An aircraft wing maintenance stand

Abstract

The application discloses an airplane wing maintenance platform for airplane maintenance, and belongs to the technical field of wing maintenance equipment, which comprises a movable maintenance platform, an automatic lifting device, a wing close structure and a nondestructive testing structure, the automatic lifting device is clamped on the movable maintenance platform, the wing close structure is arranged on the automatic lifting device, the wing close structure is lifted along with the lifting of the automatic lifting device, and the nondestructive testing structure is arranged on the wing close structure. In order to solve the problems of low automation, high dependence on detection personnel and easy damage to the surface coating of the wing of the current wing maintenance equipment, the present application provides an airplane wing maintenance platform, which effectively solves the problems of low automation, insufficient positioning accuracy, single detection function and easy damage to the surface coating of the wing of the traditional wing maintenance equipment.

Description

Technical Field

[0001] This invention belongs to the technical field of wing maintenance equipment, specifically referring to a wing maintenance platform for aircraft maintenance. Background Technology

[0002] As a critical aerodynamic component of aircraft, the regular inspection and maintenance of aircraft wings is a core element in ensuring flight safety. Currently, the wing inspection methods commonly used in the aviation maintenance field mainly rely on fixed inspection platforms, hydraulic lifting platforms, or manually erected scaffolding systems. These traditional devices have significant limitations in terms of structural design and functional integration: they typically lack intelligent positioning capabilities and cannot adaptively adjust to the actual curved contours of the wing, resulting in difficulties in achieving an ideal fit between the inspection equipment and the wing surface. While some improvements have been made in existing technologies, such as using sliding tracks and contour frames to partially adapt to the wing shape, or using lifting platforms with detachable guardrails to ensure the safety of maintenance personnel, these solutions still do not fundamentally solve the integration problem of precise positioning and intelligent inspection.

[0003] In practice, maintenance personnel often need to repeatedly adjust the equipment position based on experience and determine the inspection distance and angle manually. This process is not only time-consuming and labor-intensive, but also highly susceptible to blind spots due to human error. Furthermore, traditional non-destructive testing equipment is mostly a standalone device, not integrated with the maintenance platform, resulting in a fragmented inspection process that requires multiple positioning and installation steps, severely impacting maintenance efficiency and reliability. Especially when dealing with different aircraft models and wings with varying curvatures, the adaptability of existing equipment is clearly insufficient, failing to achieve rapid, accurate positioning and comprehensive inspection. This has become a technical bottleneck restricting the improvement of aircraft maintenance quality and efficiency. Summary of the Invention

[0004] In response to the above situation, and to address the problems of low automation, high dependence on inspection personnel, and the risk of mechanical damage to the wing surface coating caused by inspection equipment in current wing maintenance equipment, this invention provides an aircraft maintenance wing inspection platform, which effectively solves the problems of low automation, insufficient positioning accuracy, limited inspection functions, and easy damage to the wing surface coating caused by traditional wing maintenance equipment.

[0005] The technical solution adopted by the present invention is as follows: The present invention provides an aircraft wing inspection platform, including a mobile inspection platform, an automatic lifting device, a wing proximity structure, and a non-destructive testing structure. The automatic lifting device is engaged on the mobile inspection platform, the wing proximity structure is mounted on the automatic lifting device and rises with the automatic lifting device, and the non-destructive testing structure is mounted on the wing proximity structure to perform flaw detection operations on the aircraft wing. The mobile inspection platform can be towed to the underside of the aircraft wing by a shuttle vehicle.

