Maintenance maintenance machine belly skin dismounting and mounting equipment

Abstract

The invention belongs to the technical field of aircraft maintenance, and particularly discloses aircraft maintenance belly skin dismounting and mounting equipment which comprises supporting levers arranged in pairs and moving wheels on the lower portions of the supporting levers, the two supporting levers are connected together through a plurality of bidirectional hydraulic rods, the bidirectional hydraulic rods are fixed to a middle lever, and telescopic hydraulic cylinders are arranged on the lower wall of the middle lever in an array mode. The lower end of the telescopic hydraulic cylinder is provided with a vacuum suction cup, supporting rods are arranged on the upper wall of the supporting lever in an array mode, the upper ends of the supporting rods are connected together through a transverse lever, lifting assemblies are arranged on the supporting lever and the transverse lever, self-matching adjusting assemblies are arranged on the lifting assemblies, and an automatic contour adapting assembly is arranged between every two opposite self-matching adjusting assemblies. The connecting blocks are sequentially connected through the curable connecting assemblies to form a chain-shaped structure, the chain-shaped structure is automatically attached to the surface of the airplane belly skin according to the shape of the airplane belly skin, fixing of the positions of the connecting blocks is automatically completed, and deformation of the airplane belly skin in the hoisting process is avoided.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft maintenance, and specifically refers to a device for disassembling and assembling the belly skin of an aircraft during maintenance. Background Art

[0002] After the skin bears the aerodynamic force, it transmits the force to the connected fuselage and wing skeletons. The force is complex. In addition, since the skin is in direct contact with the outside world, it is not only required that the skin material has high strength and good plasticity, but also requires a smooth surface and high corrosion resistance. The function of the aircraft skin is to maintain the aircraft's shape and make it have good aerodynamic characteristics. Therefore, the design requirements for the shape of the aircraft skin are very high.

[0003] For aircraft repair and seasonal inspection, etc., it is necessary to disassemble and assemble the belly skin of the aircraft. The belly skin is relatively large, with a height generally between 1 meter and 2 meters, and the cross-sectional shape of the belly skin is a curved arc. During the disassembly and assembly process, it is necessary to lift the belly skin. Due to the large weight of the belly skin, it is easy to cause deformation of the belly skin during the lifting process, thus affecting the aerodynamic characteristics of the aircraft's shape.

[0004] Therefore, a device for disassembling and assembling the belly skin of an aircraft during maintenance is needed to solve the above problems. Summary of the Invention

[0005] In view of the above situation, to overcome the defects of the prior art, the present invention provides a device for disassembling and assembling the belly skin of an aircraft during maintenance. The connecting blocks are sequentially connected through a curable connecting component to form a chain-like structure, which automatically adheres to the surface of the belly skin according to the shape of the belly skin and automatically fixes the positions of the connecting blocks, avoiding deformation of the belly skin during the lifting process.

[0006] The technical solution adopted by the present invention is as follows: The present invention provides a device for disassembling and assembling the belly skin of an aircraft during maintenance, including a pair of support bars and moving wheels at their lower parts. The two support bars are connected together by a plurality of bidirectional hydraulic rods. The bidirectional hydraulic rods are fixed on an intermediate bar. The lower wall of the intermediate bar is provided with telescopic hydraulic cylinders in an array. The lower ends of the telescopic hydraulic cylinders are provided with vacuum suction cups. The upper walls of the support bars are provided with support rods in an array. The upper ends of the support rods are connected together by a cross bar. Lifting components are provided on the support bars and the cross bar. Self-matching adjustment components are provided on the lifting components. A contour automatic adaptation component is provided between two opposite self-matching adjustment components; The contour automatic adaptation component includes a hinge component, a connecting block, and a curable connecting component. The two hinge components are respectively arranged at the lower parts of the two self-matching adjustment components. There are a plurality of connecting blocks. Connecting blocks are respectively provided on the two hinge components. Adjacent connecting blocks are connected together by a curable connecting component. An adsorption component is provided on the connecting block.

