CN212194954U - Skew aircraft tire structure for dealing with short-time impact load - Google Patents
Skew aircraft tire structure for dealing with short-time impact load Download PDFInfo
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- CN212194954U CN212194954U CN201922416199.7U CN201922416199U CN212194954U CN 212194954 U CN212194954 U CN 212194954U CN 201922416199 U CN201922416199 U CN 201922416199U CN 212194954 U CN212194954 U CN 212194954U
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Abstract
The utility model discloses a diagonal aircraft tire structure for dealing with short-time impact load, which comprises a tire bead, a reverse cladding cord fabric, a ring core rubber sheet, a steel wire ring, a forward cladding cord fabric, a tire bead wrapping cloth, a hard rubber sheet, a central line and a bead filler; different from the structure of the existing skew aviation tire: the high-strength nylon cord is used, and 2-12 layers of turn-up cord fabric layers which turn up and pass through the steel ring part are arranged; arranging the ends of the turn-up cord fabric layers which are turned up and down on the tire center line 15-16mm in a step shape from top to bottom by a difference level of 5-15mm, and ensuring that two turn-up cord fabric layer ends do not exist at the same height; the ring core rubber sheet is adopted to replace wrapping cloth of a bead core, and a steel wire ring and a bead filler are wrapped to be separated from a turn-up cord fabric layer; a layer of hard rubber sheet is arranged between the chafer and the positive wrapping cord fabric layer, and the tire has the capacity of coping with short-time impact load through the combined action of the whole structure.
Description
Technical Field
The utility model belongs to the technical field of the oblique crossing aircraft tire, concretely relates to reply short-time impact load's oblique crossing aircraft tire structure.
Background
The aviation tire is made of three basic materials of rubber, nylon wire and steel wire, which are bonded together through vulcanization, the external structure of the aviation tire comprises a tire tread, a tire sidewall, a tire bead and a lining, and the internal structure of the aviation tire comprises a buffer layer, a tire body cord layer, a high-strength steel wire tire bead, a cord fabric, a turned edge and the like.
When the aircraft tire of the carrier-based aircraft is used under a special working condition, the tire bears a short-time huge impact load which can be more than 10 times of the common shutdown load of the tire, so that the tire can reach a great sinking rate in a very short time, and the tire can generate a great deformation. Under the working condition, the maximum compression stress and the maximum strain energy density inside the central line area and outside the tire bead of the tire can reach more than 8 times of those of the ground-based condition. The higher the strain energy density of the tire, the larger the local strain of the tire is characterized and the higher the heat generation is. The prior common bias aircraft tire has a plurality of cord fabric ends from a center line area to a tire bead area, and the tire bead part is composed of a bead core wrapping cloth for wrapping a steel wire ring and a bead apex, a turn-up layer cord fabric and a bead wrapping cloth. The central line area is thick, and can not adapt to the great deformation under the simultaneous action of large compressive stress and large deformation, so that the fracture phenomenon of the central line area is easily caused. The existing oblique crossing aircraft tire structure has the defects that the stress between cord fabrics cannot be effectively dispersed and the delamination and bulging phenomena are easily caused due to the stress concentration phenomenon because a large number of cord fabric ends are gathered and the larger interlayer shearing exists between the positive cord fabric and the tire bead filler.
The CN104118280B applicant filed application discloses an aviation tire with a durable bead and a preparation method thereof, which increases the thickness of a bead part protective layer and improves the durability of the bead and the durability of the tire by increasing the number of layers of chafers and arranging a hard rubber sheet with excellent wear resistance between an outer layer chafer and an inner layer chafer at the bead part, but the aviation tire only increases the thickness of a rim part and has insufficient capability of dealing with short-time impact load.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a reply impact load's skew aircraft tire structure for solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
a diagonal aircraft tire structure for handling short-time impact loads is different from the existing diagonal aircraft tire structure in that:
(1) the high-strength nylon cord is used, and 2-12 layers of turn-up cord fabric layers which turn up and pass through the steel ring part are arranged;
(2) arranging the ends of the turn-up cord fabric layers which are turned up and down on the tire center line 15-16mm in a step shape from top to bottom by a difference level of 5-15mm, and ensuring that two turn-up cord fabric layer ends do not exist at the same height;
(3) the ring core rubber sheet is adopted to replace wrapping cloth of a bead core, and a steel wire ring and a bead filler are wrapped to be separated from a turn-up cord fabric layer;
(4) a layer of hard rubber sheet is arranged between the chafer and the positive wrapping cord fabric layer.