[0006] Furthermore, the automatic lifting device includes a lifting box, an acoustic locator, lead screw A, lead screw B, lifting bracket A, lifting bracket B, nut A, nut B, screw groove A, screw groove B, hinge plate A, hinge plate B, and a central positioning bracket. The lifting box is placed on the top wall of the mobile maintenance platform, the acoustic locator is installed on the wing's close-fitting structure, and both screw groove A and screw groove B are placed inside the lifting box. Lead screw A and lead screw B are engaged and rotated within screw groove A and screw groove B, respectively. Nut A and nut B are engaged and slide on lead screw A and lead screw B, respectively, and are engaged and slide within screw groove A and screw groove B, respectively. The lifting bracket... One end of support A and lifting bracket B is hinged to nuts A and B, respectively. Hinge plates A and B are hinged to the other ends of lifting brackets A and B, respectively. Lifting brackets A and B are cross-connected, and a locking center positioning bracket is located at the intersection of lifting brackets A and B. Lead screws A and B are both driven by motors. A central controller a is located on the mobile inspection platform. The acoustic locator is signal-connected to central controller a, and central controller a is electrically connected to the motor. After the mobile inspection platform moves to below the wing, the acoustic locator determines the height difference between the wing and the equipment and sends a signal to central controller a. Central controller a controls the motor to raise hinge plates A and B. As the wing rises closer to the structure, the time for the acoustic locator to receive the reflected signal shortens, thereby calculating the distance between the detection equipment and the wing in real time. When the distance reaches a preset value, central controller a controls the motor to stop rotating.

[0007] Furthermore, in order to improve the stability of lifting bracket A and lifting bracket B and ensure that the wing close to the structure can be raised stably, bracket grooves are provided on the side wall of the lifting box, and the central positioning bracket engages and slides within the bracket grooves.

[0008] Furthermore, the wing proximity structure includes a lifting plate, an angle adjustment bracket, a laser distance sensor, a screw groove c, a ball screw c, a nut connecting rod c, a channel steel structure, a screw groove d, a ball screw d, and a nut connecting rod d. The lifting plate is engaged and slidably connected to the automatic lifting device. The angle adjustment bracket is engaged and rotated on the lifting plate. The screw groove c is fixedly connected to the angle adjustment bracket. The ball screw c is engaged and rotated within the screw groove c. The nut connecting rod c is engaged and slid within the screw groove c, and is also engaged and connected to the nut connecting rod c. The screw groove d is fixedly installed on the lifting plate and is engaged and rotated with the angle adjustment bracket on the screw groove. When the angle adjustment bracket rotates, it drives the screw groove c to rotate, while the screw groove d remains fixed. The ball screw d... The lead screw rotates within the groove d, and the nut connecting rod d is engaged and connected to the ball screw d, while the nut connecting rod d slides within the groove d. Channel steel structures are respectively provided on the nut connecting rod d and the nut connecting rod c. The laser distance sensor is installed on the side wall of the channel steel structure. The angle adjustment bracket, ball screw c, and ball screw d are all driven by motors. The laser distance sensor detects whether the channel steel structure is horizontal with the wing. When the wing and the channel steel structure are not parallel, or the distance between them exceeds a preset range, the laser distance sensor sends a signal to the central controller a. The central controller a controls the motors connected to the angle adjustment bracket, ball screw c, and ball screw d to adjust the angle of the channel steel structure and the distance between it and the wing, ensuring stable detection by the equipment.

[0009] Furthermore, the bottom wall of the lifting plate is provided with a connecting piece slot, and the hinge piece A and hinge piece B respectively engage and slide within the connecting piece slot. The acoustic positioner is fixedly installed on the top wall of the lifting plate.

[0010] Furthermore, the non-destructive testing structure includes a rack, a gear, a limiting clamp, a clamp slot, an equipment mounting plate, a detection distance adjusting screw, a screw slot, a push nut, and a testing work plate. The rack is disposed within the channel steel structure, and the gear meshes with the rack. The clamp slot is disposed on the inner wall of the channel steel structure, and the limiting clamp slides within the clamp slot. The gear rotates within the limiting clamp, and the equipment mounting plate is fixedly mounted on the limiting clamp. The gear is driven by a motor. The screw slot is fixedly disposed on the upper wall of the equipment mounting plate, and the detection distance adjusting screw rotates within the screw slot. The push nut slides within the screw slot and is threadedly connected to the detection distance adjusting screw. The testing work plate is fixedly connected to the push nut. After the channel steel structure is parallel to the wing, the central controller A simultaneously sends an electrical signal to the motor connected to the detection distance adjusting screw, causing the motor to operate, the detection distance adjusting screw to rotate, and the testing work plate to move towards the wing.