[0007] Further, the curable connection assembly includes hinge plates, a connecting shaft, protrusions, and electrorheological fluid. There are two hinge plates. One end of each of the two hinge plates is rotatably connected by the connecting shaft. A rotating cavity is provided at the end of the hinge plate. An insulating layer is provided on the inner wall of the rotating cavity. The electrorheological fluid fills the rotating cavity. The end of the connecting shaft is located in the rotating cavity. The protrusions are arranged in an array at both ends of the connecting shaft. The protrusions are provided in the rotating cavity. The other end of the hinge plate is fixedly provided at the end of the connecting block.

[0008] Further, the adsorption assembly includes a Bernoulli suction cup, a connecting column, and a second spring. A placement hole is provided on the upper wall of the connecting block. The placement hole is a blind hole. A spring hole is provided on the inner bottom wall of the placement hole. The spring hole is a blind hole. The second spring is provided on the inner bottom wall of the spring hole. The connecting column is slidably provided in the spring hole. The lower end of the connecting column is connected to the second spring. The Bernoulli suction cup is slidably provided in the placement hole. The Bernoulli suction cup is provided at the upper end of the connecting column.

[0009] Further, a total electrical circuit is provided on the curable connection assembly. A plurality of resistors are provided on the total electrical circuit. Electrical contacts one and two are provided on the inner wall of the spring hole. The electrical contact one is electrically connected to the total electrical circuit through a wire. The electrical contact two is electrically connected to the electrorheological fluid in the rotating cavity through a wire. The electrorheological fluid in each rotating cavity is respectively connected in parallel with the resistor.

[0010] Further, the lifting assembly includes a placement table, a winch, a guiding frame, guiding wheels, a support frame, a sliding hoop, and a lifting rope. The placement table is provided in the middle of the outer side wall of the support bar. The winch is provided on the upper wall of the placement table. The guiding frame is provided in the middle of the upper wall of the cross bar. The guiding wheels are symmetrically provided on the guiding frame. The support frame is provided inside the support rod. The sliding hoop is slidably provided on the support rod. The sliding hoop is fixedly connected to the support frame. The lifting rope is wound around the winch. The lifting rope bypasses the two guiding wheels. The movable end of the lifting rope is fixedly provided on the upper wall of the support frame.

[0011] Further, the self-matching adjustment assembly includes a sliding block, a vertical rod, a first spring, a baffle, and a locking screw. A sliding hole is provided through the side wall of the sliding block. The sliding block is sleeved on the side wall of the support frame through the sliding hole. The vertical rod is slidably provided through the sliding block. The baffle is provided at the upper end of the vertical rod. The first spring is sleeved on the vertical rod. The upper and lower ends of the first spring are respectively provided on the baffle and the upper wall of the sliding block. The locking screw is provided on the outer side wall of the sliding block.

[0012] Further, the hinge assembly includes a hinge frame and a connecting plate. The hinge frame is provided at the lower end of the vertical rod. The hinge frame and the connecting plate are rotatably connected by a rotating shaft. The connecting block is fixedly connected to the connecting plate.

[0013] Further, scale lines are provided on the outer sidewall of the support frame.

[0014] The beneficial effects achieved by the present invention with the above structure are as follows: 1. In the self-matching adjustment component, the vertical rod can move up and down under the action of the second spring. A connecting block and a curable connection component are provided between each group of hinged components. During the process of the lifting rope pulling the support frame upward, the support frame drives the sliding block, the vertical rod, the hinged components, the connecting block and the curable connection component to move upward. Since the vertical rod can move up and down under the action of the second spring, therefore, according to the shape of the lower side of the belly skin, the connecting blocks in the middle between different hinged components can all contact the belly skin. 2. When the connecting block adheres to the surface of the belly, the Bernoulli suction cup is pressed down. The Bernoulli suction cup presses down the connecting column and the second spring. The connecting column connects the first electrical contact and the second electrical contact together. During the process of the connecting block contacting the belly surface in sequence, the Bernoulli suction cups on the adjacent connecting blocks are pressed down. The first electrical contact and the second electrical contact corresponding to this connecting block are connected together. At this time, the resistor and its corresponding electrorheological fluid form an electrical circuit through the wire. A voltage is applied to both ends of the electrorheological fluid, and the electrorheological fluid changes from a liquid to a solid. The solid electrorheological fluid forms an integral body with the connecting shaft, the protrusion and the hinged plate, and the positions of the two connecting blocks are fixed. 3. During the process of shortening the double-acting hydraulic rod, the distance between the two support bars decreases, and the connecting blocks between the two hinged components gradually contact the outer surface of the belly from the middle to both sides. Thus, the connecting blocks adhere to the outer surface of the belly in sequence according to the outer surface shape of the belly skin, and the positions of the connecting blocks are fixed according to the above operations. Description of the Drawings

