High-precision aerodynamic floating centering mechanism for aircraft wheel hub

Abstract

This application discloses a high-precision pneumatic floating centering mechanism for aircraft wheel hubs, relating to the field of aircraft wheel hubs. The mechanism includes a flaw detector, which has a clamping assembly for fixing the rotation of the aircraft wheel hub. The clamping assembly includes a groove on the upper surface of the flaw detector body. This application utilizes the cooperative arrangement of an L-shaped support plate, a cylinder, and a conical pressure block. In use, the aircraft wheel hub is placed on a placement plate. The connecting plate is lowered by activating the cylinder, and the conical pressure block is inserted into the inner hole of the aircraft wheel hub, causing the aircraft wheel hub to move on the placement plate. This aligns the aircraft wheel hub with the placement plate and the conical pressure block in a concentric circle. After centering the aircraft wheel hub, the conical pressure block is pressed down further, bringing the aircraft wheel hub abutting between the conical pressure block and the placement plate. This minimizes the need for manual control of the locking mechanism to press down the pressure block when fixing the aircraft wheel hub, which is inconvenient and reduces work efficiency.

Description

Technical Field

[0001] This application relates to the field of aircraft wheel hubs, and in particular to a high-precision aircraft wheel hub aerodynamic floating centering mechanism. Background Technology

[0002] Aircraft wheel hub flaw detection is a non-destructive testing technique used to inspect aircraft wheel hubs to detect defects such as cracks and damage, ensuring flight safety. As a major load-bearing component during takeoff and landing, the wheel hub must withstand enormous impact forces and high-temperature friction (up to 260°C). Flaw detection can detect potential cracks in a timely manner, avoiding serious consequences such as air leakage and wheel hub explosion caused by fatigue cracks.

[0003] The invention patent with announcement number CN113804750B proposes an automatic flaw detection device for the surface of an aircraft wheel hub, including a mounting base, a turntable rotatably connected to the mounting base, a limiting device for fixing the position of the aircraft wheel hub, and a probe for flaw detection of the aircraft wheel hub; a horizontal drive component is mounted on the mounting base, a vertical drive component is fixedly connected to the horizontal drive component, a mounting frame is provided on the vertical drive component, and the probe is flexibly connected to the mounting frame so as to be able to swing around the connection point with the mounting frame.

[0004] One of the aforementioned automatic flaw detection devices for aircraft wheel hubs involves placing the aircraft wheel hub on a turntable, passing a tensioning shaft through the inner hole of the aircraft wheel hub, and clamping the aircraft wheel hub between a clamping block and the turntable using a locking device, thereby fixing the aircraft wheel hub on the turntable. However, when fixing the aircraft wheel hub, it is necessary to manually control the locking device to press down the clamping block, which is inconvenient and reduces work efficiency. Utility Model Content

[0005] To address the aforementioned issues, this application provides a high-precision aircraft hub aerodynamic floating centering mechanism.

[0006] The high-precision aircraft wheel hub aerodynamic floating centering mechanism provided in this application adopts the following technical solution:

[0007] A high-precision aircraft wheel hub pneumatic floating centering mechanism includes a flaw detector. The flaw detector is equipped with a clamping assembly for fixing the rotation of the aircraft wheel hub. The clamping assembly includes a groove formed on the upper surface of the flaw detector, and a placement plate is provided in the groove. A motor for driving the placement plate to rotate is installed in the flaw detector. An L-shaped support plate is fixedly connected to the upper surface of the flaw detector. A cylinder is fixedly connected to the upper surface of the L-shaped support plate. The output end of the cylinder passes through the L-shaped support plate and is fixedly connected to a connecting plate. A connecting rod is rotatably connected to the lower surface of the connecting plate. A conical pressure block is fixedly connected to the bottom end of the connecting rod. The conical pressure block is coaxially arranged with the placement plate. The placement plate is equipped with a sliding assembly to reduce the friction of the aircraft wheel hub moving on the telescopic placement plate.

