A large curved skin hoisting tool for freighter civil aircraft

Abstract

The utility model relates to a kind of hoisting tools for large curved skin of freighter, relate to aircraft maintenance technical field, by sliding sleeve along sucker support sliding, so that each vacuum chuck is adjusted to place according to the curvature of aircraft skin, ensure that subsequent vacuum chuck can be closely adsorbed with aircraft skin 13.Vacuum chuck is adjusted to place by sliding sleeve locking device, and sliding sleeve is locked and fixed relative to sucker support, so as to ensure that vacuum chuck does not change position, vacuum generating device works, so that each vacuum chuck generates vacuum, under the action of negative pressure, vacuum chuck is adsorbed and fixed on the surface of aircraft skin, finally lifting equipment drives whole hoisting tool to move up, realize the hoisting of aircraft skin.It is suitable for hoisting of large curved skin of freighter, improve the efficiency of freight system modification, reduce the deformation and knock of skin curved surface in manual handling process, ensure the smooth hoisting of large curved skin.

Description

Technical Field

[0001] This utility model relates to the field of aircraft maintenance technology, specifically to a lifting tool for large curved skins of cargo civil aircraft. Background Technology

[0002] With the development of technology and large-scale manufacturing, large, one-piece aircraft skins are gradually replacing multi-piece aircraft skins and are widely used in cargo aircraft. While one-piece aircraft skins optimize the aircraft's aerodynamic shape and strengthen its structural strength, they also bring new problems, one of which is the exponentially increased difficulty of lifting. Traditional skin loading and unloading relies on manual labor, with personnel scattered around the skin for lifting and moving. Due to uneven force distribution and repeated bending, the skin is prone to deformation and impacts. Using skin lifting tools can optimize the lifting process and ensure the curvature and smoothness of the skin surface.

[0003] Currently, the single-piece skin used in cargo aircraft mainly consists of four skins: one upper skin, two cargo hold middle skins, and one lower skin. To achieve compatible lifting of different types of skins, the suction cup brackets and suction cups need to adopt a movable layout.

[0004] Patent application CN 120364557 A discloses a suction cup type curved skin lifting device. It includes a lifting longitudinal beam, a frame connected to the longitudinal beam, and two crossbeams on the frame. Each crossbeam has a suction cup connected to both ends. An adjustment component is connected to the suction cups, allowing adjustment of the suction cup angle. This device can lift the machine head skin. Because it lacks an additional negative pressure device, it relies solely on the suction cups to adhere the skin. Its reliability is no longer applicable when dealing with large skins, especially the curved skins of the fuselage and cargo hold of cargo aircraft. Summary of the Invention

[0005] To overcome the shortcomings of the above technologies, this utility model provides a tool that increases negative pressure and improves the reliability of hoisting large curved skin panels of aircraft.

[0006] The technical solution adopted by this utility model to overcome its technical problem is: A lifting tool for large curved skins of cargo civil aircraft, comprising: The main beam is horizontally arranged in the left-right direction, and a portal beam is installed at the upper end of the main beam through a fixing mechanism. Several arc-shaped suction cup brackets are fixed to the lower end of the main beam. The suction cup brackets are arranged along the front-to-back direction, and the suction cup brackets are spaced apart from each other along the length of the main beam. Each suction cup bracket has a sliding sleeve mounted on both the left and right ends. The sliding sleeve is equipped with a locking device, which locks and fixes the sliding sleeve relative to the suction cup bracket. A vacuum generator is mounted on the portal beam; Each sliding sleeve is provided with a guide sleeve, and a sliding rod is slidably inserted in the guide sleeve along the vertical direction. The sliding rod is elastically connected to the guide sleeve through an elastic mechanism. A vacuum suction cup is installed at the lower end of the sliding rod, and the vacuum suction cup is connected to a vacuum generating device.

[0007] To facilitate lifting, lifting lugs are provided on the left and right sides of the upper end of the above-mentioned portal beam.

[0008] Furthermore, the aforementioned fixing mechanism consists of several U-bolts, and the lower end of the portal beam is attached to the main beam by U-bolt clamps.

