Puncturing structure of aircraft tire cord calendering device

Abstract

The utility model relates to the technical field of aircraft tire processing, and discloses a puncturing structure of an aircraft tire cord fabric calendering device, which comprises a working table, four supporting legs are fixedly arranged on the bottom surface of the working table and are uniformly distributed on the peripheral bottom surface of the working table, a calendering mechanism is fixedly arranged on the front surface of the working table, and the calendering mechanism is fixedly arranged on the back surface of the working table. A puncturing mechanism is fixedly arranged on the top face of the right end of the workbench. The calendaring mechanism comprises a calendaring part and a clamping part; the left side surface of the clamping part is fixedly connected with the right side surface of the calendaring part; the clamping part comprises fixing plates, and the back faces of the two fixing plates are fixedly connected with the front end face and the rear end face of the right end of the workbench correspondingly. Through the arrangement of the calendaring mechanism, the arrangement of a spring and the cooperation of a clamping plate, when the two calendaring rollers conduct calendaring guiding on the aircraft tire cord fabric, the ends, needing to be punctured, of the calendaring rollers can be fixedly clamped, the situation that the follow-up puncturing work is affected due to position deviation of the calendaring rollers is avoided, and the puncturing efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation tire processing, in particular to a puncture structure of an aviation tire cord calendering device. Background Art

[0002] Aircraft tires, commonly known as aircraft tires, are a key component of an aircraft's landing gear system. Their primary function is to provide support, load bearing, and cushioning during parking, takeoff, and landing. They are composed of rubber, a carcass, and various additives, all cross-linked through complex chemical reactions. Cord is a common carcass material used in tire manufacturing.

[0003] A Chinese patent discloses a cord calendering device for producing tires for electric motorcycles, with the authorization announcement number CN214562388U. The device includes a base, the upper end of which is provided with a power supply and a negative terminal, and a positive terminal is provided on one side of the negative terminal; a bottom plate is provided on the lower side of the positive terminal, a lower roller is provided on the upper side of the bottom plate, and an upper roller is provided on the upper side of the lower roller. Rollers are provided inside the lower roller and the upper roller. By providing a power supply, a positive terminal and a negative terminal, dust on the upper roller and the lower roller can be removed.

[0004] However, there are still the following disadvantages: the cord calendering device for producing electric motorcycle tires cannot quickly position and clamp the cord when puncturing it, so it is urgent to design a puncture structure for the cord calendering device of an aviation tire. Utility Model Content

[0005] The purpose of the utility model is to provide a puncture structure for an aircraft tire cord calendering device to solve the problems raised in the above background technology.

[0006] To achieve the above-mentioned object, the present invention provides the following technical solution: a puncture structure of an aircraft tire cord calendering device includes a workbench, the bottom surface of the workbench is fixedly provided with support legs, the number of the support legs is four and the number of the support legs is evenly distributed around the bottom surface of the workbench, the front surface of the workbench is fixedly provided with a calendering mechanism, and the top surface of the right end of the workbench is fixedly provided with a puncture mechanism;

[0007] The calendering mechanism includes a calendering portion and a clamping portion, wherein the left side of the clamping portion and the right side of the calendering portion are fixedly connected;

[0008] The clamping part includes a fixing plate, the back surfaces of the two fixing plates are fixedly connected to the front and rear end surfaces of the right end of the workbench respectively, and the inner bottom surfaces of the two fixing plates are fixedly provided with springs;

[0009] The puncture mechanism comprises a puncture part and a power part, wherein the back side of the power part and the front side of the puncture part are fixedly connected;

[0010] The power unit includes a device block, the bottom surface of which is fixedly connected to the top surface of the right end of the workbench, and a motor B is fixedly arranged on the front surface of the device block.

[0011] Preferably, a motor A is fixedly installed on the front side of the workbench, and the back end surface of the output rod of the motor A passes through the front side of the workbench and extends to the inside of the workbench. An active rod is fixedly installed on the back end surface of the output rod of the motor A, and the back end surface of the active rod and the inner wall of the workbench are rotatably connected by a bearing.

