High-precision static balance testing device for aircraft tires

Abstract

This utility model discloses a high-precision static balance testing device for aircraft tires, including a static balancing machine. A support device is fixedly installed at the front end of the static balancing machine, and the support device is arranged in a ring. A positioning device is threaded into the front end of the static balancing machine and located at the side end of the support device. An aircraft tire is placed on the outer ring of the support device. The support device includes a first piston rod, a support rod, an L-shaped air cylinder, a second piston rod, and a hydraulic cylinder. The first piston rod is slidably inserted into the top end of the L-shaped air cylinder, the support rod is fixedly installed at the top end of the first piston rod, the second piston rod is slidably inserted into the front end of the L-shaped air cylinder, and the hydraulic cylinder is fixedly installed at the bottom end of the second piston rod. This utility model, through the setting of the support device and the positioning device, achieves the purpose of restricting and positioning aircraft tires of different sizes.

Description

Technical Field

[0001] This utility model relates to the field of testing device technology, specifically a high-precision static balance testing device for aircraft tire bodies. Background Technology

[0002] A static balancing machine is a device used to detect and correct static imbalances in rotating components (such as tires, flywheels, rotors, fan impellers, etc.). Its core function is to ensure that the mass distribution of an object is uniform when it is stationary, thus preventing vibration or eccentric loads during rotation.

[0003] For example, Chinese Patent Publication No. CN201501530U describes a balancing machine controlled by a hydraulic device. It includes a base and a base spindle connected sequentially from bottom to top; a spherical bearing is provided at the top of the base spindle, and a suspension spindle is fitted over the base spindle; a detection system and a supporting hydraulic cylinder are provided at the bottom of the suspension spindle; two opposing tapered sleeves are fitted on the outer surface of the suspension spindle, and a bearing cap is provided at the top of the suspension spindle; the top center and edge of the spherical bearing match the shapes of the bottom center and edge of the bearing cap, respectively; when the spherical bearing and the bearing cap are in close contact, a center sealing surface and an edge sealing surface are formed at the top center and edge of the spherical bearing, respectively, and a balancing groove is formed in the area between the center and the edge; an output channel communicating with the top side of the spherical bearing is provided between the base spindle and the suspension spindle, and an input channel communicating with the balancing groove is also provided inside the spherical bearing; the detection system, the supporting hydraulic cylinder, and the input and output channels are respectively connected to the hydraulic system.

[0004] During trial operation, existing static balancing machines can only balance tires of a specified size due to the different sizes of aircraft tires and the fact that they rely on the fit between the wheel hub and its internal components for support. Therefore, an improved device is needed to address these issues. Utility Model Content

[0005] The purpose of this invention is to provide a high-precision static balance testing device for aircraft tires to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a high-precision static balance testing device for aircraft tire carcasses, comprising a static balance machine, a support device fixedly installed at the front end of the static balance machine, and the support device being arranged in a ring, a positioning device threaded into the front end of the static balance machine, the positioning device being located at the side end of the support device, an aircraft tire being placed on the outer ring of the support device, the support device comprising a first piston rod, a support rod, an L-shaped air cylinder, a second piston rod, and a hydraulic cylinder, the first piston rod being slidably inserted into the top end of the L-shaped air cylinder, the support rod being fixedly installed at the top end of the first piston rod, the second piston rod being slidably inserted into the front end of the L-shaped air cylinder, and the hydraulic cylinder being fixedly installed at the bottom end of the second piston rod.

[0007] Preferably, the positioning device includes an adjusting bolt, a support base, a positioning bolt, a movable plate, and an extension base. The support base is rotatably mounted on the outer front end of the adjusting bolt and is arranged in a ring. The movable plate is slidably inserted into the support base away from the adjusting bolt. The extension base is fixedly mounted on the end of the movable plate opposite to the support base. The positioning bolt is threaded into the front end of the support base. When the hydraulic cylinder is running, it can drive the second piston rod into the interior of the L-shaped air cylinder, so that the first piston rod can support the support rod to move to a designated position, thereby contacting the inner wall of aircraft tires of different diameters. Furthermore, when the adjusting bolt is turned, it can drive the extension base and the support base to move, so that the aircraft tire can be squeezed into contact with the balance disc. Moreover, the extension base can be adjusted to facilitate the use of aircraft tires of different sizes to complete the work of limiting and positioning the aircraft tire.