[0011] Furthermore, the non-destructive testing structure also includes a liquid reservoir, a hydraulic sensor, a central controller b, a dust removal duct, and an ultrasonic flaw detector. The liquid reservoir is fixedly mounted on the testing work plate, and the hydraulic sensor is located inside the liquid reservoir, capturing changes in hydraulic pressure within the reservoir. The central controller b is fixedly mounted on the upper wall of the equipment mounting plate, and the dust removal duct and ultrasonic flaw detector are also fixedly mounted on the testing work plate. Using a non-contact method, the dust removal duct removes adhering materials from the wing surface to avoid damaging the wing surface coating. The ultrasonic flaw detector then detects cracks on the upper surface of the wing. The liquid reservoir moves along the wing edge; when a gap appears in the wing, the hydraulic pressure inside the reservoir drops, which is captured by the hydraulic sensor and uploaded to the central controller b, which then transmits the data to the display.

[0012] Furthermore, the detection work plate is composed of a flat plate, clamp a, clamp b and clamp c, the liquid reservoir is set at the junction of clamp b and clamp c, and the liquid reservoir is set in a fan-shaped structure, and the liquid reservoir array is on clamp b and clamp c.

[0013] This solution provides an aircraft wing maintenance platform, the advantages of which are as follows:

[0014] (1) By combining the mobile inspection platform with the automatic lifting device, the equipment can be quickly positioned and its height can be adaptively adjusted under the wing. The acoustic positioner detects the distance to the wing in real time, and the central controller automatically controls the lifting process, which significantly improves the positioning accuracy and operating efficiency and reduces the reliance on manual experience;

[0015] (2) The wing-fitting structure employs a laser distance sensor and an angle adjustment bracket, which can automatically adjust the angle and distance of the detection equipment according to the actual curvature of the wing, ensuring that the channel steel structure remains parallel to the wing surface. This structure effectively improves the fit between the detection equipment and the wing, and is suitable for wings of different models and curvatures;

[0016] (3) The non-destructive testing structure integrates an ultrasonic flaw detector, a dust removal duct, and a hydraulic sensing reservoir, enabling non-contact testing and cleaning and avoiding damage to the wing coating. By identifying wing edge defects through hydraulic changes and combining real-time data uploads, the comprehensiveness and reliability of the testing are improved, realizing intelligent and integrated wing maintenance. Attached Figure Description

[0017] Figure 1 A perspective view of an aircraft wing maintenance platform provided by the present invention;

[0018] Figure 2 This is a schematic diagram of the internal structure of the automatic lifting device;

[0019] Figure 3A bottom-view perspective view of the automatic lifting device;

[0020] Figure 4 This is a structural diagram of the wing close to the structure.

[0021] Figure 5 A bottom-view perspective of the non-destructive testing structure;

[0022] Figure 6 This is a schematic diagram of the internal structure of a non-destructive testing structure.

[0023] Figure 7 This is a schematic diagram of the hydraulic sensor structure inside the reservoir.

[0024] Figure 8 for Figure 6 A magnified view of part A in the middle;

[0025] Figure 9 Here is a flowchart of the operation of the acoustic locator;

[0026] Figure 10 This is a flowchart of the laser distance sensor operation.

[0027] Figure 11 Hydraulic sensor operation flowchart.

[0028] Among them, 1. Mobile inspection platform, 2. Automatic lifting device, 3. Wing proximity structure, 4. Non-destructive testing structure, 5. Lifting box, 6. Acoustic positioner, 7. Lead screw A, 8. Lead screw B, 9. Lifting bracket A, 10. Lifting bracket B, 11. Nut A, 12. Nut B, 13. Screw groove A, 14. Screw groove B, 15. Hinge plate A, 16. Hinge plate B, 17. Center positioning bracket, 18. Central controller a, 19. Lifting plate, 20. Angle adjustment bracket, 21. Laser distance sensor, 22. Lead screw groove c, 23. Ball screw c, 24. 25. Nut connecting rod c; 26. Channel steel structure; 27. Screw groove d; 28. Ball screw d; 29. ​​Nut connecting rod d; 30. Connecting plate groove; 31. Rack; 32. Gear; 33. Limiting clamp; 34. Clamping plate groove; 35. Equipment mounting plate; 36. Detection distance adjusting screw; 37. Screw groove; 38. Push nut; 39. Detection work plate; 40. Liquid reservoir; 41. Hydraulic sensor; 42. Central controller b; 43. Dust removal duct; 44. Ultrasonic flaw detector; 45. Flat plate; 46. Clamping plate a; 47. Clamping plate c.

