Multi-point self-adaptive hoisting and overturning tooling for aircraft skin

Abstract

The utility model relates to the field of hoisting tooling, concretely is the aircraft skin multi -point self -adaptation hoisting turnover tooling, the utility model discloses hoisting suction cup, first support board and second support board, the top of first support board and second support board is provided with the adjusting assembly for adjusting hoisting adaptation to the different size width aircraft skin. The utility model discloses through the self -adaptation component, through the sliding fit and spring stretch of telescopic guide pillar in the sleeve, hoisting suction cup is in vertical direction self -adaptation adjustment height difference, thereby realizes the automatic adaptation of hoisting suction cup bottom to skin cambered surface, when hoisting suction cup contacts the curved skin of overturning, both sides suction cup because cambered surface height difference passes through connecting rod and rotates angle in fixed support middle part, and fixed support swings in H type foot support both sides, forms the multi -free angle adjustment, makes every hoisting suction cup can be perpendicular or adheres on the curved skin surface of overturning on direction and carries out adsorption.

Description

Technical Field

[0001] This utility model relates to the field of hoisting fixtures, specifically a multi-point adaptive hoisting and flipping fixture for aircraft skin. Background Technology

[0002] The multi-point adaptive lifting and flipping fixture for aircraft skin is a key piece of equipment used in aerospace manufacturing, especially in the process of manufacturing aircraft fuselages. It has important application significance. This fixture is mainly used for lifting large structural components such as aircraft skin. Usually, the aircraft skin is processed into a flipped or arc shape, and the flipped aircraft skin is lifted by the suction cups of the lifting device.

[0003] However, in existing devices, the suction cups of traditional lifting devices can only adsorb flat aircraft skin and cannot be used to adsorb and lift non-flat surfaces, such as flipped aircraft skin. Its limitation is that it can only handle flat skin and cannot meet the diverse flipping shape requirements of aircraft skin, which greatly limits the application scenarios of the lifting device. Utility Model Content

[0004] The purpose of this invention is to provide a multi-point adaptive lifting and flipping fixture for aircraft skin to solve the problems mentioned in the background art.

[0005] The objective of this utility model can be achieved through the following technical solutions:

[0006] An aircraft skin multi-point adaptive lifting and flipping fixture includes a lifting suction cup, a first support plate, and a second support plate. The fixture is characterized in that the top of the first and second support plates are provided with adjustment components for adjusting the lifting to accommodate aircraft skins of different widths. The bottom of the first and second support plates are respectively provided with a first mounting plate and a second mounting plate, with the first mounting plate located directly below the first support plate. The bottom of both the first and second mounting plates is provided with multiple adaptive components, and the bottom end of each adaptive component is provided with a lifting suction cup for adaptive telescopic movement and angle adjustment. The lifting suction cup adsorbs the aircraft skin.

[0007] Preferably, the adjustment assembly includes a guide rail plate with a sliding groove inside. Sliding blocks are slidably connected to both ends of the sliding groove. The bottom ends of the two sliding blocks are fixedly connected to the top centers of the first and second support plates, respectively. A sleeve plate is fixedly connected to the top of each sliding block. A bidirectional threaded rod is threadedly connected to the inside of the sleeve plate. The two sleeve plates are threadedly connected to both ends of the bidirectional threaded rod. Fixed plates are fixedly connected to both ends of the top of the guide rail plate. A first motor is fixedly connected to one side of one of the fixed plates. The two ends of the bidirectional threaded rod are rotatably sleeved within the two fixed plates. One end of the bidirectional threaded rod passes through the fixed plate and is fixedly connected to the output shaft of the first motor.

[0008] Preferably, fixed support plates are fixedly installed at both ends of the top of the first support plate and the second support plate. Support sleeves and support guide rods are respectively provided on opposite sides of the first support plate and the second support plate. The support sleeves and support guide rods are respectively fixedly connected to opposite sides of the fixed support plates on the first support plate and the second support plate. The support guide rods are slidably sleeved in the support sleeves.

[0009] Preferably, the bottom of both the first support plate and the second support plate are fixedly connected to a plurality of fixed guide posts, and the bottom ends of the plurality of fixed guide posts are respectively fixedly connected to the top wall panels of the first mounting plate and the second mounting plate.