[0008] Preferably, the static balancing machine has a balancing disc at its front end, and a central shaft is fixedly installed at the center of the front end of the balancing disc.

[0009] Preferably, the adjusting bolt is threaded into the center of the front end of the central shaft, and the L-shaped air cylinder and hydraulic cylinder are fixedly installed on the side surface of the balance disc, and the L-shaped air cylinder and hydraulic cylinder are both arranged in a ring.

[0010] Preferably, the front end of the central shaft is threaded, the top and bottom of the support base are marked with scale lines, and the top and bottom of the extension substrate are fixedly mounted with pointers.

[0011] Preferably, the interior of the L-shaped air cylinder is hollow, and a sealed cavity is formed between the first piston rod, the L-shaped air cylinder, and the second piston rod.

[0012] Compared with the prior art, the beneficial effects of this utility model are as follows: When in use, the hydraulic cylinder drives the second piston rod into the L-shaped air cylinder, allowing the first piston rod to support the support rod to move to a designated position, thus contacting the inner wall of aircraft tires of different diameters. Furthermore, by adjusting the screws, the extension plate and support frame can be displaced, allowing the aircraft tire to be squeezed into contact with the balance disc. The extension plate can also be adjusted to accommodate aircraft tires of different sizes, thus completing the task of positioning and limiting the aircraft tire. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the main structure of this utility model; Figure 2 This is a schematic diagram of the support device structure of this utility model; Figure 3 This is a schematic diagram of the positioning device structure of this utility model; Figure 4 This is a schematic diagram of the static balancing machine structure of this utility model.

[0014] In the diagram: 1-Support device, 2-Positioning device, 3-Static balancing machine, 4-Aircraft tire, 5-First piston rod, 6-Support rod, 7-L-shaped air cylinder, 8-Second piston rod, 9-Hydraulic cylinder, 10-Adjusting bolt, 11-Supporting base frame, 12-Positioning bolt, 13-Modible plate, 14-Extension base plate, 15-Balance disc, 16-Central shaft. Detailed Implementation

[0015] 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.

[0016] Please see Figure 1-4 An embodiment of this utility model provides a high-precision static balance testing device for aircraft tires, including a static balance machine 3. A support device 1 is fixedly installed at the front end of the static balance machine 3, and the support device 1 is arranged in a ring. A positioning device 2 is threaded into the front end of the static balance machine 3. The positioning device 2 is located at the side end of the support device 1. An aircraft tire 4 is placed on the outer ring of the support device 1. The support device 1 includes a first piston rod 5, a support rod 6, an L-shaped air cylinder 7, a second piston rod 8, and a hydraulic cylinder 9. The first piston rod 5 is slidably inserted into the top end of the L-shaped air cylinder 7. The support rod 6 is fixedly installed at the top end of the first piston rod 5. The second piston rod 8 is slidably inserted into the front end of the L-shaped air cylinder 7. The hydraulic cylinder 9 is fixedly installed at the bottom end of the second piston rod 8.