[0015] Figure 1 is a three-dimensional structural schematic diagram of a belly skin disassembly and assembly device for aircraft maintenance proposed by the present invention; Figure 2 is Figure 1 the front view of; Figure 3 is a three-dimensional structural schematic diagram of the self-matching adjustment component and the contour automatic adaptation component; Figure 4 is a three-dimensional structural schematic diagram of the self-matching adjustment component; Figure 5 is a three-dimensional structural schematic diagram of the curable connection component; Figure 6 is a three-dimensional structural schematic diagram of the connecting block and the hinged plate; Figure 7 is an internal structural schematic diagram of the connection between two hinged plates and the connecting shaft; Figure 8 is an internal structural schematic diagram of the hinged plate; Figure 9Schematic diagram of the three-dimensional structure of the connecting shaft and the protrusion; Figure 10 Circuit connection diagram of the contour automatic adaptation component and the total electrical circuit; Figure 11 For Figure 10 Enlarged view of part A in Figure 12 For Figure 11 Enlarged view of part B in Figure 13 For Figure 11 Enlarged view of part C in

[0016] Among them, 1. Support bar, 2. Moving wheel, 3. Double-acting hydraulic rod, 4. Support rod, 5. Cross bar, 6. Lifting component, 7. Self-matching adjustment component, 8. Contour automatic adaptation component, 9. Hinge component, 10. Connecting block, 11. Curable connection component, 12. Adsorption component, 13. Hinge plate, 14. Connecting shaft, 15. Protrusion, 16. Electrorheological fluid, 17. Vacuum suction cup, 18. Rotation cavity, 19. Scale line, 20. Bernoulli suction cup, 21. Connecting column, 22. Spring two, 23. Placing hole, 24. Spring hole, 25. Total electrical circuit, 26. Resistor, 27. Electrical contact one, 28. Electrical contact two, 29. Placing table, 30. Winch, 31. Guide frame, 32. Guide wheel, 33. Support frame, 34. Sliding hoop, 35. Suspension rope, 36. Sliding block, 37. Vertical rod, 38. Spring one, 39. Baffle, 40. Locking screw, 41. Sliding hole, 42. Hinge frame, 43. Connecting plate, 44. Rotation shaft, 45. Intermediate bar, 46. Telescopic hydraulic cylinder.

[0017] The attached drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation to the present invention. Detailed implementation manners

[0018] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments; based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0019] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc. indicate the orientation or position relationship based on the orientation or position relationship shown in the drawings. These are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation on the present invention.

[0020] As Figure 1 , Figure 2 , Figure 3 shown, the present invention provides a belly skin disassembly and assembly device for aircraft maintenance, including a pair of support bars 1 and moving wheels 2 at their lower parts. The two support bars 1 are connected together by a plurality of bidirectional hydraulic rods 3. The bidirectional hydraulic rods 3 are fixed on an intermediate bar 45. The lower wall of the intermediate bar 45 is provided with telescopic hydraulic cylinders 46 in an array. The lower ends of the telescopic hydraulic cylinders 46 are provided with vacuum suction cups 17. The upper walls of the support bars 1 are provided with support rods 4 in an array. The upper ends of the support rods 4 are connected together by a cross bar 5. A lifting assembly 6 is provided on the support bars 1 and the cross bar 5. A self-matching adjustment assembly 7 is provided on the lifting assembly 6. A contour automatic adaptation assembly 8 is provided between two opposite self-matching adjustment assemblies 7; The contour automatic adaptation assembly 8 includes hinge assemblies 9, connection blocks 10, and curable connection assemblies 11. The two hinge assemblies 9 are respectively arranged at the lower parts of the two self-matching adjustment assemblies 7. There are a plurality of connection blocks 10. The two hinge assemblies 9 are respectively provided with connection blocks 10. Adjacent connection blocks 10 are connected together by curable connection assemblies 11. Adsorption assemblies 12 are provided on the connection blocks 10. In the initial state, the contour automatic adaptation assembly 8 is in a chain shape.