[0010] Preferably, the adaptive component includes connecting blocks. Multiple connecting blocks are fixedly connected to the bottom of both the first mounting plate and the second mounting plate. A housing is fixedly connected to the bottom of the connecting blocks. A first ring plate is fixedly connected to the top of the inner part of the housing. A telescopic spring is fixedly installed at the lower end of the first ring plate. A second ring plate is fixedly connected to the end of the telescopic spring away from the first ring plate. A telescopic guide post is fixedly sleeved inside the second ring plate. A telescopic sleeve is movably sleeved on the outer side of the telescopic guide post. The top of the telescopic sleeve is fixedly connected to the bottom end of the first ring plate. Both the telescopic sleeve and the telescopic guide post are located inside the telescopic spring.

[0011] Preferably, one end of the telescopic guide column is fixedly connected to an H-shaped bracket, the H-shaped bracket is fixedly connected to a "U"-shaped fixed bracket, the two ends of the fixed bracket are respectively fixedly connected to the two ends of the H-shaped bracket by bolts, a connecting rod is rotatably connected to the bottom center of the fixed bracket, a fixed block is fixedly connected to the bottom end of the connecting rod, and a lifting suction cup is fixedly installed at the bottom of the fixed block.

[0012] Preferably, a first limiting block is fixedly connected to both sides of the second ring plate, and a second limiting block is movably engaged at the bottom of the first limiting block. The two second limiting blocks are fixedly connected to the bottom sides of the outer shell by screws, and the second limiting blocks limit the telescopic guide column through the first limiting blocks.

[0013] The beneficial effects of this utility model are:

[0014] 1. This utility model utilizes an adaptive component, through the sliding engagement of the telescopic guide post within the sleeve and spring tension, to allow the lifting suction cup to adaptively adjust its height difference in the vertical direction. This enables the bottom of the lifting suction cup to automatically adapt to the curved surface of the skin. When the lifting suction cup contacts the flipped curved skin, the suction cups on both sides rotate at the center of the fixed bracket due to the height difference of the curved surface via a connecting rod, creating multiple free angle adjustments. This allows each lifting suction cup to be adsorbed vertically or against the surface of the flipped curved skin. Furthermore, through the first and second limiting blocks, when the weight of the skin pulls the telescopic guide post downwards, the second limiting block on the outer side of the second ring plate moves with the guide post. Once it approaches the end of the sleeve, it abuts against the first limiting block, forcibly restricting the guide post from further downward movement and preventing the guide post from completely detaching from the sleeve and causing the suction cup to fall off.

[0015] 2. This utility model uses a first motor to drive a bidirectional threaded rod to rotate. The forward and reverse threaded structures at both ends can synchronously drive the two sleeve plates to move in opposite directions, thereby pushing the first support plate and the second support plate to move towards each other. By adjusting the distance between the first support plate and the second support plate, the lifting suction cup can be adapted to different aircraft flip skin widths, thereby adsorbing and lifting different aircraft flip skins. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0018] Figure 2 This is a schematic diagram of the structure of the adjustment component of this utility model;

[0019] Figure 3 This is a structural schematic diagram of the bidirectional threaded rod, the first support plate, and the second support plate of this utility model;

[0020] Figure 4 This is a schematic diagram of the structure of the adaptive component of this utility model;

[0021] Figure 5 This is a schematic diagram of the disassembled adaptive component of this utility model;

[0022] Figure 6 This is a structural cross-sectional view of the adaptive component of this utility model.