[0012] Preferably, a driven rod is provided inside the workbench, the surface of the driven rod and the inner wall of the workbench are rotatably connected by a bearing, and two gears are fixedly sleeved on the back end surfaces of the driven rod and the active rod respectively, and the two gear side surfaces are meshed with each other.

[0013] Preferably, the surfaces of the active rod and the driven rod are fixedly sleeved with calendering rollers, the top surfaces of the two springs are respectively fixedly provided with two clamping plates, and the side surfaces of the two clamping plates are respectively in frictional sliding contact with the inner wall of the workbench.

[0014] Preferably, the back end surface of the output rod of the motor B passes through the front surface of the device block and extends to the inside of the device block. A bidirectional threaded rod is fixedly provided on the back end surface of the output rod of the motor B. The surface of the bidirectional threaded rod and the inner wall of the device block are rotatably connected by a bearing.

[0015] Preferably, two movable plates are threadedly sleeved on the front and rear end surfaces of the bidirectional threaded rod respectively, the side surfaces of the movable plates are frictionally and slidingly connected to the inner walls of the device blocks, the bottom surfaces of the movable plates are hingedly provided with connecting plates, and hydraulic rods are fixedly provided on the inner walls of the bottom ends of the two connecting plates through hinged rods, and a puncture head is fixedly provided on the bottom surface of the hydraulic rod output rod.

[0016] Compared with the prior art, the beneficial effects of the present invention are:

[0017] 1. The puncture structure of the aircraft tire cord calendering device is equipped with a calendering mechanism. Through the cooperation of a spring and a clamping plate, the two calendering rollers can fix and clamp the end of the aircraft tire cord to be punctured when calendering and guiding it, preventing positional deviation that would affect subsequent puncturing work, thereby improving puncture efficiency.

[0018] 2. The puncture structure of the aircraft tire cord calendering device is equipped with a motor A and an active rod to work together. The transmission effect of the two gears enables the two calendering rollers to rotate synchronously, thereby quickly calendering the aircraft tire cord that needs to be calendered and conveyed. The operation is fully automated, saving time, effort and labor.

[0019] 3. The puncturing structure of the aircraft tire cord calendering device is provided with a puncturing mechanism. Through the cooperation of the motor B and the bidirectional threaded rod, the two movable plates are moved in opposite directions through the action of the two reverse threads, and the connection of the connecting plates is folded at an angle, so that the hydraulic rod can drive the puncturing head to perform rapid puncturing. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a three-dimensional schematic diagram of the front structure of the utility model;

[0021] Figure 2 This is a schematic sectional view of the front structure of the utility model;

[0022] Figure 3 This is a three-dimensional schematic diagram of the back structure of the utility model;

[0023] Figure 4 This is a schematic diagram of a three-dimensional cross-sectional view of the right side structure of the utility model;

[0024] Figure 5 For this utility model Figure 4 A three-dimensional enlarged schematic diagram of the structure of area A in the middle.

[0025] In the figure: 1. Workbench; 2. Support legs; 3. Calendering mechanism; 301. Motor A; 302. Active rod; 303. Driven rod; 304. Gear; 305. Calendering roller; 306. Fixed plate; 307. Spring; 308. Clamping plate; 4. Puncture mechanism; 401. Device block; 402. Motor B; 403. Bidirectional threaded rod; 404. Moving plate; 405. Connecting plate; 406. Hydraulic rod; 407. Puncture head. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0027] Example 1

[0028] See also Figure 1-Figure 5As shown, a puncture structure of an aircraft tire cord calendering device includes a workbench 1, a bottom surface of the workbench 1 is fixedly provided with supporting legs 2, the number of supporting legs 2 is four and is evenly distributed on the bottom surface around the workbench 1, a calendering mechanism 3 is fixedly provided on the front surface of the workbench 1, and a puncture mechanism 4 is fixedly provided on the top surface of the right end of the workbench 1; the calendering mechanism 3 includes a calendering part and a clamping part, and the left side of the clamping part is fixedly connected to the right side of the calendering part; the clamping part includes a fixed plate 306, the back surfaces of the two fixed plates 306 are respectively fixedly connected to the front and rear end surfaces of the right end of the workbench 1, and the inner bottom surfaces of the two fixed plates 306 are fixedly provided with springs 307; the spring 307 is always in a contracted state, the puncture mechanism 4 includes a puncture part and a power part, and the back surface of the power part is fixedly connected to the front surface of the puncture part; the power part includes a device block 401, the bottom surface of the device block 401 is fixedly connected to the top surface of the right end of the workbench 1, and the front surface of the device block 401 is fixedly provided with a motor B402;