[0021] As Figure 1 , Figure 2 , Figure 3 , Figure 5 , Figure 6 , Figure 7 , Figure 8 , Figure 9 shown, the curable connection assembly 11 includes hinge plates 13, connection shafts 14, protrusions 15, and electrorheological fluids 16. There are two hinge plates 13. One end of each of the two hinge plates 13 is rotatably connected by a connection shaft 14. The end of the hinge plate 13 is provided with a rotating cavity 18. The inner wall of the rotating cavity 18 is provided with an insulating layer. The electrorheological fluid 16 fills the rotating cavity 18. The end of the connection shaft 14 is located in the rotating cavity 18. The protrusions 15 are arranged in an array at both ends of the connection shaft 14. The protrusions 15 are arranged in the rotating cavity 18. The other end of the hinge plate 13 is fixedly arranged at the end of the connection block 10.

[0022] AsFigure 1 , Figure 10 , Figure 11 , Figure 12 , Figure 13 As shown in Figure 13 , the adsorption assembly 12 includes a Bernoulli suction cup 20, a connecting column 21, and a second spring 22. A placement hole 23 is provided on the upper wall of the connecting block 10. The placement hole 23 is a blind hole. A spring hole 24 is provided on the inner bottom wall of the placement hole 23. The spring hole 24 is a blind hole. The second spring 22 is provided on the inner bottom wall of the spring hole 24. The connecting column 21 is slidably arranged in the spring hole 24. The lower end of the connecting column 21 is connected to the second spring 22. The Bernoulli suction cup 20 is slidably arranged in the placement hole 23. The Bernoulli suction cup 20 is arranged at the upper end of the connecting column 21. The connecting column 21 is electrically conductive. The Bernoulli suction cup 20 is controlled by high-pressure gas from the outside.

[0023] As Figure 1 , Figure 10 , Figure 11 , Figure 12 , Figure 13 As shown in Figure 13 , the curable connection assembly 11 has a total electrical circuit 25. A plurality of resistors 26 are provided on the total electrical circuit 25. An electrical contact one 27 and an electrical contact two 28 are provided on the inner wall of the spring hole 24. The electrical contact one 27 is electrically connected to the total electrical circuit 25 through a wire. The electrical contact two 28 is electrically connected to the electrorheological fluid 16 in the rotating cavity 18 through a wire. The electrorheological fluid 16 in each rotating cavity 18 is respectively connected in parallel with the resistor 26. The electrical contact one 27 and the electrical contact two 28 are embedded in the inner wall of the spring hole 24 and are insulated from the connecting block 10. In the initial state, the second spring 22 bounces the connecting column 21 upward, and the electrical contact one 27 and the electrical contact two 28 do not contact the connecting column 21, and the electrical contact one 27 and the electrical contact two 28 are in an open state.

[0024] As Figure 1 , Figure 2 , Figure 3 , Figure 4 As shown in Figure 4 , the lifting assembly 6 includes a placement table 29, a winch 30, a guide frame 31, guide wheels 32, a support frame 33, a sliding hoop 34, and a lifting rope 35. The placement table 29 is arranged in the middle of the outer side wall of the support bar 1. The winch 30 is arranged on the upper wall of the placement table 29. The guide frame 31 is arranged in the middle of the upper wall of the cross bar 5. The guide wheels 32 are symmetrically arranged on the guide frame 31. The support frame 33 is arranged inside the support rod 4. The sliding hoop 34 is slidably arranged on the support rod 4. The sliding hoop 34 is fixedly connected to the support frame 33. The lifting rope 35 is wound around the winch 30. The lifting rope 35 bypasses the two guide wheels 32. The movable end of the lifting rope 35 is fixed to the upper wall of the support frame 33.

