An automatic testing device for the tensile strength of steel wire in aircraft tires

Abstract

This utility model provides an automatic testing device for the tensile strength of steel wire in aviation tires, belonging to the field of tire steel wire production and processing technology. The automatic testing device includes a base plate; a first slide groove formed at the upper end of the base plate; a fixed frame slidably connected within the first slide groove, with a side frame fixedly connected to the side end of the fixed frame; and a clamping mechanism including a side frame, a side plate, a mounting frame, a clamping mold, a cylinder, a first spring, and a limiting component. The side frame is fixedly connected to the side end of the fixed frame, the side plate is connected to the side end of the side frame, the mounting frame is connected to the side end of the side plate, and the clamping mold is connected to the side end of the mounting frame. By designing a modular T-block and T-slot connection between the clamping mold and the mounting frame, the device can quickly and easily replace clamping molds of different specifications.

Description

Technical Field

[0001] This utility model belongs to the field of tire steel wire production and processing technology, and specifically relates to an automatic detection device for the tensile strength of aviation tire steel wire. Background Technology

[0002] Currently, the automatic tensile strength testing device for aircraft tire steel wires is a key piece of equipment specifically designed to evaluate the mechanical properties of high-strength steel wires used in aircraft tires. With the aviation industry's ever-increasing demands for flight safety and material reliability, this equipment plays a crucial role in ensuring the quality of aircraft tires. Its main function is to measure key parameters such as tensile strength and elongation of the steel wires through a precisely controlled stretching process, ensuring that each steel wire meets stringent quality standards, thereby guaranteeing the stability and safety of aircraft tires under complex and variable flight conditions.

[0003] Existing equipment for testing the tensile strength of steel wire in aircraft tires typically employs mechanical transmission to clamp and stretch the wire, combined with sensor technology for data acquisition and analysis. These devices can meet basic testing requirements to a certain extent and possess a degree of operational stability and data accuracy. For example, some devices provide stable tensile force through electric or hydraulic drive systems and utilize high-precision sensors to monitor mechanical changes during the stretching process in real time, providing strong support for quality control.

[0004] However, in practical applications, when faced with steel wire samples of different specifications and sizes, how to further improve the adaptability and stability of clamping, optimize the speed and accuracy of tensile loading, and enhance the automation and data processing capabilities of the entire system remains an important direction for current technological improvement. Utility Model Content

[0005] The purpose of this invention is to provide an automatic detection device for the tensile strength of steel wires in aircraft tires, which aims to solve the problems in the prior art.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] An automatic testing device for the tensile strength of steel wire in aircraft tires includes:

[0008] Base plate;

[0009] A first slide groove is formed at the upper end of the base plate; a fixed frame is slidably connected in the first slide groove, and a side frame is fixedly connected to the side end of the fixed frame;

[0010] The clamping mechanism includes a side frame, a side plate, a mounting frame, a clamping mold, a cylinder, a first spring, and a limiting assembly. The side frame is fixedly connected to the side end of the fixed frame, the side plate is connected to the side end of the side frame, the mounting frame is connected to the side end of the side plate, the clamping mold is connected to the side end of the mounting frame, the cylinder is fixedly connected to the side end of the side plate, the output end of the cylinder is connected to the mounting frame, and the first spring is sleeved and connected to the circumferential surface of the output end of the cylinder.

[0011] As a preferred embodiment of this utility model, a second sliding groove is provided on the side end of the side plate, and a slider is slidably connected in the second sliding groove. The slider is connected to the mounting frame. A T-shaped groove is provided on the side end of the mounting frame. A T-shaped block is fixedly connected to the side end of the clamping mold, and the T-shaped block matches the T-shaped groove.

[0012] In a preferred embodiment of this utility model, a mounting base is fixedly connected to the lower end of the base plate, a lead screw is rotatably connected to the side end of the mounting base, a lead screw nut is connected to the circumferential surface of the lead screw, and the lead screw nut is connected to the fixing frame.

[0013] In a preferred embodiment of this utility model, a motor is fixedly connected to the lower end of the base plate, and a gear chain is connected to the output end of the motor and the side end of the lead screw.

[0014] In a preferred embodiment of this utility model, the upper end of the base plate is provided with multiple slots, a rectangular plate is fixedly connected to the side end of the side frame, a telescopic rod is fixedly connected to the lower end of the rectangular plate, a locking block is fixedly connected to the output end of the telescopic rod, a third spring is sleeved and connected to the circumferential surface of the output end of the telescopic rod, and the locking block engages with the slots.