[0009] Furthermore, the aforementioned locking device includes a bolt screwed onto the sliding sleeve, the head of which contacts the outer surface of the suction cup bracket.

[0010] Furthermore, the aforementioned vacuum generating device includes a vacuum pump mounted on the portal beam and a main air pipe mounted on the main beam via a bracket. The main air pipe is horizontally arranged along the length of the main beam, and is sealed on all sides with a closed air chamber inside. The air inlet of the vacuum pump is connected to the closed air chamber of the main air pipe through a vacuum pipe. The two vacuum suction cups on each suction cup bracket are respectively connected to the first and second connecting ends of the tee via flexible hoses. One end of the vacuum switch is connected to the third connecting end of the tee, and the other end of the vacuum switch is connected to the closed air chamber of the main air pipe via a suction pipe.

[0011] Furthermore, the aforementioned vacuum switch includes a valve core and a sleeve that slides onto the valve core. The valve core has a cylindrical structure, with its lower end connected to a tee and its upper end connected to a suction pipe. A vent is provided on the valve core in the horizontal direction. When the sleeve slides along the valve core to the uppermost end, the vent is exposed. When the sleeve slides along the valve core to the lowermost end, the vent is closed.

[0012] Furthermore, the aforementioned elastic mechanism includes a spring fitted onto a slide rod. A retaining ring is provided at the top of the slide rod, and the outer diameter of the retaining ring is larger than the inner diameter of the guide sleeve. When the spring is in a free state, the lower end of the retaining ring contacts the upper end of the guide sleeve. When the slide rod slides upward, the lower end of the spring contacts the vacuum suction cup, and its upper end contacts the lower end of the guide sleeve, thus compressing and storing energy.

[0013] To better fit the curved surface of the aircraft skin, the lower end of the aforementioned slide bar is equipped with a ball head, through which the slide bar is rotatably connected to the vacuum suction cup.

[0014] The beneficial effects of this invention are as follows: By sliding the sliding sleeve along the suction cup bracket, each vacuum suction cup is adjusted to the correct position according to the curvature of the aircraft skin, ensuring that the subsequent vacuum suction cups can be tightly adsorbed onto the aircraft skin 13. After the vacuum suction cups are adjusted to the correct position, the locking device locks the sliding sleeve relative to the suction cup bracket, ensuring that the vacuum suction cups will not change position. The vacuum generating device then operates, creating a vacuum within each vacuum suction cup. Under negative pressure, the vacuum suction cups are adsorbed and fixed onto the surface of the aircraft skin. Finally, the lifting equipment moves the entire lifting tool upwards, realizing the lifting of the aircraft skin. This invention is suitable for lifting large curved skins of cargo aircraft, improving the efficiency of cargo system modification, reducing deformation and impact on the curved skin surface during manual handling, and ensuring the smooth lifting of large curved skins. Attached Figure Description

[0015] Figure 1 This is a three-dimensional structural diagram of the present invention; Figure 2 This is a perspective view of the utility model in use; Figure 3 This is a structural diagram of the vacuum suction cup part of this utility model; Figure 4 This is a structural diagram of the locking bolt portion of this utility model; Figure 5 This is a diagram showing the exposed air vent of this utility model. Figure 6 This is a diagram showing the closed state of the air vent of this utility model; Figure 7 This is a front sectional view of the sliding rod portion of this utility model; In the diagram, 1. Main beam 2. U-bolt 3. Portal beam 4. Lifting lug 5. Main air pipe 6. Support 7. Vacuum pipe 8. Vacuum pump 9. Suction cup support 10. Vacuum suction cup 11. Hose 12. Evacuation pipe 13. Aircraft skin 14. Valve core 15. Seal 16. T-joint 17. Sliding sleeve 18. Guide sleeve 19. Sliding rod 20. Spring 21. Retaining ring 22. Bolt 23. Vent 24. Ball head. Detailed Implementation

[0016] The following is in conjunction with the appendix Figure 1 To be continued Figure 7 The present invention will be further described below.