[0025] As Figure 1 , Figure 2 ,Figure 3 , Figure 4 As shown, the self-matching adjustment component 7 includes a sliding block 36, a vertical rod 37, a first spring 38, a baffle 39, and a locking screw 40. A sliding hole 41 is provided through the side wall of the sliding block 36. The sliding block 36 is sleeved on the side wall of the support frame 33 through the sliding hole 41. The vertical rod 37 is slidably disposed through the sliding block 36. The baffle 39 is disposed at the upper end of the vertical rod 37. The first spring 38 is sleeved on the vertical rod 37. The upper and lower ends of the first spring 38 are respectively disposed on the baffle 39 and the upper wall of the sliding block 36. The locking screw 40 is disposed on the outer side wall of the sliding block 36.

[0026] As Figure 1 , Figure 4 shown, the hinge assembly 9 includes a hinge frame 42 and a connecting plate 43. The hinge frame 42 is disposed at the lower end of the vertical rod 37. The hinge frame 42 and the connecting plate 43 are rotatably connected through a rotating shaft 44. The connecting block 10 is fixedly connected to the connecting plate 43.

[0027] As Figure 3 shown, a scale line 19 is provided on the outer side wall of the support frame 33. The position of the sliding block 36 is adjusted according to the scale line 19, and the two opposite sliding blocks 36 can be aligned.