[0008] By adopting the above technical solution, during use, the aircraft wheel hub is placed on the placement plate. The connecting plate is lowered by starting the cylinder, and the conical pressure block is inserted into the inner hole of the aircraft wheel hub. During this process, the conical pressure block contacts and presses against the side wall of the inner hole of the aircraft wheel hub. The friction between the aircraft wheel hub and the placement plate is reduced by the sliding component, allowing the aircraft wheel hub to move on the placement plate and align the aircraft wheel hub, the placement plate, and the conical pressure block with the same center. After centering the aircraft wheel hub, the conical pressure block is pressed down further, bringing the aircraft wheel hub abutting between the conical pressure block and the placement plate. Then, the placement plate is rotated by the motor, causing the aircraft wheel hub to rotate for flaw detection. This method avoids the problem of manually controlling the locking device to press down the pressure block when fixing the aircraft wheel hub, which is inconvenient and reduces work efficiency.

[0009] Preferably, the sliding assembly includes a cavity formed within the placement tray, a movable tray is provided within the cavity, and a plurality of support rods in an annular array are fixedly connected to the upper surface of the movable tray. The top ends of the support rods penetrate the top wall of the cavity and are rotatably connected to a first ball bearing.

[0010] By adopting the above technical solution, when the aircraft wheel hub is placed on the placement plate, the aircraft wheel hub comes into contact with the first ball bearing. The first ball bearing reduces the friction between the aircraft wheel hub and the placement plate, making it easier to center the aircraft wheel hub.

[0011] Preferably, electric push rods are fixedly connected to both sides of the placement tray within the groove, and a push ring is sleeved on the placement tray. The top ends of the electric push rods are fixedly connected to the push rings. Two annular array grooves are opened on the side wall of the placement tray, and sliders are slidably arranged in the grooves. One end of each slider is fixedly connected to the moving tray, and the other end of the slider is located above the push rings.

[0012] By adopting the above technical solution, after the aircraft wheel hub is positioned, the electric push rod is activated, causing it to retract and move the push ring downwards. This moves the push ring away from the slider, causing the slider to slide downwards and drive the moving plate downwards, allowing the first ball to slide into the cavity. Then, the conical pressure block continues to press down on the aircraft wheel hub, bringing the aircraft wheel hub abutting between the conical pressure block and the placement plate. This prevents the aircraft wheel hub from shaking on the placement plate due to the first ball when it is rotated.

[0013] Preferably, a plurality of positioning posts are fixedly connected inside the cavity, and the movable disk is sleeved on the positioning posts.

[0014] By adopting the above technical solution, the stability of the moving disk can be improved by using positioning columns to prevent shaking.

[0015] Preferably, the groove is provided with multiple guide rollers on both sides of the placement tray, and the two ends of the guide rollers are rotatably connected to the side walls of the groove.

[0016] By adopting the above technical solution, after the aircraft hub is placed on the guide roller, the aircraft hub is moved on the guide roller by pushing the aircraft hub, which makes it convenient to place the aircraft hub on the placement tray.

[0017] Preferably, a plurality of fixing rods are fixedly connected to the upper surface of the connecting plate, and the other end of the fixing rods passes through the L-shaped support plate and forms a sliding arrangement.

[0018] By adopting the above technical solution, the stability of the connecting plate during lifting and lowering can be improved by using a fixing rod.

[0019] Preferably, the lower surface of the placement tray is rotatably connected with a plurality of annular arrays of second balls, the second balls being in contact with the bottom wall of the groove.

[0020] By adopting the above technical solution, the second ball bearing can support the placement plate, preventing the placement plate from sticking to the bottom wall of the groove and reducing the friction between the placement plate and the bottom wall of the groove.

[0021] Preferably, each of the slide grooves is provided with a spring, one end of which is fixedly connected to the lower surface of the slider, and the other end of which is fixedly connected to the bottom wall of the slide groove.

[0022] By adopting the above technical solution, the spring can push the slider to move upward in the groove, preventing the slider from sliding downward and sticking to the push ring due to gravity when the electric push rod retracts. When the placement plate rotates, friction between the slider and the push ring will cause wear.