[0023] The reference numerals in the attached figures are as follows: 1. First support plate; 11. Second support plate; 2. Fixed guide post; 3. First mounting plate; 31. Second mounting plate; 4. Adjustment component; 41. Guide rail plate; 42. Sliding groove; 43. Fixed support plate; 44. Support guide rod; 45. Support sleeve; 46. Sliding block; 47. Sleeve plate; 48. Bidirectional threaded rod; 49. First motor; 410. Fixed plate; 5. Adaptive component; 51. Connecting block; 52. Outer shell; 53. Telescopic guide post; 54. First ring plate; 55. Telescopic spring; 56. Telescopic sleeve; 57. Second ring plate; 58. First limit block; 59. Second limit block; 510. H-shaped bracket; 511. Fixed support; 512. Connecting rod; 513. Fixed block; 7. Lifting suction cup. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0025] like Figure 1 As shown, the aircraft skin multi-point adaptive lifting and flipping fixture includes a lifting suction cup 7, a first support plate 1, and a second support plate 11. The fixture is characterized in that the top of the first support plate 1 and the second support plate 11 is provided with an adjustment component 4 for adjusting the lifting to accommodate aircraft skins of different widths. The bottom of the first support plate 1 and the second support plate 11 is respectively provided with a first mounting plate 3 and a second mounting plate 31, with the first mounting plate 3 located directly below the first support plate 1. The bottom of both the first mounting plate 3 and the second mounting plate 31 is provided with multiple adaptive components 5. The bottom end of each adaptive component 5 is provided with a lifting suction cup 7 for adaptive telescopic movement and angle adjustment, and the lifting suction cup 7 adsorbs the aircraft skin.

[0026] In practical implementation, the lifting system includes multiple lifting suction cups 7. These suction cups 7 are the most common type of vacuum suction cup, mainly relying on vacuum suction force to fix objects, making them very suitable for workpieces with flat and smooth surfaces. When operating on the aircraft skin, the lifting suction cups 7 will adhere to the surface of the aircraft skin that has been flipped over. The formation and control of the vacuum environment are achieved through a vacuum generator, and the entire suction cup lifting operation is completed by the mold-specific lifting tool of the electric hoist. The electric hoist can move on the fixed truss, thereby driving the lifting suction cups 7 and the adhered aircraft skin to adjust their positions within a certain range. It should be noted that the lifting suction cups 7, the electric hoist, and the fixed truss all adopt existing technologies; therefore, their specific structures and working principles will not be described in detail in this solution.

[0027] like Figures 1 to 3 As shown, as a technical optimization of this utility model, the adjustment component 4 includes a guide rail plate 41. A sliding groove 42 is formed inside the guide rail plate 41. Sliding blocks 46 are slidably connected to both ends of the sliding groove 42. The bottom ends of the two sliding blocks 46 are respectively fixedly connected to the top center of the first support plate 1 and the second support plate 11. A sleeve plate 47 is fixedly connected to the top of the sliding blocks 46. A bidirectional threaded rod 48 is threadedly connected inside the sleeve plate 47. The two sleeve plates 47 are respectively threaded to the two ends of the bidirectional threaded rod 48. Fixing plates 410 are fixedly connected to both ends of the top of the guide rail plate 41. A first motor 49 is fixedly connected to one side of one of the fixing plates 410. The two ends of the bidirectional threaded rod 48 are rotatably sleeved within the two fixing plates 410. One end of the bidirectional threaded rod 48 passes through the fixing plate 410 and is fixedly connected to the output shaft of the first motor 49. The top ends of the first bracket plate 1 and the second bracket plate 11 are both fixedly installed with fixing support plates 43. The opposing sides of the first bracket plate 1 and the second bracket plate 11 are respectively provided with a support sleeve 45 and a support guide rod 44. The support sleeve 45 and the support guide rod 44 are respectively fixedly connected to the opposing sides of the fixing support plates 43 on the first bracket plate 1 and the second bracket plate 11. The support guide rod 44 is slidably sleeved in the support sleeve 45. The bottom of the first bracket plate 1 and the second bracket plate 11 are both fixedly connected with multiple fixing guide posts 2. The bottom ends of the multiple fixing guide posts 2 are respectively fixedly connected to the top wall of the first mounting plate 3 and the second mounting plate 31.

[0028] In a specific embodiment, when different aircraft flip-over skin widths are different, the first motor 49 drives the bidirectional threaded rod 48 to rotate, and rotates inside the sleeve plate 47, thereby driving the two sleeve plates 47 to move in opposite directions, which in turn drives the two sliding blocks 46 to move. The two sliding blocks 46 move in opposite directions inside the sliding groove 42 of the guide rail plate 41. When the two sleeve plates 47 and the sliding blocks 46 move relative to each other, the first support plate 1 and the second support plate 11 are further moved relative to each other. By adjusting the distance between the first support plate 1 and the second support plate 11, the lifting suction cup 7 can be adapted to different aircraft flip-over skin widths, thereby adsorbing and lifting different aircraft flip-over skins.