[0029] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used together with the embodiments of the invention to explain the invention and do not constitute a limitation thereof. Detailed Implementation

[0030] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0031] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0032] like Figures 1-11 As shown, the present invention provides an aircraft wing inspection platform, including a mobile inspection platform 1, an automatic lifting device 2, a wing proximity structure 3, and a non-destructive testing structure 4. The automatic lifting device 2 is engaged on the mobile inspection platform 1, the wing proximity structure 3 is disposed on the automatic lifting device 2, and the wing proximity structure 3 rises as the automatic lifting device 2 rises. The non-destructive testing structure 4 is disposed on the wing proximity structure 3.

[0033] The automatic lifting device 2 includes a lifting box 5, an acoustic positioner 6, lead screws A7 and B8, lifting brackets A9 and B10, nuts A11 and B12, screw grooves A13 and B14, hinge plates A15 and B16, and a center positioning bracket 17. The lifting box 5 is placed on the top wall of the mobile maintenance platform 1. The acoustic positioner 6 is set on the wing proximity structure 3. Screw grooves A13 and B14 are both placed inside the lifting box 5. Lead screws A7 and B8 are engaged and rotated in screw grooves A13 and B14, respectively. Nuts A11 and B12 are engaged and slide on lead screws A7 and B8, respectively. 12 are respectively engaged and slidable in screw grooves A13 and B14. One end of lifting bracket A9 and lifting bracket B10 is respectively hinged to nut A11 and nut B12. Hinge piece A15 and hinge piece B16 are respectively hinged to the other end of lifting bracket A9 and lifting bracket B10. Lifting bracket A9 and lifting bracket B10 are cross-connected. A center positioning bracket 17 is provided at the intersection of lifting bracket A9 and lifting bracket B10. Screw A7 and screw B8 are both driven by motor. At the same time, a central controller a18 is provided on the mobile maintenance platform 1. The acoustic positioner 6 is signal-connected to the central controller a18. The central controller a18 is electrically connected to the motor.

[0034] A bracket slide groove is provided on the side wall of the lifting box 5, and the central positioning bracket 17 is engaged and slid within the bracket slide groove.

[0035] The wing proximity structure 3 includes a lifting plate 19, an angle adjustment bracket 20, a laser distance sensor 21, a lead screw groove c22, a ball screw c23, a nut connecting rod c24, a channel steel structure 25, a lead screw groove d26, a ball screw d27, and a nut connecting rod d28. The lifting plate 19 is engaged and slidably connected to the automatic lifting device 2. The angle adjustment bracket 20 is engaged and rotates on the lifting plate 19. The lead screw groove c22 is fixedly connected to the angle adjustment bracket 20. The ball screw c23 is engaged and rotates within the lead screw groove c22. The nut connecting rod c24 is engaged and slides within the lead screw groove c22. 3 is engaged with the nut connecting rod c24. The screw groove d26 is fixedly installed on the lifting plate 19 and engages with the angle adjustment bracket 20 on the screw groove for rotation. The ball screw d27 is engaged and rotates in the screw groove d26. The nut connecting rod d28 is engaged with the ball screw d27 and engages and slides in the screw groove d26. The nut connecting rod d28 and the nut connecting rod c24 are respectively provided with channel steel structures 25. The laser distance sensor 21 is set on the side wall of the channel steel structure 25. The angle adjustment bracket 20, the ball screw c23 and the ball screw d27 are all driven by a motor.