[0015] In a preferred embodiment of this utility model, a support frame is fixedly connected to the upper end of the base plate, a rotating rod is connected to the upper end of the support frame, a second spring is sleeved on the circumferential surface of the rotating rod, and the side end of the second spring is connected to the guide roller.

[0016] Compared with the prior art, the beneficial effects of this utility model are:

[0017] 1. In this solution, the modular T-block and T-slot connection between the clamping mold and the mounting frame allows for quick and easy replacement of clamping molds of different specifications. This design not only improves the equipment's adaptability to steel wires of various diameters and shapes but also ensures that the steel wire is firmly clamped during tensile testing, avoiding test errors or wire slippage caused by unstable clamping. Furthermore, the first spring design provides a cushioning effect, reducing the risk of damage to the steel wire surface during clamping and further enhancing the stability and reliability of the clamping process.

[0018] 2. In this solution, by utilizing a motor and gear chain to drive the lead screw rotation, combined with the lead screw nut to achieve precise movement of the fixing frame and clamping mechanism, a precisely controlled tensile force can be applied to the steel wire of aviation tires. Simultaneously, the guide roller, through a rotating rod and a second spring, can adjust the steel wire's posture in real time during the stretching process, ensuring uniform force distribution and smooth operation. The entire system boasts a high degree of automation; from feeding and clamping to tensile testing and result recording, all operations can be automated, significantly improving testing efficiency and data accuracy, meeting the demands of modern industry for efficient and precise quality control. Attached Figure Description

[0019] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0020] Figure 1 This is a perspective view of the present utility model;

[0021] Figure 2 This is an exploded view of the present invention;

[0022] Figure 3 This utility model Figure 2 Exploded view of the central fixed frame;

[0023] Figure 4 This utility model Figure 2 Exploded view of the midsole plate.

[0024] In the diagram: 1. Base plate; 2. Mounting base; 3. Lead screw; 4. Lead screw nut; 5. Gear chain; 6. Motor; 7. First slide groove; 8. Slot; 9. Fixing frame; 10. Side frame; 11. Rectangular plate; 12. Protrusion; 1201. Notch; 13. Side plate; 14. Second slide groove; 15. Slider; 16. Mounting frame; 1601. T-slot; 17. Clamping mold; 1701. T-block; 18. Side plate; 19. Cylinder; 20. First spring; 21. Support frame; 22. Rotating rod; 23. Guide roller; 24. Second spring; 25. Telescopic rod; 26. Slot; 27. Third spring. Detailed Implementation

[0025] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0026] Example 1

[0027] Please see Figure 1-4 The present invention provides the following technical solution:

[0028] An automatic testing device for the tensile strength of steel wire in aircraft tires includes:

[0029] Base plate 1;

[0030] The first slide groove 7 is formed at the upper end of the base plate 1; the fixing frame 9 is slidably connected in the first slide groove 7, and the side end of the fixing frame 9 is fixedly connected to the side frame 10;

[0031] The clamping mechanism includes a side frame 10, a side plate 13, a mounting frame 16, a clamping mold 17, a cylinder 19, a first spring 20, and a limiting assembly. The side frame 10 is fixedly connected to the side end of the fixed frame 9, the side plate 13 is connected to the side end of the side frame 10, the mounting frame 16 is connected to the side end of the side plate 13, the clamping mold 17 is connected to the side end of the mounting frame 16, the cylinder 18 is fixedly connected to the side end of the side plate 13, the output end of the cylinder 18 is connected to the mounting frame 16, and the first spring 20 is sleeved and connected to the circumferential surface of the output end of the cylinder 18.

[0032] In a specific embodiment of this utility model, when the aviation tire steel wire to be tested is placed between the clamping molds 17, the clamping mechanism is in its initial state, ready to clamp and fix the steel wire.

[0033] When the cylinder 18 is activated and pushes the mounting bracket 16 to move toward the steel wire, the clamping mold 17 moves synchronously with the mounting bracket to approach the surface of the steel wire, achieving a preliminary clamping action. At the same time, the first spring 20 acts as a buffer at the output end of the cylinder to prevent excessive clamping force from causing deformation or damage to the steel wire.

[0034] When the slider 15 in the limiting assembly slides along the second slide groove 14 and connects with the mounting bracket 16, the running trajectory of the mounting bracket is effectively limited during the clamping process, which improves the stability and positioning accuracy of the clamping action and ensures that the steel wire is subjected to uniform force.

