata is positioned under it; In the two adjacent groups bracing ply group, it is narrow to be positioned at the bracing ply group that the width of the bracing ply group on upper strata is positioned under it.
Described band bundle carcass plies is made of aramid fiber/nylon composite cord.
Compared with prior art, every layer of band bundle carcass plies or crown lamination of being with the termination of restrainting carcass plies all to be wrapped or being positioned on it in the radial aviation tire belt of the present invention lived, thereby can effectively prevent to peel off between cord termination and the sizing material generation of phenomenon, improve the stability of tire belt, and then improved the anti-high speed performance and the fatigue performance of tire; Belt cord and the circumferential angle of tyre surface are designed to 10 °～20 °, also can suppress the expansion of carcass on diametric(al) well and increase, more help raising speed.
Description of drawings
Fig. 1 is the structural representation of radial aviation tire belt of the present invention;
Fig. 2 is the circumferential angle scheme drawing of belt cord and tyre surface.
Number in the figure is:
1, first group of bracing ply group; 2, second group of bracing ply group; 3, the 3rd group of bracing ply group; 4, band bundle carcass plies; 5, interface; 6 crimpings; 7 belt cords; W1, first group of bracing ply group fold the width behind the bound edge; W2, second group of bracing ply group fold the width behind the bound edge; W3, the 3rd group of bracing ply group fold the width behind the bound edge; The circumferential angle of α, belt cord and tyre surface.
The specific embodiment
Meridian aviation tyre of the present invention comprises bracing ply, and described bracing ply is fitted by at least one group of bracing ply group and formed, and belt cord 7 is 10 °～20 ° with the circumferential angle α of tyre surface, preferred 12 °～17 °; Wherein,
Described bracing ply group is fitted by three layers or quadriply belt bundle carcass plies 4 and is formed, in the same group of bracing ply group, the two ends of orlop band bundle carcass plies 4 reflexed that makes progress forms crimping 6, crimping 6 encases the two ends of the band of other except that ground floor band bundle carcass plies 4 bundle carcass plies 4 in this group bracing ply group, the end of crimping 6 joins with the two ends of ground floor band bundle carcass plies 4 respectively, and interface 5 places are positioned at the band bundle carcass plies 4 on this ground floor band bundle carcass plies 4 or the coverage of crown layer.
Adjacent two band bundle carcass pliess in same bracing ply group, it is narrow to be positioned at the band bundle carcass plies 4 that the width of the band bundle carcass plies 4 on upper strata is positioned under it; In the two adjacent groups bracing ply group, it is narrow to be positioned at the bracing ply group that the width of the bracing ply group on upper strata is positioned under it.
Described band bundle carcass plies preferably is made of aramid fiber/nylon composite cord.
Specifically the bracing ply with the meridian aviation tyre of 740 * 220R381 model is example explanation the present invention, and Fig. 1 is the structural representation of this model radial aviation tire belt.
Referring to Fig. 1, Fig. 2, the bracing ply of this model meridian aviation tyre is fitted by three groups of bracing ply groups and is formed, and belt cord 7 is 10 °～20 ° with the circumferential angle α of tyre surface; Whole bracing ply has 11 layers of band bundle carcass plies 4, this band bundle carcass plies 4 is made of aramid fiber/nylon composite cord, wherein, first group of bracing ply group 1 and second group of bracing ply group 2 are fitted by 4 layers of band bundle carcass plies 4 respectively and are formed, and the 3rd group of bracing ply group 3 fitted by 3 layers of band bundle carcass plies 4 and formed.
As shown in Figure 1, in first group of bracing ply group 1, the width minimum of the 1st layer of band bundle carcass plies 4, the width of the 2nd layer of band bundle carcass plies 4 is big slightly than the 1st layer, and the width of the 3rd layer of band bundle carcass plies 4 is big slightly than the 2nd layer, the width maximum of the 4th layer of band bundle carcass plies 4; The two ends that are positioned at undermost band bundle carcass plies 4 (promptly the 4th layer band bundle carcass plies) reflexed that makes progress forms crimping 6, crimping 6 encases the two ends of the 2nd and the 3rd layer of band bundle carcass plies 4 in this group bracing ply group, the end of crimping 6 respectively with this group bracing ply group in the two ends of the 1st layer of band bundle carcass plies 4 join, interface 5 places are arranged in the coverage of the 4th layer of band bundle carcass plies 4 of second group of bracing ply group 2, and the width W 1 behind described first group of bracing ply group, the 1 folding bound edge is 180～200 millimeters.Being sticked to form of above-mentioned second group of bracing ply group 2 and the 3rd group of bracing ply group 3 is similar to first group of bracing ply group, wherein the width W 2 behind second group of bracing ply group, the 2 folding bound edges is 160～180 millimeters, and the width W 3 behind the 3rd group of bracing ply group 3 folding bound edge is 140～160 millimeters.