[0028] During actual use, when disassembling the belly skin, first the staff remove the rivets of the belly skin, leaving a few rivets to keep the belly skin from falling off the aircraft frame. Move the support bar 1. The two support bars 1 are on both sides of the aircraft body. The connecting block 10 and the curable connecting component 11 are on the lower side of the belly. According to the scale line 19 on the side wall of the support frame 33, adjust the position of the sliding block 36 on the support frame 33. The sliding block 36 drives the vertical rod 37 and the hinge assembly 9 to move. The hinge assembly 9 drives the connecting block 10 and the curable connecting component 11 to move, so that the connecting block 10 and the curable connecting component 11 are in the middle of the lower side of the belly. Then adjust the telescopic cylinder to extend, so that the vacuum suction cup 17 adsorbs on the ground. Adjust the double-acting hydraulic rod 3 to extend. The double-acting hydraulic rod 3 drives the support rod 4 to move to both sides. At this time, the contour automatic adaptation component 8 is in a nearly straightened state. Unscrew the locking screw 40, connect the external high-pressure gas, and the Bernoulli suction cup 20 is in an adsorption state. Turn on the winch 30. The winch 30 winds up the lifting rope 35. The lifting rope 35 pulls the support frame 33 upward. The support frame 33 drives the sliding block 36 to move upward. The sliding block 36 drives the vertical rod 37 and the hinge assembly 9 to move upward. The hinge assembly 9 drives the connecting block 10 and the curable connecting component 11 to move upward. Since the vertical rod 37 can move up and down under the action of the first spring 38, the connecting block 10 in the middle between different hinge assemblies 9 can all contact the belly skin. Then adjust the double-acting hydraulic rod 3 to shorten. The connecting block 10 between different hinge assemblies 9 contacts the belly skin in sequence from the middle to both sides. When the connecting block 10 adheres to the surface of the belly, the Bernoulli suction cup 20 is pressed down. The Bernoulli suction cup 20 presses down the connecting column 21. The connecting column 21 presses down the second spring 22. The connecting column 21 connects the first electric contact 27 and the second electric contact 28 together. During the process that the connecting block 10 contacts the belly surface in sequence, the Bernoulli suction cup 20 on the adjacent connecting block 10 is pressed down. The first electric contact 27 and the second electric contact 28 corresponding to this connecting block 10 are connected together. At this time, the resistor 26 and its corresponding electrorheological fluid 16 form an electric circuit through the wire. A voltage is applied to both ends of the electrorheological fluid 16. The electrorheological fluid 16 changes from a liquid to a solid. The solid electrorheological fluid 16 forms an integral body with the connecting shaft 14, the protrusion 15 and the hinge plate 13. The positions of the two connecting blocks 10 are fixed. During the process of shortening the double-acting hydraulic rod 3, the distance between the two support bars 1 decreases. The connecting block 10 between the two hinge assemblies 9 gradually contacts the outer surface of the belly from the middle to both sides. Thus, the connecting block 10 adheres to the outer surface of the belly in sequence according to the outer surface shape of the belly skin, and the position of the connecting block 10 is fixed according to the above operations. Then tighten the locking screw 40. After the maintenance staff remove the last few rivets of the belly skin, the belly skin is fixed on the connecting block 10. Then adjust the winch 30 to gradually release the lifting rope 35. Under the action of gravity, the belly skin follows the support frame 33, the sliding block 36, the vertical rod 37, the hinge assembly 9 and the connecting block 10 to descend.Complete the disassembly of the belly skin. When it is necessary to remove the belly skin, disconnect the external high-pressure gas, and the suction force of the Bernoulli suction cup 20 disappears; When installing the belly skin, adjust the position of the sliding block 36 on the support frame 33 according to the scale line 19 on the side wall of the support frame 33. The sliding block 36 drives the vertical rod 37 and the hinge assembly 9 to move. The hinge assembly 9 drives the connecting block 10 and the curable connecting assembly 11 to move. Then adjust the telescopic cylinder to extend so that the vacuum suction cup 17 adsorbs on the ground. Adjust the double-acting hydraulic rod 3 to extend, and the double-acting hydraulic rod 3 drives the support rod 4 to move to both sides. At this time, the contour automatic adaptation assembly 8 is in a state close to being straightened. Unscrew the locking screw 40, hoist the repaired or new belly skin onto the connecting block 10 and the curable connecting assembly 11 between the hinge assemblies 9, and repeat the operation when disassembling the belly skin. The connecting block 10 adheres to the outer surface of the belly in sequence according to the outer surface shape of the belly skin and is fixed. Then tighten the locking screw 40 to finally fix the belly skin. Turn on the winch 30 to wind up the lifting rope 35, turn on the vacuum suction cup 17, adjust the telescopic cylinder to shorten, move the support bar 1 so that the skin is under the belly, and then adjust the telescopic hydraulic cylinder 46 to extend so that the vacuum suction cup 17 adsorbs on the ground again, making the belly skin dock with the aircraft frame to complete the installation of the belly skin. Disconnect the main power circuit 25, and no voltage is applied to both ends of all the electrorheological fluids 16. The electrorheological fluids 16 change from solid state to liquid state, and the two hinge plates 13 between the two connecting blocks 10 can rotate freely. The contour automatic adaptation assembly 8 returns to a chain shape.

[0029] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variation thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or elements inherent to such process, method, article or device.

[0030] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention.

[0031] The above describes the present invention and its implementation manners. Such description is not restrictive. What is shown in the drawings is only one of the implementation manners of the present invention, and the actual structure is not limited thereto. Generally speaking, if those of ordinary skill in the art are inspired by it and, without departing from the gist of the present invention, design similar structural manners and embodiments to this technical solution without creative efforts, they shall fall within the protection scope of the present invention.