[0036] The bottom wall of the lifting plate 19 is provided with a connecting piece slot 29, and the hinge piece A15 and the hinge piece B16 respectively engage and slide in the connecting piece slot 29. The acoustic positioner 6 is fixedly installed on the top wall of the lifting plate 19.

[0037] The non-destructive testing structure 4 includes a rack 30, a gear 31, a limiting clamp 32, a clamp groove 33, an equipment mounting plate 34, a detection distance adjusting screw 35, a screw groove 36, a push nut 37, and a testing work plate 38. The rack 30 is set inside the channel steel structure 25, and the gear 31 meshes with the rack 30. The clamp groove 33 is set on the inner wall of the channel steel structure 25. The limiting clamp 32 engages and slides on the clamp groove 33, and the gear 31 engages and rotates on the limiting clamp 32. The equipment mounting plate 34 is fixedly installed on the limiting clamp 32, and the gear 31 is driven by a motor. The screw groove 36 is fixedly set on the upper wall of the equipment mounting plate 34. The detection distance adjusting screw 35 engages and rotates in the screw groove 36, and the push nut 37 slides in the screw groove 36 and is threadedly connected to the detection distance adjusting screw 35. The testing work plate 38 is fixedly connected to the push nut 37.

[0038] The non-destructive testing structure 4 also includes a liquid reservoir 39, a hydraulic sensor 40, a central controller b41, a dust removal duct 42, and an ultrasonic flaw detector 43. The liquid reservoir 39 is fixedly mounted on the testing work plate 38, the hydraulic sensor 40 is mounted inside the liquid reservoir 39, the central controller b41 is fixedly mounted on the upper wall of the equipment mounting plate 34, the dust removal duct 42 is fixedly mounted on the testing work plate 38, and the ultrasonic flaw detector 43 is fixedly mounted on the testing work plate 38.

[0039] The detection work plate 38 is composed of a flat plate 44, a clamping plate a45, a clamping plate b46 and a clamping plate c47. The liquid storage bladder 39 is set at the junction of the clamping plate b46 and the clamping plate c47, and the liquid storage bladder 39 is designed as a fan-shaped structure. The liquid storage bladder 39 is arrayed on the clamping plate b46 and the clamping plate c47.

[0040] In practical use, the mobile inspection platform 1 is moved to the area under the wing of the passenger aircraft via a shuttle vehicle. If it is necessary to raise the inspection equipment, the lifting plate 19 is moved to the area under the wing. The acoustic locator 6 sends a signal to the bottom wall of the wing. After the signal is reflected by the wing, it receives the signal and transmits it to the central controller a18. The central controller a18 calculates the height difference and controls the motors connected to the lead screws A7 and B8 to be energized. The lead screws A7 and B8 rotate, and the nuts A11 and B12 slide in the screw grooves A13 and B14, respectively. Due to the structural limitation of the central positioning bracket 17, the top height of the lifting brackets A9 and B10 is raised, and the lifting plate 19 is raised.

[0041] During the process of raising the lifting plate 19, the acoustic positioner 6 continuously sends and receives signals and transmits them to the central controller a18 to calculate the distance between the lifting plate 19 and the wing in real time. When the distance between the lifting plate 19 and the wing is shortened to the predetermined value in the central controller a18, the central controller a18 sends a stop signal to the motors connected to the lead screws A7 and B8, and the height of the lifting plate 19 is fixed.

[0042] At this point, the channel steel structure 25 is horizontal with the edge of the wing. Then, it is necessary to make the channel steel structure 25 parallel with the edge of the wing so that the testing equipment can detect along the edge of the wing. One of the two sets of channel steel structures 25 is parallel to one side of the wing, while the other set of channel steel structures 25 is not yet parallel to the other side of the wing. The angle of the non-parallel channel steel structures 25 needs to be adjusted.