[0029] During operation, the workbench 1 is placed firmly by the four supporting legs 2, and one end of the aircraft tire cord to be calendered is placed on one end of the two calendering rollers 305. Through the contraction and rebound effect of the spring 307, the two clamping plates 308 can quickly fix and clamp the calendered aircraft tire cord.

[0030] Furthermore, a motor A301 is fixedly provided on the front of the workbench 1. The model of the motor A301 is Y2-112M-6. The back end surface of the output rod of the motor A301 passes through the front of the workbench 1 and extends into the interior of the workbench 1. An active rod 302 is fixedly provided on the back end surface of the output rod of the motor A301. The back end surface of the active rod 302 and the inner wall of the workbench 1 are rotatably connected by a bearing.

[0031] During operation, the motor A301 is started to rotate the active rod 302 .

[0032] Furthermore, a driven rod 303 is provided inside the workbench 1. The surface of the driven rod 303 is rotatably connected to the inner wall of the workbench 1 by a bearing. Two gears 304 are fixedly sleeved on the back end surfaces of the driven rod 303 and the active rod 302, respectively. The side surfaces of the two gears 304 are meshed with each other.

[0033] During operation, the active rod 302 rotates, and the driven rod 303 rotates simultaneously through the meshing transmission of the two gears 304 .

[0034] Furthermore, a calendering roller 305 is fixedly sleeved on the surface of the active rod 302 and the driven rod 303. Two clamping plates 308 are fixedly mounted on the top surfaces of the two springs 307. The sides of the two clamping plates 308 are in frictional sliding contact with the inner wall of the workbench 1. The front and rear end surfaces of the workbench 1 are respectively provided with two sliding grooves of the same size as the side dimensions of the clamping plates 308.

[0035] During operation, the driven rods 303 rotate simultaneously, thereby driving the two calendering rollers 305 to rotate in opposite directions and calendering and conveying the aircraft tire cord placed therebetween.

[0036] Furthermore, the back end face of the output rod of the motor B402 passes through the front face of the device block 401 and extends into the interior of the device block 401. A bidirectional threaded rod 403 is fixedly provided on the back end face of the output rod of the motor B402. The surface of the bidirectional threaded rod 403 and the inner wall of the device block 401 are rotatably connected by a bearing.

[0037] During operation, the motor B402 is started to rotate the bidirectional threaded rod 403, and the two moving plates 404 are moved in opposite directions through the action of the two reverse threads.

[0038] Furthermore, two movable plates 404 are respectively threadedly sleeved on the front and rear end surfaces of the bidirectional threaded rod 403. The side surfaces of the movable plates 404 are frictionally and slidingly connected to the inner wall of the device block 401. The bottom surface of the movable plate 404 is hingedly provided with a connecting plate 405. The inner walls of the bottom ends of the two connecting plates 405 are fixedly provided with hydraulic rods 406 through hinged rods. The bottom surface of the output rod of the hydraulic rod 406 is fixedly provided with a piercing head 407.

[0039] During operation, the two movable plates 404 move toward each other, and the hydraulic rod 406 moves downward through the hinged connecting plate 405 and the folding of its connection. At the same time, the hydraulic rod 406 is activated, so that the puncturing head 407 quickly punctures the surface of the aircraft tire cord.