Claims

1. An aircraft maintenance belly skin disassembly and assembly device, including paired support bars (1) and moving wheels (2) at their lower parts. The two support bars (1) are connected together by a plurality of double-acting hydraulic rods (3). The double-acting hydraulic rods (3) are fixed on an intermediate bar (45). The lower wall of the intermediate bar (45) is provided with telescopic hydraulic cylinders (46) in an array. The lower ends of the telescopic hydraulic cylinders (46) are provided with vacuum suction cups (17), and it is characterized in that: The upper wall of the support bar (1) is provided with a support rod (4) in an array, the upper ends of the support rods (4) are connected together by a cross bar (5), a lifting assembly (6) is provided on the support bar (1) and the cross bar (5), a self-matching adjustment assembly (7) is provided on the lifting assembly (6), and a contour automatic adaptation assembly (8) is provided between two opposite self-matching adjustment assemblies (7); The contour automatic adaptation assembly (8) includes a hinge assembly (9), a connecting block (10) and a curable connection assembly (11). The two hinge assemblies (9) are respectively arranged at the lower parts of the two self-matching adjustment assemblies (7). There are a plurality of connecting blocks (10). The connecting blocks (10) are respectively arranged on the two hinge assemblies (9), and the adjacent connecting blocks (10) are connected together by the curable connection assembly (11). An adsorption assembly (12) is provided on the connecting block (10).

2. The belly skin disassembly and assembly equipment for aircraft maintenance according to claim 1, wherein: The curable connection assembly (11) includes hinge plates (13), a connecting shaft (14), protrusions (15) and electrorheological fluid (16). There are two hinge plates (13). One ends of the two hinge plates (13) are rotatably connected by the connecting shaft (14). A rotating cavity (18) is provided at the end of the hinge plate (13). The inner wall of the rotating cavity (18) is provided with an insulating layer. The electrorheological fluid (16) fills the rotating cavity (18). The end of the connecting shaft (14) is located in the rotating cavity (18). The protrusions (15) are arranged in an array at both ends of the connecting shaft (14). The protrusions (15) are arranged in the rotating cavity (18). The other ends of the hinge plates (13) are fixedly arranged at the ends of the connecting blocks (10).

3. The belly skin disassembly and assembly equipment for aircraft maintenance according to claim 2, characterized in that: The adsorption assembly ( 4. The belly skin disassembly and assembly equipment for aircraft maintenance according to claim 3, characterized in that: ​ 5. The belly skin disassembly and assembly equipment for aircraft maintenance according to claim 4, wherein: The lifting assembly (6) includes a placement table (29), a winch (30), a guide frame (31), guide wheels (32), a support frame (33), a sliding hoop (34), and a lifting rope (35). The placement table (29) is arranged in the middle of the outer sidewall of the support bar (1). The winch (30) is arranged on the upper wall of the placement table (29). The guide frame (31) is arranged in the middle of the upper wall of the cross bar (5). The guide wheels (32) are symmetrically arranged on the guide frame (31). The support frame (33) is arranged inside the support rod (4). The sliding hoop (34) is slidably arranged on the support rod (4). The sliding hoop (34) is fixedly connected to the support frame (33). The lifting rope (35) is wound around the winch (30). The lifting rope (35) bypasses the two guide wheels (32). The movable end of the lifting rope (35) is fixed to the upper wall of the support frame (33).

6. The belly skin disassembly and assembly equipment for aircraft maintenance according to claim 5, characterized in that: The self-matching adjustment assembly (7) includes a sliding block (36), a vertical rod (37), a first spring (38), a baffle (39), and a locking screw (40). A sliding hole (41) is provided through the sidewall of the sliding block (36). The sliding block (36) is sleeved on the sidewall of the support frame (33) through the sliding hole (41). The vertical rod (37) is slidably arranged through the sliding block (36). The baffle (39) is arranged at the upper end of the vertical rod (37). The first spring (38) is sleeved on the vertical rod (37). The upper and lower ends of the first spring (38) are respectively arranged on the baffle (39) and the upper wall of the sliding block (36). The locking screw (40) is arranged on the outer sidewall of the sliding block (36).

7. The belly skin disassembly and assembly equipment for aircraft maintenance according to claim 6, characterized in that: The hinge assembly (9) includes a hinge frame (42) and a connecting plate (43). The hinge frame (42) is arranged at the lower end of the vertical rod (37). The hinge frame (42) and the connecting plate (43) are rotatably connected through a rotating shaft (44). The connecting block (10) is fixedly connected to the connecting plate (43).

8. The belly skin disassembly and assembly equipment for aircraft maintenance according to claim 7, characterized in that: A scale line (19) is provided on the outer sidewall of the support frame (33).

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