The bias aircraft tire is an aircraft tire in which a carcass ply and adjacent layer cords are crossed and arranged at an angle of less than 90 degrees with the center line of the tread;
the high-strength nylon cord is a nylon cord with the single cord breaking strength being more than 300N;
the short-time impact load is a load which enables the sinking rate of the tire to reach more than 50% within 15 seconds and the application time to be not more than 100 seconds;
the central line refers to a straight line connected with the maximum distance between the two outer sides of the tire section, namely the section width position when the aircraft tire is designed.
The core rubber sheet is a rubber sheet with the thickness of 0.5-1.0mm and the same as the reverse wrapping ply rubber material.
The hard film is a film with the thickness of 1.0-1.5mm and excellent wear resistance.
The utility model discloses a technological effect and advantage:
at present, the breaking strength of a normal nylon cord is 196N, the number of the turn-up cord fabric layers can be effectively reduced by using a high-strength nylon cord, for example, a 500 × 140 specification tire of an embodiment is used, the number of the turn-up cord fabric layers of the tire using the high-strength nylon cord is 4, and the number of the turn-up cord fabric ends can be reduced fundamentally by using a common nylon cord and only needing 6 turn-up cord fabric layers to achieve the same strength; the ring core rubber sheet replaces the wrapping cloth of the bead core, so that the two ends of the wrapping cloth of the bead core are directly reduced, and the interlayer stress can be effectively relieved; taking the 500 × 140 standard tire of the embodiment as an example, the number of the original 10 cord ends can be reduced to 4. The central line area is the position where the maximum deformation occurs when the bias aircraft tire bears the huge impact load, the thickness of the central line area is effectively reduced through the reduction of the end heads of the reverse cladding layer cord fabric and the setting position and the setting mode, the transition from thin to thick from the central line area to the tire bead position can be uniform, the central line area has good flexibility, the ultrahigh stress borne by the tire body cord can be effectively buffered or weakened, and the fracture resistance of the central line area is obviously improved. The use of the ring core rubber sheet and the arrangement of the hard rubber sheet can effectively eliminate and disperse the stress between the cord fabric layers, avoid the occurrence of stress concentration and obviously improve the fatigue resistance of the tire bead. The tire has the capability of coping with short-time impact load through the combined action of the whole structure.
Drawings
FIG. 1 is a schematic structural view of an aircraft tire of the present invention;
in the figure: 1, tyre beads; 2 a turn-up ply; 3, winding core films; 4, a steel wire ring; 5 a positive coating ply; 6, wrapping the tire bead cloth; 7, hard films; 8, a central line; 9 triangular glue.
Detailed Description
The present invention will be further described with reference to the following drawings and examples, but the present invention is not limited thereto.
Referring to fig. 1, the structure of a bias aviation tire for dealing with short-time impact load comprises a tire bead 1, a turn-up cord fabric layer 2, a core rubber sheet 3, a steel wire ring 4, a turn-up cord fabric layer 5, a chafer 6, a hard rubber sheet 7, a center line 8 and a triangular rubber 9; the structure of the bias aircraft tire is different from the structure of the existing bias aircraft tire:
(1) four layers of turn-up cord fabric layers 2 are arranged at the positions of beads 1 of the tire;
(2) the ends of the turning-up cord fabric layer 2 are arranged 16mm below the central line 8 and are arranged in a step shape from top to bottom in a 15mm difference level, and two ends of the turning-up cord fabric layer 2 do not exist at the same height;
(3) a ring core rubber sheet 3 with the thickness of 0.5mm is adopted to replace the wrapping cloth of the bead core, and the steel wire ring 4 and the bead filler 9 are wrapped up to be separated from the turn-up cord fabric layer 2;
(4) a layer of hard rubber sheet 7 with the thickness of 1.0mm is arranged between the chafer 6 and the positive covering cord fabric layer 5.