[0029] The first motor 49 drives the bidirectional threaded rod 48 to rotate. The forward and reverse threaded structures at both ends of the rod can simultaneously drive the two sleeve plates 47 to move in opposite directions, thereby pushing the first support plate 1 and the second support plate 11 to move towards each other. By adjusting the distance between the first support plate 1 and the second support plate 11, the lifting suction cup 7 can be adapted to different aircraft flip skin widths, thereby adsorbing and lifting different aircraft flip skins.

[0030] like Figure 1 and Figure 2 , Figures 4 to 6 As shown, as a technical optimization of this utility model, the adaptive component 5 includes a connecting block 51. Multiple connecting blocks 51 are fixedly connected to the bottom of both the first mounting plate 3 and the second mounting plate 31. A housing 52 is fixedly connected to the bottom of each connecting block 51. A first ring plate 54 is fixedly connected to the top of the inner part of the housing 52. A telescopic spring 55 is fixedly installed at the lower end of the first ring plate 54. A second ring plate 57 is fixedly connected to the end of the telescopic spring 55 away from the first ring plate 54. A telescopic guide post 53 is fixedly sleeved inside the second ring plate 57. A telescopic sleeve 56 is movably sleeved on the outer side of the telescopic guide post 53. The top of the telescopic sleeve 56 is fixedly connected to the bottom end of the first ring plate 54. Both the telescopic sleeve 56 and the telescopic guide post 53 are located inside the telescopic spring 55. One end of the telescopic guide post 53 is fixedly connected to an H-shaped bracket 510, and the H-shaped bracket 510 is fixedly connected to a "U"-shaped fixed bracket 511. The two ends of the fixed bracket 511 are respectively fixedly connected to the two ends of the H-shaped bracket 510 by bolts. A connecting rod 512 is rotatably connected to the bottom center of the fixed bracket 511. A fixed block 513 is fixedly connected to the bottom end of the connecting rod 512. A lifting suction cup 7 is fixedly installed at the bottom of the fixed block 513. The two sides of the second ring plate 57 are fixedly connected to the first limiting block 58. The bottom of the first limiting block 58 is movably engaged with the second limiting block 59. The two second limiting blocks 59 are respectively fixedly connected to the bottom sides of the outer shell 52 by screws. The second limiting blocks 59 limit the telescopic guide post 53 through the first limiting blocks 58.

[0031] In a specific embodiment, when the adjusting component 4 adjusts the spacing of the lifting suction cups 7 to fit the aircraft skin to be flipped, the lifting device descends, causing the bottoms of multiple lifting suction cups 7 to contact and adhere to the surface of the flipped skin. Since the skin surface is curved or arc-shaped, when each lifting suction cup 7 contacts the skin, the lifting suction cups 7 on both sides will rotate at the middle of the fixed bracket 511 through the upper end of the connecting rod 512. By adjusting the angle of the connecting rod 512, the bottom of the lifting suction cup 7 can adaptively fit the curved surface of the skin to complete the adsorption. At this time, the weight of the lifting suction cup 7 itself drives the telescopic guide post 53 to move downward in the telescopic sleeve 56, stretching the telescopic spring 55. Since there is a height difference between the two sides and the middle of the curved surface of the skin, the descent height of the lifting suction cups 7 on both sides is greater than that in the middle, thereby realizing the automatic adaptation of the bottom of the suction cup to the curved surface of the skin. When the lifting device lifts the skin, the weight of the skin further pulls the telescopic guide post 53 downward. To prevent the guide post from completely moving out of the sleeve, the second limiting block 59 on the outer side of the second ring plate 57 abuts against the surface of the first limiting block 58, thus limiting its position. The vacuum suction cup matrix consists of multiple flexible vacuum suction cups, adaptable to various curved surfaces. Furthermore, in existing technologies, multiple lifting vacuum suction cups are nested inside the fixed block 513 via a spherical rotating structure. This spherical connecting assembly can achieve 360° full-angle rotation and swing within the limiting cavity of the fixed block 513, thereby driving each vacuum suction cup to independently adjust its multi-angle posture. This dynamic adsorption structure allows the vacuum suction cup group to adapt to curved workpieces with different curvatures, forming a three-dimensional array layout that completely conforms to the surface to be adsorbed through coordinated posture changes, ensuring a stable adsorption force distribution even under complex curved surface conditions. Since the multiple lifting vacuum suction cups are nested inside the fixed block 513 via a spherical rotating structure, existing technology is used, and therefore, its specific structure and working principle will not be described in detail in this solution.