[0040] Working principle: When in use, first place the workbench 1 firmly through the four supporting legs 2, place one end of the aircraft tire cord to be calendered on one end of the two calendering rollers 305, start the motor A301, so that the active rod 302 rotates, and through the meshing transmission of the two gears 304, the driven rod 303 rotates at the same time, thereby driving the two calendering rollers 305 to rotate in opposite directions, and calendering and conveying the aircraft tire cord placed in the middle. After the right end of the aircraft tire cord is calendered, it enters the right end of the workbench 1 When inside, the two clamping plates 308 quickly fix and clamp the calendered aircraft tire cord through the contraction and rebound effect of the spring 307, and the motor B402 is started to rotate the bidirectional threaded rod 403. The two movable plates 404 move in opposite directions through the action of the two reverse threads. The hydraulic rod 406 moves downward through the hinged connecting plate 405 and the folding of its connection, and at the same time, the hydraulic rod 406 is started, so that the puncturing head 407 quickly punctures the surface of the aircraft tire cord.

[0041] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein with equivalents. Any modifications, equivalent replacements, and similar improvements made within the theoretical and principle content of the present invention shall be included in the scope of protection of the present invention.

Claims

1. A puncture structure for an aircraft tire cord calendering device, comprising a workbench (1), characterized in that: The bottom surface of the workbench (1) is fixedly provided with support legs (2), the number of the support legs (2) is four and they are evenly distributed around the bottom surface of the workbench (1), the front surface of the workbench (1) is fixedly provided with a calendering mechanism (3), and the top surface of the right end of the workbench (1) is fixedly provided with a puncturing mechanism (4); The calendering mechanism (3) comprises a calendering portion and a clamping portion, wherein the left side of the clamping portion and the right side of the calendering portion are fixedly connected; The clamping portion includes a fixing plate (306), the back surfaces of the two fixing plates (306) are respectively fixedly connected to the front and rear end surfaces of the right end of the workbench (1), and the inner bottom surfaces of the two fixing plates (306) are fixedly provided with springs (307); The puncture mechanism (4) comprises a puncture part and a power part, wherein the back side of the power part and the front side of the puncture part are fixedly connected; The power unit comprises a device block (401), the bottom surface of the device block (401) is fixedly connected to the top surface of the right end of the workbench (1), and the front surface of the device block (401) is fixedly provided with a motor B (402).

2. The puncture structure of an aircraft tire cord calendering device according to claim 1, characterized in that: A motor A (301) is fixedly provided on the front face of the workbench (1); a back end face of an output rod of the motor A (301) passes through the front face of the workbench (1) and extends into the interior of the workbench (1); an active rod (302) is fixedly provided on the back end face of the output rod of the motor A (301); a back end surface of the active rod (302) and an inner wall of the workbench (1) are rotatably connected via a bearing.

3. The puncture structure of an aircraft tire cord calendering device according to claim 2, characterized in that: A driven rod (303) is provided inside the workbench (1), and the surface of the driven rod (303) and the inner wall of the workbench (1) are rotatably connected by a bearing. Two gears (304) are fixedly sleeved on the back end surfaces of the driven rod (303) and the active rod (302), respectively, and the side surfaces of the two gears (304) are meshed with each other.

4. The puncture structure of an aircraft tire cord calendering device according to claim 3, characterized in that: The surfaces of the active rod (302) and the driven rod (303) are fixedly sleeved with a calendering roller (305), and the top surfaces of the two springs (307) are respectively fixedly provided with two clamping plates (308), and the side surfaces of the two clamping plates (308) are respectively in frictional sliding contact with the inner wall of the workbench (1).

5. The puncture structure of an aircraft tire cord calendering device according to claim 1, characterized in that: The back end surface of the output rod of the motor B (402) passes through the front surface of the device block (401) and extends into the interior of the device block (401). A bidirectional threaded rod (403) is fixedly provided on the back end surface of the output rod of the motor B (402). The surface of the bidirectional threaded rod (403) and the inner wall of the device block (401) are rotatably connected by a bearing.

6. The puncture structure of an aircraft tire cord calendering device according to claim 5, characterized in that: Two movable plates (404) are respectively threadedly sleeved on the front and rear end surfaces of the bidirectional threaded rod (403); the side surfaces of the movable plates (404) are frictionally and slidingly connected to the inner wall of the device block (401); the bottom surface of the movable plate (404) is hingedly provided with a connecting plate (405); the inner walls of the bottom ends of the two connecting plates (405) are fixedly provided with hydraulic rods (406) through hinged rods; and the bottom surface of the output rod of the hydraulic rod (406) is fixedly provided with a puncture head (407).

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