[0035] After clamping is completed, the fixing frame 9 slides along the base plate 1 in the first slide groove 7, driving the side frame 10 and the clamping mechanism to move as a whole; in this way, the clamped aircraft tire steel wire enters the tensile test area, ready to be tested for tensile strength.

[0036] When the motor 6 drives the lead screw 3 to rotate, the lead screw nut 4 drives the fixed frame 9 to move in the opposite direction; in this way, the two ends of the steel wire are fixed by the clamping mechanisms on both sides and a tensile force is applied, thereby completing the tensile strength test. The system can collect the mechanical parameters during the tensile process in real time.

[0037] After the tensile test is completed, each actuator resets in sequence, the cylinder 18 retracts to release the clamping force, and the clamping mold 17 releases the steel wire; in this way, the operator can remove the tested steel wire, replace it with a new sample, and enter the next round of testing process.

[0038] Please refer to the details. Figure 1-4 The side plate 13 has a second slide groove 14 at its side end, and a slider 15 is slidably connected in the second slide groove 14. The slider 15 is connected to the mounting bracket 16. The mounting bracket 16 has a T-slot 1601 at its side end. The clamping mold 17 has a T-block 1701 fixedly connected to its side end, and the T-block 1701 matches the T-slot 1601.

[0039] In this embodiment: when the cylinder 18 starts to push the mounting bracket 16 to slide, the mounting bracket 16 drives the slider 15 connected to it to move synchronously. The slider 15 slides smoothly in the second slide groove 14 on the side plate 13, providing guidance and support for the clamping action and preventing the mounting bracket from shifting or getting stuck.

[0040] When the slider 15 slides along the second slide groove 14 to the set position, the mounting bracket 16 remains in a stable moving state, ensuring that the clamping mold 17 is subjected to uniform force during the clamping process, thereby improving the clamping accuracy and the reliability of the wire clamping.

[0041] When the clamping mold 17 needs to be replaced to fit different specifications of aviation tire steel wire, the operator can align the T-block 1701 on the side of the clamping mold 17 with the T-slot 1601 on the mounting bracket 16 and slide it in along the slot direction to achieve quick installation and positioning.

[0042] After the clamping mold 17 is connected to the T-slot 1601 via the T-block 1701, a stable and detachable connection structure is formed between the clamping mold and the mounting frame. This structure is not easy to loosen during the tensile testing process and is also convenient for later maintenance and replacement.

[0043] Please refer to the details. Figure 1-4 The lower end of the base plate 1 is fixedly connected to the mounting base 2, and the side end of the mounting base 2 is rotatably connected to the lead screw 3. The circumferential surface of the lead screw 3 is connected to the lead screw nut 4, and the lead screw nut 4 is connected to the fixing frame 9.

[0044] In this embodiment: when the motor 6 drives the lead screw 3 to rotate through the gear chain 5, the lead screw 3 drives the lead screw nut 4 meshing with it to move along the lead screw axis, realizing linear reciprocating motion, and providing power support for the sliding of the fixed frame 9.

[0045] When the lead screw nut 4 moves on the lead screw 3, the fixed frame 9 connected to it slides synchronously along the first slide groove 7 on the base plate 1, thereby driving the clamping mechanism to move as a whole and realizing the tensile loading of the steel wire of the aircraft tire.

[0046] When the lead screw 3 rotates in the reverse direction, the lead screw nut 4 drives the fixing bracket 9 back to the initial position, completing one tensile testing cycle and facilitating the rapid start of the next testing operation.

[0047] When the equipment needs to be replaced with steel wires of different specifications for tensile testing, the stroke and running speed of the lead screw 3 can be adjusted through the control system; in this way, it can adapt to various tensile strength testing needs and improve the flexibility and automation of equipment use.

[0048] Please refer to the details. Figure 1-4 A motor 6 is fixedly connected to the lower end of the base plate 1, and a gear chain 5 is connected to the output end of the motor 6 and the side end of the lead screw 3.

[0049] In this embodiment: when the motor 6 starts, the motor output drives the lead screw 3 to rotate synchronously through the gear chain 5, efficiently transmitting the motor's kinetic energy to the lead screw transmission system, providing stable power for the reciprocating movement of the fixed frame 9.