[0032] Through the adaptive component 5, the sliding engagement of the telescopic guide post 53 within the sleeve, and the spring tension, the lifting suction cup 7 adaptively adjusts the height difference in the vertical direction, thereby achieving automatic adaptation of the bottom of the lifting suction cup 7 to the curved surface of the skin. When the lifting suction cup 7 contacts the flipped curved skin, the suction cups on both sides rotate at the center of the fixed bracket 511 due to the height difference of the curved surface via the connecting rod 512, forming a multi-free angle adjustment, allowing each lifting suction cup 7 to be adsorbed vertically or against the surface of the flipped curved skin. On the other hand, through the first limiting block 58 and the second limiting block 59, when the weight of the skin pulls the telescopic guide post 53 downward, the second limiting block 59 on the outer side of the second ring plate 57 moves with the guide post. Once it approaches the end of the sleeve, it abuts against the first limiting block 58, forcibly restricting the guide post from continuing to move downward, preventing the guide post from completely detaching from the sleeve and causing the suction cup to fall off.

[0033] In use, when different aircraft skin widths vary, the first motor 49 drives the bidirectional threaded rod 48 to rotate, which in turn rotates inside the sleeve 47. This causes the two sleeves 47 to move in opposite directions, thereby moving the two sliding blocks 46. The two sliding blocks 46 move in opposite directions within the sliding groove 42 of the guide rail plate 41. As the two sleeves 47 and the sliding blocks 46 move relative to each other, the first support plate 1 and the second support plate 11 move relative to each other. Adjusting the distance between the first support plate 1 and the second support plate 11 allows the lifting suction cups 7 to be adapted to different aircraft skin widths, thus adsorbing and lifting different aircraft skins. When the adjusting component 4 adjusts the distance between the lifting suction cups 7 to fit the aircraft skin to be flipped, the lifting device descends, causing the bottoms of the multiple lifting suction cups 7 to contact and adhere to the surface of the flipped skin. Since the skin surface is curved or arc-shaped, when each lifting suction cup 7 contacts the skin, the lifting suction cups 7 on both sides will rotate at the middle of the fixed bracket 511 through the upper end of the connecting rod 512. At the same time, the two sides of the fixed bracket 511 will rotate and swing on both sides of the H-shaped bracket. Through the angle adjustment of the fixed bracket 511 and the connecting rod 512, the bottom of the lifting suction cup 7 can adaptively fit the curved surface of the skin to complete the adsorption. At this time, the weight of the lifting suction cup 7 itself will drive the telescopic guide column 53 to move downward in the telescopic sleeve 56, stretching the telescopic spring 55. Since there is a height difference between the two sides and the middle of the curved surface of the skin, the descent height of the two lifting suction cups 7 is greater than that of the middle position, thereby realizing the automatic adaptation of the bottom of the suction cup to the curved surface of the skin. When the lifting device lifts the skin, the weight of the skin itself will further pull the telescopic guide column 53 downward. In order to prevent the guide column from completely moving out of the sleeve, the second limiting block 59 on the outer side of the second ring plate 57 will abut against the surface of the first limiting block 58 to limit it.

[0034] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model.

Claims

1. An aircraft skin multi-point adaptive lifting and flipping fixture, comprising a lifting suction cup (7), a first support plate (1), and a second support plate (11), characterized in that, The top of the first support plate (1) and the second support plate (11) are provided with adjustment components (4) for adjusting the hoisting to adapt to aircraft skin of different sizes and widths. The bottom of the first support plate (1) and the second support plate (11) are respectively provided with a first mounting plate (3) and a second mounting plate (31), and the first mounting plate (3) is located directly below the first support plate (1). The bottom of the first mounting plate (3) and the second mounting plate (31) are provided with multiple adaptive components (5). The bottom end of the adaptive component (5) is provided with a hoisting suction cup (7) for adaptive telescopic movement and angle adjustment. The hoisting suction cup (7) adsorbs the aircraft skin.