[0023] In summary, this application includes at least one of the following beneficial technical effects:

[0024] 1. This application utilizes the coordinated structure of an L-shaped support plate, a cylinder, and a conical pressure block. During use, the aircraft hub is placed on a placement plate. The connecting plate is lowered by the starting cylinder, and the conical pressure block is inserted into the inner hole of the aircraft hub. This process causes the conical pressure block to contact and press against the side wall of the inner hole of the aircraft hub. A sliding component reduces the friction between the aircraft hub and the placement plate, allowing the aircraft hub to move on the placement plate and align the aircraft hub, the placement plate, and the conical pressure block with the same center. After centering the aircraft hub, the conical pressure block is pressed down further, bringing the aircraft hub abutting between the conical pressure block and the placement plate. Then, a motor drives the placement plate to rotate, causing the aircraft hub to rotate for flaw detection. This method minimizes the inconvenience and reduced work efficiency associated with manually controlling the locking mechanism to press down the pressure block when fixing the aircraft hub.

[0025] 2. When placing the aircraft hub on the placement tray, the aircraft hub is brought into contact with the first ball bearing. The first ball bearing reduces the friction between the aircraft hub and the placement tray, facilitating the centering of the aircraft hub. After the aircraft hub is positioned, the electric push rod is activated, causing it to retract and move the push ring downwards. This moves the push ring away from the slider, causing the slider to slide downwards and dragging the moving tray downwards, allowing the first ball bearing to slide into the cavity. Then, the conical pressure block continues to press down on the aircraft hub, bringing the aircraft hub abutting between the conical pressure block and the placement tray. This prevents the aircraft hub from wobbling on the placement tray due to the first ball bearing when the aircraft hub is rotated. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the overall structure of a high-precision aircraft wheel hub aerodynamic floating centering mechanism according to an embodiment of this application;

[0027] Figure 2 This is a schematic diagram illustrating the interior of the flaw detector, which is a key feature of this application's embodiments.

[0028] Figure 3 The embodiments of this application mainly embody Figure 2 A schematic diagram of the enlarged structure of region A in the middle;

[0029] Figure 4 This is a schematic diagram illustrating the driving ring structure, which is the main feature of this application embodiment.

[0030] Reference numerals: 1. Flaw detector; 2. Groove; 3. Placement tray; 4. Motor; 5. L-shaped support plate; 6. Cylinder; 7. Connecting plate; 8. Connecting rod; 9. Conical pressure block; 10. Cavity; 11. Moving tray; 12. Support rod; 13. First ball bearing; 14. Electric push rod; 15. Push ring; 16. Slide groove; 17. Slider; 18. Positioning post; 19. Guide roller; 20. Fixed rod; 21. Second ball bearing; 22. Spring. Detailed Implementation

[0031] The following is in conjunction with the appendix Figures 1-4 This application will be described in further detail.

[0032] This application discloses a high-precision aircraft hub aerodynamic floating centering mechanism.

[0033] Reference Figure 1 , Figure 2 and Figure 3 A high-precision aircraft wheel hub pneumatic floating centering mechanism includes a flaw detector 1. The flaw detector 1 is equipped with a clamping assembly for fixing the rotation of the aircraft wheel hub. The clamping assembly includes a groove 2, a placement plate 3, a motor 4, an L-shaped support plate 5, a cylinder 6, a connecting plate 7, a connecting rod 8, and a conical pressure block 9.

[0034] A groove 2 is formed on the upper surface of the flaw detector 1. A placement plate 3 is set in the groove 2. A motor 4 is installed inside the flaw detector 1. The output end of the motor 4 passes through the flaw detector 1 and is fixedly connected to the placement plate 3. An L-shaped support plate 5 is fixedly connected to the upper surface of the flaw detector 1. A cylinder 6 is fixedly connected to the upper surface of the L-shaped support plate 5. The output end of the cylinder 6 passes through the L-shaped support plate 5 and is fixedly connected to the connecting plate 7. A connecting rod 8 is rotatably connected to the lower surface of the connecting plate 7. A conical pressure block 9 is fixedly connected to the bottom end of the connecting rod 8. The conical pressure block 9 is coaxially arranged with the placement plate 3. The placement plate 3 is provided with a sliding component to reduce the friction of the aircraft hub moving on the telescopic placement plate 3.