[0050] When the gear chain 5 drives the lead screw 3 to rotate in the forward direction, the lead screw nut 4 moves along the lead screw axis and drives the fixed frame 9 connected to it to slide along the base plate 1, thereby realizing the tensile loading of the aircraft tire steel wire in the clamped state.

[0051] When the control system issues a return command, the motor 6 drives the lead screw 3 to rotate in the opposite direction; in this way, the lead screw nut 4 drives the fixed frame 9 to move in the opposite direction, so that the clamping mechanism returns to the initial position and completes a complete tensile testing cycle.

[0052] When it is necessary to adjust the stretching speed or stroke to adapt to the testing of steel wires of different strength grades, the stretching process can be precisely controlled by adjusting the speed and running angle of the motor 6 and coordinating with the transmission ratio of the gear chain 5, thereby improving the applicability and testing accuracy of the equipment.

[0053] In this way, when the drive system consisting of motor 6, gear chain 5 and lead screw 3 works in coordination, it not only achieves stable power transmission and precise control in the tensile testing process, but also enhances the automation level and operating efficiency of the entire automatic testing device for the tensile strength of aviation tire steel wire, meeting the actual needs of modern industry for high-precision and intelligent testing.

[0054] Please refer to the details. Figure 1-4 The upper end of the base plate 1 is provided with multiple slots 8. A rectangular plate 11 is fixedly connected to the side end of the side frame 10. A telescopic rod 25 is fixedly connected to the lower end of the rectangular plate 11. A locking block 26 is fixedly connected to the output end of the telescopic rod 25. A third spring 27 is sleeved and connected to the circumferential surface of the output end of the telescopic rod 25. The locking block 26 is engaged with the slot 8.

[0055] In this embodiment: when the position of the clamping mechanism needs to be adjusted, the operator activates the telescopic rod 25, causing its output end to drive the locking block 26 to disengage from the locking groove 8 on the base plate 1, thereby releasing the limiting fixation of the clamping mechanism and allowing the side frame 10 to move freely along the first sliding groove 7.

[0056] When the side frame 10 drives the rectangular plate 11 and the telescopic rod 25 to slide to the target position, the telescopic rod 25, under the elastic force of the third spring 27, pushes the locking block 26 to automatically insert into the corresponding slot 8, thereby realizing the quick positioning and stable connection of the clamping mechanism on the base plate 1.

[0057] When vibration or external force disturbance occurs during the tensile testing process, the cooperation structure between the clamping block 26 and the slot 8 can effectively prevent the clamping mechanism from shifting, thereby improving the stability and data reliability during the testing process.

[0058] When it is necessary to replace the steel wire of different specifications of aviation tires and adjust the clamping distance, simply control the telescopic rod 25 again to disengage the clamping block 26 from the slot 8, and the position of the clamping mechanism can be readjusted. In this way, when the entire clamping and positioning structure works together in actual testing operations, it not only achieves rapid positioning and stable support of the clamping mechanism, but also enhances the adaptability and ease of operation of the equipment under multiple working conditions, meeting the requirements of high precision and high efficiency for automatic testing of the tensile strength of aviation tire steel wires.

[0059] Please refer to the details. Figure 1-4 A support frame 21 is fixedly connected to the upper end of the base plate 1. A rotating rod 22 is connected to the upper end of the support frame 21. A second spring 24 is sleeved on the circumferential surface of the rotating rod 22. The side end of the second spring 24 is connected to the guide roller 23.

[0060] In this embodiment: when the aviation tire steel wire is fed into the clamping mechanism; the guide roller 23 is located on both sides of the steel wire travel path, which initially guides the steel wire to accurately enter the clamping area of ​​the clamping mold 17, avoiding misalignment or damage to the steel wire surface.

[0061] When the steel wire experiences slight vibration or uneven tension during the stretching process, the guide roller 23 rotates freely via the rotating rod 22 and automatically adjusts its contact pressure with the steel wire under the elastic action of the second spring 24, maintaining smooth operation of the steel wire and improving the stability of the clamping and stretching process.

[0062] When changing to steel wires of different diameters, the operator can manually move the guide roller 23 to swing around the rotating rod 22 and adapt to the new wire width. The second spring 24 provides appropriate rebound force according to the change in wire tension, ensuring that the guide roller always fits the wire surface without causing excessive compression.

[0063] When the steel wire is released after the tensile test, the guide roller 23 automatically returns to its initial position under the action of the spring, preparing for the introduction and clamping of the next set of steel wires, thus improving the operating efficiency and automation level of the equipment.