[0043] After the two sets of laser distance sensors 21 at both ends of the channel steel structure 25 emit light signals to the wing, the signals are reflected by the wing and then collected by the laser distance sensors 21. The signals are then transmitted to the central controller a18. The central controller a18 calculates the straight-line distance between the two sets of laser distance sensors 21 and the wing. Based on the distance difference, the motor connected to the angle adjustment bracket 20 is controlled to work. The angle adjustment bracket 20 rotates, and the laser distance sensors 21 transmit signals in real time until the distance between the two sets of laser distance sensors 21 and the wing is the same. At this time, the channel steel structure 25 is parallel to the edge of the wing.

[0044] Subsequently, the motor connected to ball screws d27 and c23 operates, causing ball screws d27 and c23 to rotate. Nut connecting rods d28 and c24 move towards the wing. As the detection plate 38 approaches the wing, the reservoir 39 is pressed by the wing. The hydraulic sensor 40 receives the pressure and transmits the relevant signal to the central controller b41. The central controller b41 stores pressure values ​​within a specific range. When the value obtained by the hydraulic sensor 40 reaches the predetermined range, ball screws d27 and c23 stop rotating.

[0045] Then, the liquid reservoir 39 was slid along the edge of the wing to check for cracks or dents on the edge of the wing.

[0046] When gear 31 is rotated, the limiting clamp 32 slides along the clamp groove 33, and multiple sets of liquid storage bladders 39 slide along the wing. When the liquid storage bladder 39 moves to the concave area of ​​the wing, the pressure of the part of the liquid storage bladder 39 that is pressed decreases, the pressure inside the liquid storage bladder 39 decreases, the value of the hydraulic sensor 40 changes, and the central controller b41 acquires and uploads the relevant data.

[0047] Dust removal duct 42 removes dust from above the wing, and ultrasonic flaw detector 43 performs crack detection on the wing and uploads real-time data.

[0048] It should be noted that, in this document, the terms “comprising,” “including,” or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0049] The present invention and its embodiments have been described above. This description is not restrictive, and the accompanying drawings are only one embodiment of the present invention; the actual structure is not limited thereto. In conclusion, if those skilled in the art are inspired by this description and design similar structures and embodiments without departing from the spirit of the invention, such designs should fall within the protection scope of the present invention.

Claims

1. A wing maintenance platform for aircraft maintenance, characterized in that: The system includes a mobile inspection platform (1), an automatic lifting device (2), a wing-adjacent structure (3), and a non-destructive testing structure (4). The automatic lifting device (2) is engaged on the mobile inspection platform (1), and the wing-adjacent structure (3) is mounted on the automatic lifting device (2). The wing-adjacent structure (3) rises as the automatic lifting device (2) rises. The non-destructive testing structure (4) is mounted on the wing-adjacent structure (3). The non-destructive testing structure (4) includes a rack (30), a gear (31), a limiting clamp (32), and a clamp. The equipment includes a plate slot (33), an equipment mounting plate (34), a detection distance adjustment screw (35), a screw slot (36), a push nut (37), and a detection work plate (38). The rack (30) is set inside the wing-adjacent structure (3), and the gear (31) meshes with the rack (30). The clamping plate slot (33) is set on the wing-adjacent structure (3), and the limiting clamping plate (32) engages and slides on the clamping plate slot (33). The gear (31) engages and rotates on the limiting clamping plate (32). The equipment mounting plate (35)... 4) The gear (31) is fixedly installed on the limiting clamp (32), and is driven by a motor. The lead screw groove (36) is fixedly installed on the upper wall of the equipment mounting plate (34). The detection distance adjusting lead screw (35) is engaged and rotated in the lead screw groove (36). The push nut (37) slides in the lead screw groove (36) and is threadedly connected to the detection distance adjusting lead screw (35). The detection working plate (38) is fixedly connected to the push nut (37). The non-destructive testing structure (4) also includes a storage The equipment includes a liquid reservoir (39), a hydraulic sensor (40), a central controller b (41), a dust removal duct (42), and an ultrasonic flaw detector (43). The liquid reservoir (39) is fixedly mounted on the testing work plate (38). The hydraulic sensor (40) is located inside the liquid reservoir (39). The central controller b (41) is fixedly mounted on the upper wall of the equipment mounting plate (34). The dust removal duct (42) is fixedly mounted on the testing work plate (38). The ultrasonic flaw detector (43) is fixedly mounted on the testing work plate (38).The wing proximity structure (3) includes a lifting plate (19), an angle adjustment bracket (20), a laser distance sensor (21), a screw groove c (22), a ball screw c (23), a nut connecting rod c (24), a channel steel structure (25), a screw groove d (26), a ball screw d (27), and a nut connecting rod d (28). The lifting plate (19) is engaged and slidably connected to the automatic lifting device (2). The angle adjustment bracket (20) is engaged and rotated on the lifting plate (19). The screw groove c (22) is fixedly connected to the angle adjustment bracket (20). The ball screw c (23) is engaged and rotated in the screw groove c (22). The nut connecting rod c (24) is engaged and slid in the screw groove c (22). c(23) is engaged with nut connecting rod c(24). The screw groove d(26) is fixedly installed on the lifting plate (19) and engaged with the angle adjustment bracket (20) to rotate on the screw groove. The ball screw d(27) is engaged and rotated in the screw groove d(26). The nut connecting rod d(28) is engaged with the ball screw d(27) and engaged and slid in the screw groove d(26). The nut connecting rod d(28) and the nut connecting rod c(24) are respectively provided with channel steel structures (25). The laser distance sensor (21) is set on the side wall of the channel steel structure (25). The angle adjustment bracket (20), ball screw c(23) and ball screw d(27) are all driven by a motor.