[0035] Reference Figure 2 and Figure 3 The sliding assembly includes a cavity 10 formed in the placement plate 3. A movable plate 11 is provided in the cavity 10. A plurality of support rods 12 in a ring array are fixedly connected to the upper surface of the movable plate 11. The top of the support rods 12 penetrates the top wall of the cavity 10 and is rotatably connected to a first ball bearing 13. When the aircraft wheel hub is placed on the placement plate 3, the aircraft wheel hub contacts the first ball bearing 13. The friction between the aircraft wheel hub and the placement plate 3 is reduced by the first ball bearing 13, which facilitates the centering of the aircraft wheel hub.

[0036] Reference Figure 2 , Figure 3 and Figure 4 Electric push rods 14 are fixedly connected to both sides of the placement plate 3 in the groove 2. The two electric push rods are started synchronously by the controller. A push ring 15 is sleeved on the placement plate 3. The top of the electric push rods 14 are fixedly connected to the push ring 15. Two annular array of sliding grooves 16 are opened on the side wall of the placement plate 3. A slider 17 is slidably arranged in the sliding groove 16. One end of the slider 17 is fixedly connected to the moving plate 11. The other end of the slider 17 is located above the push ring 15. After the aircraft wheel hub is adjusted to the correct position, the electric push rods 14 are started to retract, which moves the push ring 15 downward, moves the push ring 15 away from the slider 17, and causes the slider 17 to slide downward, which drives the moving plate 11 to slide downward, so that the first ball 13 slides into the cavity 10. Then the conical pressure block 9 continues to press down on the aircraft wheel hub, and the aircraft wheel hub is pressed against the conical pressure block 9 and the placement plate 3. This can prevent the aircraft wheel hub from shaking on the placement plate 3 due to the first ball 13 when the aircraft wheel hub is rotated.

[0037] Reference Figure 2 and Figure 3 Multiple positioning posts 18 are fixedly connected inside the cavity 10. The movable disk 11 is sleeved on the positioning posts 18. The positioning posts 18 can improve the stability of the movable disk 11 and prevent shaking.

[0038] Reference Figure 1The groove 2 is located on both sides of the placement tray 3 and is provided with multiple guide rollers 19. The two ends of the guide rollers 19 are rotatably connected to the side walls of the groove 2. After the aircraft hub is placed on the guide rollers 19, the aircraft hub is pushed to move on the guide rollers 19, which makes it convenient to place the aircraft hub on the placement tray 3.

[0039] Reference Figure 1 Multiple fixing rods 20 are fixedly connected to the upper surface of the connecting plate 7. The other end of the fixing rod 20 passes through the L-shaped support plate 5 and forms a sliding setting. The stability of the connecting plate 7 when it is raised or lowered can be improved by the fixing rods 20.

[0040] Reference Figure 3 The lower surface of the placement disk 3 is rotatably connected with a plurality of annular arrays of second ball bearings 21. The second ball bearings 21 are in contact with the bottom wall of the groove 2. The second ball bearings 21 can support the placement disk 3, prevent the placement disk 3 from sticking to the bottom wall of the groove 2, and reduce the friction between the placement disk 3 and the bottom wall of the groove 2.

[0041] Reference Figure 3 Each slide groove 16 is equipped with a spring 22. One end of the spring 22 is fixedly connected to the lower surface of the slider 17, and the other end of the spring 22 is fixedly connected to the bottom wall of the slide groove 16. The spring 22 can push the slider 17 to move upward in the slide groove 16, preventing the slider 17 from sliding downward and fitting with the push ring 15 due to gravity when the electric push rod 14 retracts. When the placement plate 3 rotates, the friction between the slider 17 and the push ring 15 causes wear.