[0017] A lifting tool for large curved skins of cargo civil aircraft includes: a main beam 1, which is horizontally arranged in the left-right direction, and a portal beam 3 is installed on the upper end of the main beam 1 through a fixing mechanism; several arc-shaped suction cup brackets 9 are fixed to the lower end of the main beam 1, and the suction cup brackets 9 are arranged in the front-back direction, with each suction cup bracket 9 spaced apart from each other in the length direction of the main beam 1; a sliding sleeve 17 is slidably fitted on the left and right ends of each suction cup bracket 9, and a locking device is provided on the sliding sleeve 17, which is locked and fixed relative to the suction cup bracket 9 by the locking device; a vacuum generating device is provided on the portal beam 3; a guide sleeve 18 is provided on each sliding sleeve 17, and a sliding rod 19 is slidably inserted in the guide sleeve 18 in the vertical direction, the sliding rod 19 is elastically connected to the guide sleeve 18 through an elastic mechanism, and a vacuum suction cup 10 is installed on the lower end of the sliding rod 19, which is connected to the vacuum generating device. When it is necessary to lift the aircraft skin 13, connect the hook of the lifting equipment to the portal beam 3, move the entire lifting tool above the aircraft skin 13, and then drive the entire lifting tool to move downwards. The sliding sleeve 17 slides along the suction cup bracket 9, thereby adjusting each vacuum suction cup 10 to the curvature of the aircraft skin 13, ensuring that the vacuum suction cups 10 can tightly adhere to the aircraft skin 13. After the vacuum suction cups 10 are adjusted to the correct position, the locking device locks the sliding sleeve 17 relative to the suction cup bracket 9, ensuring that the vacuum suction cups 10 will not change position. The lifting equipment moves the entire lifting tool downwards until each vacuum suction cup 10 contacts the surface of the aircraft skin 13. The vacuum generator then operates, creating a vacuum within each vacuum suction cup 10. Under negative pressure, the vacuum suction cups 10 adhere and fix to the surface of the aircraft skin 13. Finally, the lifting equipment moves the entire lifting tool upwards, realizing the lifting of the aircraft skin 13. Multiple vacuum suction cups 10 are used to fix the aircraft skin 13 at multiple points, enabling the overall hoisting of the aircraft skin 13. This reduces the number of operators, improves hoisting efficiency, ensures the accuracy of the skin surface, and promotes the application of a standardized hoisting method.

[0018] In one embodiment of this utility model, lifting lugs 4 are respectively provided on the left and right sides of the upper end of the portal beam 3. The gantry crane can easily hook the hook onto the lifting lugs 4, thereby lifting the entire lifting tool and improving the convenience of use.

[0019] In one embodiment of this utility model, the fixing mechanism consists of several U-bolts 2, and the lower end of the portal beam 3 is clamped to the main beam 1 by the U-bolts 2. The portal beam 3 is fixed to the main beam 1 by the U-bolts 2, which makes installation quick and convenient and improves assembly efficiency. At the same time, the U-bolts 2 are arranged around the main beam 1, so the portal beam 3 can be firmly connected to the main beam 1, ensuring the firmness of the connection.

[0020] In one embodiment of this utility model, the locking device includes a bolt 22 screwed onto the sliding sleeve 17, with the head of the bolt 22 contacting the outer surface of the suction cup bracket 9. Once the vacuum suction cup 10 is adjusted into position along the suction cup bracket 9, tightening the bolt 22 will lock the sliding sleeve 17 relative to the suction cup bracket 9, making operation convenient.