The thickness of the central line area can be reduced from 13.6mm to 7.6mm by testing according to the structure of the tire with the specification of 500 multiplied by 140. The tire is subjected to dynamic simulation test of corresponding working conditions, and test results show that the tire can bear 80kN impact load (the normal stop load of the tire is 8 kN) within 15s, the dynamic simulation test is completed under the test condition that the sinking rate reaches 65%, and the tire is not damaged in the test process.
Therefore, the oblique aviation tire structure has the advantages that the fracture resistance of the central line area and the fatigue resistance of the tire bead are obviously improved, and the oblique aviation tire structure has the capability of coping with short-time impact load.
Claims (5)
1. The utility model provides a deal with short-time impact load's skew aircraft tire structure which characterized in that: the structure of the rubber belt comprises a tire bead (1), a turn-up cord fabric layer (2), a core rubber sheet (3), a steel wire ring (4), a turn-up cord fabric layer (5), a tire chafer (6), a hard rubber sheet (7), a center line (8) and a bead filler (9);
2-12 layers of turn-up cord fabric layers (2) are arranged at the positions of the beads (1) of the tire;
the ends of the turn-up cord fabric layer (2) are arranged 15-16mm below the center line (8) of the tire and are arranged in a step shape from top to bottom in a 5-15mm difference level, and two ends of the turn-up cord fabric layer do not exist at the same height;
a bead core rubber sheet (3) is adopted to replace wrapping cloth of a bead core, and a steel wire ring (4) and a bead filler (9) are wrapped and separated from a reverse wrapping cord fabric layer (2);
a layer of hard rubber sheet (7) with the thickness of 1.0mm is arranged between the tire bead filler (6) and the positive covering cord fabric layer (5).
2. The bias aircraft tire structure handling short time impact loads according to claim 1, wherein: the turn-up cord fabric layer (2) is 4 layers.
3. The bias aircraft tire structure handling short time impact loads according to claim 1, wherein: the ends of the turn-up cord fabric layers (2) are arranged below a tire central line (8) by 16mm and above the apex (9) in a stepped manner from top to bottom with a difference of 15mm, and two ends of the turn-up cord fabric layers (2) are not arranged at the same height.
4. The bias aircraft tire structure handling short time impact loads according to claim 1, wherein: the thickness of the ring core rubber sheet (3) is 0.5-1.0mm, and the rubber sheet is consistent with the rubber material of the turn-up cord fabric layer (2).
5. The bias aircraft tire structure handling short time impact loads according to claim 1, wherein: the thickness of the hard film (7) is 1.0-1.5 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922416199.7U CN212194954U (en) | 2019-12-29 | 2019-12-29 | Skew aircraft tire structure for dealing with short-time impact load |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922416199.7U CN212194954U (en) | 2019-12-29 | 2019-12-29 | Skew aircraft tire structure for dealing with short-time impact load |
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| Publication Number | Publication Date |
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| CN212194954U true CN212194954U (en) | 2020-12-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201922416199.7U Active CN212194954U (en) | 2019-12-29 | 2019-12-29 | Skew aircraft tire structure for dealing with short-time impact load |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110978591A (en) * | 2019-12-29 | 2020-04-10 | 中国化工集团曙光橡胶工业研究设计院有限公司 | Skew aircraft tire capable of coping with short-time impact load and preparation method thereof |
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2019
- 2019-12-29 CN CN201922416199.7U patent/CN212194954U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110978591A (en) * | 2019-12-29 | 2020-04-10 | 中国化工集团曙光橡胶工业研究设计院有限公司 | Skew aircraft tire capable of coping with short-time impact load and preparation method thereof |
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