[0017] The positioning device 2 includes an adjusting bolt 10, a support base 11, a positioning bolt 12, a movable plate 13, and an extension base plate 14. The support base 11 is rotatably mounted on the front end of the outer ring of the adjusting bolt 10, and the support base 11 is arranged in a ring. The movable plate 13 is slidably inserted into the interior of the support base 11 away from the adjusting bolt 10. The extension base plate 14 is fixedly mounted on the end of the movable plate 13 opposite to the support base 11. The positioning bolt 12 is threaded into the front end of the support base 11. The extension base plate 14 can be adjusted to accommodate positioning of aircraft tires 4 of different diameters. First, the aircraft tire 4 is moved to the side end of the balance disc 15 until the inner ring of the aircraft tire 4 is vertically aligned with the support rod 6. Next, the hydraulic cylinder 9 is opened. The piston rod inside the hydraulic cylinder 9 is connected to the second piston rod 8, allowing the hydraulic cylinder 9 to drive the second piston rod 8 into the L-shaped air cylinder 7. This causes the first piston rod 5 to move the support rod 6 upwards until the support rod 6 contacts the inner ring of the aircraft tire 4. The four hydraulic cylinders 9 are controlled by the same controller, allowing them to operate synchronously. This ensures that all four support rods 6 simultaneously contact the inner ring of the aircraft tire 4, supporting its placement. Furthermore, a plastic sleeve is fixedly installed on the outer surface of the support rod 6 to prevent slippage when supporting the aircraft tire 4. Then, the adjusting bolt 10 is moved to the position relative to the central shaft 16. The front center contact is achieved through a threaded opening in the center of the central shaft 16, allowing the adjusting bolt 10 to be screwed into the interior of the central shaft 16. When the adjusting bolt 10 enters the interior of the central shaft 16, it can drive the support base 11 to move until the support base 11 presses the surface of the aircraft tire 4 into contact with the surface of the balance disc 15, thus restricting the aircraft tire 4 from the side. Furthermore, the movable plate 13 can slide and move inside the support base 11, allowing the position of the extension plate 14 to be extended. Then, the positioning bolt 12 is screwed to be fastened to the movable plate 13, thus restricting the extension plate 14 to a designated position for operation. When the extension plate 14 moves, it can drive the pointer on the surface of the support base 11 to the scale line. The upward displacement allows for precise control of the displacement of the extension base plate 14. Subsequently, after the aircraft tire 4 is constrained, the balance disc 15 is gently rotated to make the aircraft tire 4 rotate together with the balance disc 15. After the rotation stops freely, the uppermost point is the lightest point, and the most important point is the lowermost point. At this time, the unbalanced point can be marked. In addition, the above steps can be repeated 2-3 times to ensure the consistency of the results. After the aircraft tire 4 has been tested, the adjusting bolt 10 can be unscrewed from the inside of the central shaft 16 and then the hydraulic cylinder 9 can be turned on to drive the second piston rod 8 to move outward from the inside of the L-shaped air cylinder 7, so that the first piston rod 5 can drive the support rod 6 to move downward, thereby releasing the aircraft tire 4 and making it easy to remove the aircraft tire 4.

[0018] The static balancing machine 3 has a balancing disc 15 at its front end, and a central shaft 16 is fixedly installed at the center of the front end of the balancing disc 15 to support the rotation of the balancing disc 15.

[0019] The adjusting bolt 10 is threaded into the center of the front end of the central shaft 16. The L-shaped air cylinder 7 and the hydraulic cylinder 9 are fixedly installed on the side surface of the balance disc 15. The L-shaped air cylinder 7 and the hydraulic cylinder 9 are arranged in a ring to facilitate the support of the L-shaped air cylinder 7 and the hydraulic cylinder 9 for operation.

[0020] The front end of the central shaft 16 is threaded, the top and bottom of the support base 11 are marked with scale lines, and pointers are fixedly installed on the top and bottom of the extension base plate 14 to facilitate precise adjustment of the displacement of the extension base plate 14.

[0021] The L-shaped air cylinder 7 is hollow inside, and a sealed cavity is formed between the first piston rod 5, the L-shaped air cylinder 7 and the second piston rod 8, which facilitates the vertical movement of the support rod 6.