[0021] In one embodiment of this utility model, the vacuum generating device includes a vacuum pump 8 installed on the portal beam 3 and a main air pipe 5 installed on the main beam 1 via a bracket 6. The main air pipe 5 is horizontally arranged along the length direction of the main beam 1. The main air pipe 5 is sealed on all sides and has a closed air chamber inside. The air inlet of the vacuum pump 8 is connected to the closed air chamber of the main air pipe 5 via a vacuum pipe 7. The two vacuum suction cups 10 on each suction cup bracket 9 are respectively connected to the first and second connecting ends of the tee 16 via a flexible hose 11. One end of the vacuum switch is connected to the third connecting end of the tee 16, and the other end of the vacuum switch is connected to the closed air chamber of the main air pipe 5 via a suction pipe 12. The vacuum pump 8 operates, creating negative pressure in the closed chamber of the main air pipe 5 via the vacuum pipe 7. When the vacuum switch is turned on, the vacuum suction cup 10 is disconnected from each extraction pipe 12, and the vacuum suction cup 10 has no suction. This allows for easy adjustment of the position of the sliding sleeve 17, enabling the vacuum suction cup 10 to be adjusted to ensure contact with the aircraft skin 13 surface. Afterward, the vacuum switch is turned off, and each extraction pipe 12 connected to the main air pipe 5 connects to its corresponding vacuum suction cup 10, generating suction. The vacuum suction cup 10 then adheres to and fixes the aircraft skin 13. By sequentially turning the corresponding vacuum switches on and off, the vacuum suction cup 10 can be easily adjusted to the correct position before adhering to and fixing the aircraft skin 13, improving operational reliability. In this embodiment, the vacuum switch includes a valve core 14 and a sleeve 15 that slides onto the valve core 14. The valve core 14 has a cylindrical structure, with its lower end connected to a tee 16 and its upper end connected to an extraction pipe 12. A vent 23 is provided on the valve core 14 in a horizontal direction. When the sleeve 15 slides along the valve core 14 to its uppermost position, the vent 23 is exposed. When the sleeve 15 slides along the valve core 14 to its lowermost position, the sleeve 15 closes the vent 23. When the vent 23 is exposed, the airflow generated by the vacuum pump 8 flows in through the vent 23, thus preventing the vacuum suction cup 9 from operating. When the sleeve 15 closes the vent 23, the negative pressure generated by the vacuum pump 8 flows sequentially through the vacuum pipe 7, the main air pipe 5, the extraction pipe 12, the valve core 14, and the hose 11 to the vacuum suction cup 10, creating a negative pressure inside the vacuum suction cup 10 to adsorb the aircraft skin 13.

[0022] In one embodiment of this utility model, the elastic mechanism includes a spring 20 fitted onto a slide rod 19. A retaining ring 21 is provided at the top of the slide rod 19. The outer diameter of the retaining ring 21 is larger than the inner diameter of the guide sleeve 18. When the spring 20 is in a free state, the lower end of the retaining ring 21 contacts the upper end of the guide sleeve 18. When the slide rod 19 slides upward, the lower end of the spring 20 contacts the vacuum suction cup 10, and its upper end contacts the lower end of the guide sleeve 18. The spring 20 is compressed and stores energy. When the lifting equipment drives the entire lifting tool to move downward so that the vacuum suction cup 10 contacts the outer surface of the aircraft skin 13, under the action of the impact force, the vacuum suction cup 10 will drive the slide rod 19 to move upward under the guidance of the guide sleeve 18 and compress the spring 20. The deformation of the spring 20 absorbs the impact force, thereby absorbing the impact force on the aircraft skin 13 and preventing damage to the aircraft skin 13. When the aircraft skin 13 is lifted, the spring 20 releases its elastic force, and the slide bar 19 moves downward relative to the initial position. Due to the obstruction of the retaining ring 21, the slide bar 19 will not detach from the guide sleeve 18, ensuring the reliability of use.

[0023] In one embodiment of this utility model, a ball head 24 is provided at the lower end of the slide rod 19, and the slide rod 19 is rotatably connected to the vacuum suction cup 10 through the ball head 24. By providing the ball head 24, the vacuum suction cup 10 can rotate freely relative to the slide rod 19 in space, so as to better adapt to the surface of different positions of the aircraft skin 13 and ensure that the vacuum suction cup 10 can form a good adsorption on the aircraft skin 13.