[0042] The implementation principle of a high-precision aircraft wheel hub pneumatic floating centering mechanism according to an embodiment of this application is as follows: In use, the aircraft wheel hub is placed on the placement plate 3. The connecting plate 7 is lowered by the starting cylinder 6. During the insertion of the conical pressure block 9 into the inner hole of the aircraft wheel hub, the conical pressure block 9 contacts and presses against the side wall of the inner hole of the aircraft wheel hub. Simultaneously, the aircraft wheel hub contacts the first ball bearing 13. The first ball bearing 13 reduces the friction between the aircraft wheel hub and the placement plate 3, allowing the aircraft wheel hub to move on the placement plate 3, aligning the aircraft wheel hub, placement plate 3, and conical pressure block 9 at the same center. After centering the aircraft wheel hub, the starting cylinder... The electric push rod 14 retracts, moving the push ring 15 downwards, causing it to move away from the slider 17. This causes the slider 17 to slide downwards, pulling the moving disk 11 downwards, allowing the first ball bearing 13 to slide into the cavity 10. Then, the conical pressure block 9 continues to press down on the aircraft hub, bringing the hub abutting between the conical pressure block 9 and the placement disk 3. The motor 4 then drives the placement disk 3 to rotate, causing the aircraft hub to rotate for flaw detection. This method minimizes the need for manual control of the locking mechanism to press down the pressure block when fixing the aircraft hub, which is inconvenient and reduces work efficiency.

[0043] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A high-precision aircraft wheel hub pneumatic floating centering mechanism, comprising a flaw detector (1), wherein the flaw detector (1) is provided with a clamping assembly for fixing the rotation of the aircraft wheel hub, characterized in that: The clamping assembly includes a groove (2) formed on the upper surface of the flaw detector (1), a placement plate (3) is provided in the groove (2), a motor (4) for driving the placement plate (3) to rotate is installed in the flaw detector (1), an L-shaped support plate (5) is fixedly connected to the upper surface of the flaw detector (1), a cylinder (6) is fixedly connected to the upper surface of the L-shaped support plate (5), the output end of the cylinder (6) passes through the L-shaped support plate (5) and is fixedly connected to a connecting plate (7), a connecting rod (8) is rotatably connected to the lower surface of the connecting plate (7), a conical pressure block (9) is fixedly connected to the bottom end of the connecting rod (8), the conical pressure block (9) is coaxially arranged with the placement plate (3), and a sliding assembly is provided on the placement plate (3) to reduce the friction of the aircraft hub moving on the telescopic placement plate (3).

2. A high precision aerodynamic floatation centering mechanism for an aircraft wheel hub as defined in claim 1, characterized in that: The sliding assembly includes a cavity (10) opened in the placement plate (3), a movable plate (11) is provided in the cavity (10), and a plurality of support rods (12) in a ring array are fixedly connected to the upper surface of the movable plate (11). The top end of the support rod (12) passes through the top wall of the cavity (10) and is rotatably connected to a first ball bearing (13).

3. A high precision aircraft wheel hub aerodynamic float centering mechanism according to claim 2, wherein: Electric push rods (14) are fixedly connected to both sides of the placement plate (3) in the groove (2). A push ring (15) is sleeved on the placement plate (3). The top of the electric push rods (14) is fixedly connected to the push ring (15). Two annular array slide grooves (16) are opened on the side wall of the placement plate (3). A slider (17) is slidably arranged in the slide groove (16). One end of the slider (17) is fixedly connected to the moving plate (11), and the other end of the slider (17) is located above the push ring (15).

4. A high precision aircraft wheel hub aerodynamic float centering mechanism according to claim 3, wherein: Multiple positioning posts (18) are fixedly connected inside the cavity (10), and the movable disk (11) is sleeved on the positioning posts (18).

5. A high precision aircraft wheel hub aerodynamic float centering mechanism according to claim 4 wherein: The groove (2) is located on both sides of the placement plate (3) and is provided with multiple guide rollers (19). The two ends of the guide rollers (19) are rotatably connected to the side walls of the groove (2) respectively.

6. A high precision aircraft wheel hub aerodynamic float centering mechanism according to claim 5 wherein: Multiple fixing rods (20) are fixedly connected to the upper surface of the connecting plate (7), and the other end of the fixing rod (20) passes through the L-shaped support plate (5) and forms a sliding arrangement.

7. A high precision aircraft wheel hub aerodynamic float centering mechanism according to claim 6 wherein: The lower surface of the placement plate (3) is rotatably connected with a plurality of annular arrays of second balls (21), which are in contact with the bottom wall of the groove (2).

8. A high precision aircraft wheel hub aerodynamic float centering mechanism according to claim 7, wherein: Each of the slide grooves (16) is provided with a spring (22). One end of the spring (22) is fixedly connected to the lower surface of the slider (17), and the other end of the spring (22) is fixedly connected to the bottom wall of the slide groove (16).

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