[0064] The working principle and usage process of this utility model are as follows: First, the cylinder 18 is activated to push the mounting bracket 16 to slide. The mounting bracket 16 drives the connected slider 15 to move synchronously. The slider 15 slides smoothly within the second groove 14 on the side plate 13, providing guidance and support for the clamping action and preventing the mounting bracket from shifting or jamming. The slider 15 slides along the second groove 14 to the set position, and the mounting bracket 16 maintains a stable moving state, ensuring that the clamping mold 17 is subjected to uniform force during clamping, improving clamping accuracy and the reliability of wire clamping. When the clamping mold 17 needs to be replaced to adapt to different specifications of aviation tire wires, the operator will... The T-block 1701 is aligned with the T-slot 1601 on the mounting bracket 16 and slides in along the slot direction to achieve rapid installation and positioning. After the clamping mold 17 is connected to the T-slot 1601 through the T-block 1701, a stable and detachable connection structure is formed between the clamping mold and the mounting bracket. It is not easy to loosen during the tensile test and is also easy to maintain and replace later. The entire limiting and guiding structure works together during the clamping and tensile test, which effectively improves the stability and flexibility of the clamping mechanism and enhances the equipment's adaptability to various specifications of aviation tire steel wire, meeting the actual needs of efficient and accurate clamping in automated testing.

[0065] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. An automatic device for detecting the tensile strength of steel wires of an aircraft tire, characterized in that, include: Base plate (1); First slide groove (7), the first slide groove (7) is opened at the upper end of the base plate (1); fixed frame (9), the fixed frame (9) is slidably connected in the first slide groove (7), and a side frame (10) is fixedly connected to the side end of the fixed frame (9); The clamping mechanism includes a side frame (10), a side plate (13), a mounting frame (16), a clamping mold (17), a cylinder (19), a first spring (20), and a limiting component. The side frame (10) is fixedly connected to the side end of the fixing frame (9). The side plate (13) is connected to the side end of the side frame (10). The mounting frame (16) is connected to the side end of the side plate (13). The clamping mold (17) is connected to the side end of the mounting frame (16). The cylinder (19) is fixedly connected to the side end of the side plate (13). The output end of the cylinder (19) is connected to the mounting frame (16). The first spring (20) is sleeved and connected to the circumferential surface of the output end of the cylinder (19).

2. The automatic detection device for the tensile strength of steel wire of an aircraft tire according to claim 1, characterized in that: The side plate (13) has a second sliding groove (14) at its side end. A slider (15) is slidably connected in the second sliding groove (14). The slider (15) is connected to the mounting bracket (16). The mounting bracket (16) has a T-slot (1601) at its side end. A T-block (1701) is fixedly connected to the side end of the clamping mold (17). The T-block (1701) matches the T-slot (1601).

3. The automatic detection device for the tensile strength of steel wire of an aircraft tire according to claim 2, characterized in that: The lower end of the base plate (1) is fixedly connected to the mounting base (2), and the side end of the mounting base (2) is rotatably connected to the lead screw (3). The circumferential surface of the lead screw (3) is connected to the lead screw nut (4), and the lead screw nut (4) is connected to the fixing frame (9).

4. The automatic detection device for the tensile strength of steel wire of an aircraft tire according to claim 3, characterized in that: A motor (6) is fixedly connected to the lower end of the base plate (1), and the output end of the motor (6) is connected to the side end of the lead screw (3) by a gear chain (5).

5. The automatic detection device for the tensile strength of steel wire of an aircraft tire according to claim 4, characterized in that: The upper end of the base plate (1) is provided with multiple slots (8), the side end of the side frame (10) is fixedly connected to a rectangular plate (11), the lower end of the rectangular plate (11) is fixedly connected to a telescopic rod (25), the output end of the telescopic rod (25) is fixedly connected to a locking block (26), the circumferential surface of the output end of the telescopic rod (25) is sleeved with a third spring (27), and the locking block (26) is engaged with the slots (8).

6. The automatic detection device for the tensile strength of steel wire in aircraft tires according to claim 5, characterized in that: A support frame (21) is fixedly connected to the upper end of the base plate (1). A rotating rod (22) is connected to the upper end of the support frame (21). A second spring (24) is sleeved on the circumferential surface of the rotating rod (22). The side end of the second spring (24) is connected to the guide roller (23).

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