[0022] Working principle: In use, first move the aircraft tire 4 to the side of the balance disc 15 until the inner ring of the aircraft tire 4 is vertically aligned with the support rod 6. Then, open the hydraulic cylinder 9. The piston rod inside the hydraulic cylinder 9 is connected to the second piston rod 8, so that when the hydraulic cylinder 9 is running, it can drive the second piston rod 8 into the L-shaped air cylinder 7, so that the first piston rod 5 can drive the support rod 6 to move upward until the support rod 6 contacts the inner ring of the aircraft tire 4. The four hydraulic cylinders 9 are controlled by the same controller, so that the controller can open the four hydraulic cylinders 9 to operate synchronously. Four support rods 6 can simultaneously contact the inner ring of the aircraft tire 4, supporting the aircraft tire 4. Plastic sleeves are fixedly installed on the outer ring surface of the support rods 6 to prevent slippage when supporting the aircraft tire 4. Then, the adjusting bolt 10 is moved to contact the front center of the central shaft 16. The central shaft 16 has a threaded interior, allowing the adjusting bolt 10 to be screwed into the interior of the central shaft 16. When the adjusting bolt 10 enters the interior of the central shaft 16, it can drive the support base 11 to shift until the support base 11 presses the aircraft tire 4 against the flat surface. The surface contact of the balance plate 15 can restrict the aircraft tire 4 from the side. Furthermore, the movable plate 13 can slide and move inside the support frame 11, allowing the extension base plate 14 to be extended. The positioning bolt 12 is then tightened to secure it to the movable plate 13, thus restricting the extension base plate 14 to a designated position for operation. As the extension base plate 14 moves, it causes the pointer on the surface of the support frame 11 to move along the scale line, allowing precise control of the displacement of the extension base plate 14. After the aircraft tire 4 is restricted, the balance plate 15 is gently rotated to allow the aircraft tire 4 to move. The empty tire 4 rotates together with the balance disc 15. After the rotation stops freely, the uppermost point is the lightest point and the heaviest point is the lowest point. At this time, the unbalanced point can be marked. In addition, the above steps can be repeated 2-3 times to ensure the consistency of the results. After the aircraft tire 4 has been inspected, the adjusting bolt 10 can be unscrewed from the inside of the central shaft 16. Then, the hydraulic cylinder 9 is turned on to drive the second piston rod 8 to move outward from the inside of the L-shaped air cylinder 7, so that the first piston rod 5 can drive the support rod 6 to move downward, thereby releasing the aircraft tire 4 and making it easy to remove the aircraft tire 4, thus completing the work.

[0023] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A high-precision static balance testing device for aircraft tire carcasses, comprising a static balance machine (3), wherein a support device (1) is fixedly installed at the front end of the static balance machine (3), and the support device (1) is arranged in a ring, and a positioning device (2) is threadedly inserted at the front end of the static balance machine (3), the positioning device (2) being located at the side end of the support device (1), and an aircraft tire (4) is placed on the outer ring of the support device (1), characterized in that: The support device (1) includes a first piston rod (5), a support rod (6), an L-shaped air cylinder (7), a second piston rod (8), and a hydraulic cylinder (9). The first piston rod (5) is slidably inserted into the top end of the L-shaped air cylinder (7). The support rod (6) is fixedly installed at the top end of the first piston rod (5). The second piston rod (8) is slidably inserted into the front end of the L-shaped air cylinder (7). The hydraulic cylinder (9) is fixedly installed at the bottom end of the second piston rod (8).

2. The high precision static balancing detection device for the aircraft tire carcass according to claim 1, characterized in that: The positioning device (2) includes an adjusting bolt (10), a support base (11), a positioning bolt (12), a movable plate (13), and an extension base plate (14). The support base (11) is rotatably mounted on the front end of the outer ring of the adjusting bolt (10), and the support base (11) is arranged in a ring. The movable plate (13) is slidably inserted into the support base (11) away from the adjusting bolt (10). The extension base plate (14) is fixedly mounted on the end of the movable plate (13) away from the support base (11). The positioning bolt (12) is threaded into the front end of the support base (11).

3. The high precision static balancing detection device for the aircraft tire carcass according to claim 2, characterized in that: The static balancing machine (3) has a balancing disc (15) at its front end, and a central shaft (16) is fixedly installed at the center of the front end of the balancing disc (15).

4. The high precision static balancing detection device for the aircraft tire carcass according to claim 3, characterized in that: The adjusting bolt (10) is threaded into the center of the front end of the central shaft (16). The L-shaped air cylinder (7) and the hydraulic cylinder (9) are fixedly installed on the side surface of the balance disc (15), and the L-shaped air cylinder (7) and the hydraulic cylinder (9) are both arranged in a ring.

5. The high precision static balancing detection device for the aircraft tire carcass according to claim 4, characterized in that: The front end of the central shaft (16) is threaded, the top and bottom of the support base (11) are marked with scale lines, and the top and bottom of the extension base plate (14) are fixedly mounted with pointers.

6. The high precision static balancing detection device for the aircraft tire carcass according to claim 5, characterized in that: The L-shaped air cylinder (7) is hollow inside, and a sealed cavity is formed between the first piston rod (5), the L-shaped air cylinder (7), and the second piston rod (8).

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