2. The wing maintenance platform for aircraft maintenance according to claim 1, characterized in that: The detection work plate (38) is composed of a flat plate (44), a clamping plate a (45), a clamping plate b (46) and a clamping plate c (47). The liquid storage bladder (39) is set at the junction of the clamping plate b (46) and the clamping plate c (47), and the liquid storage bladder (39) is set as a fan-shaped structure. The liquid storage bladder (39) is arrayed on the clamping plate b (46) and the clamping plate c (47).

3. The wing maintenance platform for aircraft maintenance according to claim 2, characterized in that: The automatic lifting device (2) includes a lifting box (5), an acoustic locator (6), a lead screw A (7), a lead screw B (8), a lifting bracket A (9), a lifting bracket B (10), a nut A (11), a nut B (12), a screw groove A (13), a screw groove B (14), a hinge plate A (15), a hinge plate B (16), and a center positioning bracket (17). The lifting box (5) is placed on the top wall of the mobile maintenance platform (1). The acoustic locator (6) is set on the lifting plate (19). The screw groove A (13) and the screw groove B (14) are both placed inside the lifting box (5). The lead screw A (7) and the lead screw B (8) are engaged and rotated in the screw groove A (13) and the screw groove B (14), respectively. The nut A (11) and the nut B (12) are engaged and slid on the lead screw A (7) and the lead screw B (8), respectively. 11) The screw and nut B (12) are engaged and slid in the screw groove A (13) and screw groove B (14) respectively. One end of the lifting bracket A (9) and lifting bracket B (10) is hinged to nut A (11) and nut B (12) respectively. The hinge piece A (15) and hinge piece B (16) are hinged to the other end of lifting bracket A (9) and lifting bracket B (10) respectively. The lifting bracket A (9) and lifting bracket B (10) are cross-connected. A center positioning bracket (17) is provided at the intersection of lifting bracket A (9) and lifting bracket B (10). The lead screw A (7) and lead screw B (8) are both driven by a motor. At the same time, a central controller a (18) is provided on the mobile maintenance platform (1). The acoustic locator (6) is signal-connected to the central controller a (18). The central controller a (18) is electrically connected to the motor.

4. The wing maintenance platform for aircraft maintenance according to claim 3, characterized in that: The bottom wall of the lifting plate (19) is provided with a connecting piece slot (29), and the hinge piece A (15) and hinge piece B (16) respectively engage and slide in the connecting piece slot (29).

5. The wing maintenance platform for aircraft maintenance according to claim 4, characterized in that: The side wall of the lifting box (5) is provided with a bracket slide groove, and the central positioning bracket (17) engages and slides within the bracket slide groove.

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