2. The aircraft skin multi-point adaptive lifting and flipping fixture according to claim 1, characterized in that, The adjustment component (4) includes a guide rail plate (41), the inside of which is provided with a sliding groove (42). Sliding blocks (46) are slidably connected to both ends of the sliding groove (42). The bottom ends of the two sliding blocks (46) are respectively fixedly connected to the top center of the first support plate (1) and the second support plate (11). The top end of the sliding block (46) is fixedly connected to a sleeve plate (47). The inside of the sleeve plate (47) is threadedly connected to a bidirectional threaded rod (48). The two sleeve plates (47) are respectively threadedly connected to the two ends of the bidirectional threaded rod (48). The top ends of the guide rail plate (41) are fixedly connected to a fixing plate (410). A first motor (49) is fixedly connected to one side of one of the fixing plates (410). The two ends of the bidirectional threaded rod (48) are respectively rotatably sleeved in the two fixing plates (410). One end of the bidirectional threaded rod (48) passes through the fixing plate (410) and is fixedly connected to the output shaft of the first motor (49).

3. The aircraft skin multi-point adaptive lifting and flipping fixture according to claim 2, characterized in that, Fixed support plates (43) are fixedly installed at both ends of the top of the first support plate (1) and the second support plate (11). Support sleeves (45) and support guide rods (44) are respectively provided on opposite sides of the first support plate (1) and the second support plate (11). The support sleeves (45) and support guide rods (44) are respectively fixedly connected to the opposite sides of the fixed support plates (43) on the first support plate (1) and the second support plate (11). The support guide rods (44) are slidably sleeved in the support sleeves (45).

4. The aircraft skin multi-point adaptive lifting and flipping fixture according to claim 3, characterized in that, The bottom of the first support plate (1) and the second support plate (11) are each fixedly connected with a plurality of fixed guide posts (2), and the bottom ends of the plurality of fixed guide posts (2) are respectively fixedly connected to the top wall panels of the first mounting plate (3) and the second mounting plate (31).

5. The aircraft skin multi-point adaptive lifting and flipping fixture according to claim 4, characterized in that, The adaptive component (5) includes a connecting block (51). Multiple connecting blocks (51) are fixedly connected to the bottom of the first mounting plate (3) and the second mounting plate (31). A housing (52) is fixedly connected to the bottom of the connecting block (51). A first ring plate (54) is fixedly connected to the top of the inner part of the housing (52). A telescopic spring (55) is fixedly installed at the lower end of the first ring plate (54). A second ring plate (57) is fixedly connected to the end of the telescopic spring (55) away from the first ring plate (54). A telescopic guide post (53) is fixedly sleeved inside the second ring plate (57). A telescopic sleeve (56) is movably sleeved on the outer side of the telescopic guide post (53). The top of the telescopic sleeve (56) is fixedly connected to the bottom end of the first ring plate (54). The telescopic sleeve (56) and the telescopic guide post (53) are both located inside the telescopic spring (55).

6. The aircraft skin multi-point adaptive lifting and flipping fixture according to claim 5, characterized in that, One end of the telescopic guide column (53) is fixedly connected to an H-shaped bracket (510), and the H-shaped bracket (510) is fixedly connected to a "U"-shaped fixed bracket (511). The two ends of the fixed bracket (511) are respectively fixedly connected to the two ends of the H-shaped bracket (510) by bolts. A connecting rod (512) is rotatably connected at the bottom center of the fixed bracket (511). A fixed block (513) is fixedly connected to the bottom end of the connecting rod (512), and a lifting suction cup (7) is fixedly installed at the bottom of the fixed block (513).

7. The aircraft skin multi-point adaptive lifting and flipping fixture according to claim 5, characterized in that, The second ring plate (57) is fixedly connected to both sides of the first limiting block (58), and the bottom of the first limiting block (58) is movably engaged with the second limiting block (59). The two second limiting blocks (59) are fixedly connected to the bottom sides of the outer shell (52) by screws. The second limiting blocks (59) limit the telescopic guide post (53) through the first limiting block (58).

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