Claims (4)
1, a meridian aircraft tyre comprises bracing ply, it is characterized in that: bracing ply is fitted by at least one group of bracing ply group and is formed, and belt cord (7) is 10 °～20 ° with the circumferential angle of tyre surface (α); Wherein,
Described bracing ply group is fitted by three layers or quadriply belt bundle carcass plies (4) and is formed, in the same group of bracing ply group, the two ends of orlop band bundle carcass plies (4) reflexed that makes progress forms crimping (6), crimping (6) encases the two ends of the band bundle carcass plies of other except that ground floor band bundle carcass plies (4) (4) in this group bracing ply group, the end of crimping (6) joins with the two ends of ground floor band bundle carcass plies (4) respectively, and interface (5) locates to be positioned at the band bundle carcass plies (4) on this ground floor band bundle carcass plies (4) or the coverage of crown layer.
2, meridian aviation tyre according to claim 1 is characterized in that: belt cord (7) is 12 °～17 ° with the circumferential angle of tyre surface (α).
3, meridian aviation tyre according to claim 1 is characterized in that: the adjacent two band bundle carcass pliess in the same bracing ply group, and it is narrow to be positioned at the band bundle carcass plies (4) that the width of the band bundle carcass plies (4) on upper strata is positioned under it; In the two adjacent groups bracing ply group, it is narrow to be positioned at the bracing ply group that the width of the bracing ply group on upper strata is positioned under it.
4, according to claim 1,2 or 3 described meridian aviation tyres, it is characterized in that: described band bundle carcass plies is made of aramid fiber/nylon composite cord.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910114327A CN101638037A (en) | 2009-08-22 | 2009-08-22 | Meridian aircraft tyre |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910114327A CN101638037A (en) | 2009-08-22 | 2009-08-22 | Meridian aircraft tyre |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101638037A true CN101638037A (en) | 2010-02-03 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910114327A Pending CN101638037A (en) | 2009-08-22 | 2009-08-22 | Meridian aircraft tyre |
Country Status (1)
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| CN (1) | CN101638037A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102029862A (en) * | 2010-12-02 | 2011-04-27 | 中橡集团曙光橡胶工业研究设计院 | Meridian line aircraft tire winding edge wrapping belt structure |
| CN111674071A (en) * | 2020-06-18 | 2020-09-18 | 青岛双星轮胎工业有限公司 | Meridian aircraft tire forming process |
| CN112406413A (en) * | 2020-12-17 | 2021-02-26 | 中国化工集团曙光橡胶工业研究设计院有限公司 | Radial aircraft tire belt ply structure resistant to high speed, high pressure and fatigue |
| CN113242802A (en) * | 2018-12-14 | 2021-08-10 | 株式会社普利司通 | Pneumatic tire |
-
2009
- 2009-08-22 CN CN200910114327A patent/CN101638037A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102029862A (en) * | 2010-12-02 | 2011-04-27 | 中橡集团曙光橡胶工业研究设计院 | Meridian line aircraft tire winding edge wrapping belt structure |
| CN113242802A (en) * | 2018-12-14 | 2021-08-10 | 株式会社普利司通 | Pneumatic tire |
| CN111674071A (en) * | 2020-06-18 | 2020-09-18 | 青岛双星轮胎工业有限公司 | Meridian aircraft tire forming process |
| CN111674071B (en) * | 2020-06-18 | 2022-01-25 | 青岛双星轮胎工业有限公司 | Meridian aircraft tire forming process |
| CN112406413A (en) * | 2020-12-17 | 2021-02-26 | 中国化工集团曙光橡胶工业研究设计院有限公司 | Radial aircraft tire belt ply structure resistant to high speed, high pressure and fatigue |
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Open date: 20100203 |