[0024] 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. A lifting tool for large curved skins of cargo civil aircraft, characterized in that, include: The main beam (1) is horizontally arranged in the left and right direction, and the upper end of the main beam (1) is fitted with a portal beam (3) through a fixing mechanism. Several arc-shaped suction cup brackets (9) are fixed to the lower end of the main beam (1). The suction cup brackets (9) are arranged along the front and back direction, and each suction cup bracket (9) is arranged at intervals along the length of the main beam (1). Each suction cup bracket (9) has a sliding sleeve (17) slidably fitted on its left and right ends. The sliding sleeve (17) is equipped with a locking device, and the sliding sleeve (17) is locked and fixed relative to the suction cup bracket (9) by the locking device. A vacuum generating device is mounted on the portal beam (3); Each sliding sleeve (17) is provided with a guide sleeve (18), and a sliding rod (19) is slidably inserted in the guide sleeve (18) along the vertical direction. The sliding rod (19) is elastically connected to the guide sleeve (18) through an elastic mechanism. A vacuum suction cup (10) is installed at the lower end of the sliding rod (19), and the vacuum suction cup (10) is connected to a vacuum generating device.

2. The lifting tool for large curved skin of cargo civil aircraft according to claim 1, characterized in that: The upper left and right sides of the portal beam (3) are respectively provided with lifting lugs (4).

3. The lifting tool for large curved skin of cargo civil aircraft according to claim 1, characterized in that: The fixing mechanism consists of several U-bolts (2), and the lower end of the portal beam (3) is fastened to the main beam (1) by the U-bolts (2).

4. The lifting tool for large curved skin of cargo civil aircraft according to claim 1, characterized in that: The locking device includes a bolt (22) screwed onto the sliding sleeve (17), the head of which is in contact with the outer surface of the suction cup bracket (9).

5. The lifting tool for large curved skin of cargo civil aircraft according to claim 1, characterized in that: The vacuum generating device includes a vacuum pump (8) installed on the portal beam (3) and a main air pipe (5) installed on the main beam (1) via a bracket (6). The main air pipe (5) is horizontally arranged along the length of the main beam (1). The main air pipe (5) is sealed on all sides and has a closed air chamber inside. The air inlet of the vacuum pump (8) is connected to the closed air chamber of the main air pipe (5) via a vacuum pipe (7). The two vacuum suction cups (10) on each suction cup bracket (9) are respectively connected to the first and second connection ends of the tee (16) via a hose (11). One end of the vacuum switch is connected to the third connection end of the tee (16), and the other end of the vacuum switch is connected to the closed air chamber of the main air pipe (5) via a suction pipe (12).

6. The lifting tool for large curved skin of cargo civil aircraft according to claim 5, characterized in that: The vacuum switch includes a valve core (14) and a sleeve (15) that slides on the valve core (14). The valve core (14) has a cylindrical structure. The lower end of the valve core (14) is connected to a tee (16), and the upper end is connected to a suction pipe (12). A vent (23) is provided on the valve core (14) in the horizontal direction. When the sleeve (15) slides along the valve core (14) to the uppermost end, the vent (23) is exposed. When the sleeve (15) slides along the valve core (14) to the lowermost end, the sleeve (15) closes the vent (23).

7. The lifting tool for large curved skin of cargo civil aircraft according to claim 1, characterized in that: The elastic mechanism includes a spring (20) fitted on a slide rod (19). A retaining ring (21) is provided at the top of the slide rod (19). The outer diameter of the retaining ring (21) is larger than the inner diameter of the guide sleeve (18). When the spring (20) is in a free state, the lower end of the retaining ring (21) is in contact with the upper end of the guide sleeve (18). When the slide rod (19) slides upward, the lower end of the spring (20) is in contact with the vacuum suction cup (10), and its upper end is in contact with the lower end of the guide sleeve (18). The spring (20) is compressed and stores energy.

8. The lifting tool for large curved skin of cargo civil aircraft according to claim 1, characterized in that: The lower end of the slide rod (19) is provided with a ball head (24), and the slide rod (19) is rotatably connected to the vacuum suction cup (10) through the ball head (24).

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