Aircraft wing box hoisting aid

Abstract

The application discloses an airplane wing box hoisting auxiliary device and belongs to the transportation field. The auxiliary device comprises an auxiliary traction mechanism fixed at the top end of a trailer, and the auxiliary traction mechanism is used for upward and downward traction of the wing. The auxiliary traction mechanism comprises a plurality of groups of slidingly arranged traction mechanisms. The traction mechanism comprises a movable mounting plate slidingly arranged at the top end of the trailer. The movable mounting plate is rotationally provided with a U-shaped groove. An installation head is slidingly arranged on the U-shaped groove. A length-adjustable rotating seat is rotationally arranged on the installation head. A plurality of groups of telescopic assemblies are rotationally arranged on the rotating seat. The telescopic assemblies have a telescopic function. Suction cups are arranged on the plurality of groups of telescopic assemblies. The suction cups in the application can be attached to the two side surfaces of the wing and attract the wing, so that the wing is limited from shaking and stable lifting and falling of the wing are realized.

Description

Technical Field

[0001] This invention relates to the field of transportation, and in particular to an auxiliary device for hoisting aircraft wing boxes. Background Technology

[0002] Aircraft wings are the core aerodynamic components that ensure flight. Their core function is to generate lift through the air pressure difference between the upper and lower surfaces of the airfoil, supporting the aircraft to take off and maintain stable flight. They also have functions such as maintaining lateral balance, controlling flight attitude, and carrying payloads. They have internal fuel tanks to store fuel, and can carry engines, avionics, etc. Their design directly determines the aircraft's flight performance, fuel efficiency, and flight safety.

[0003] The transportation of aircraft wings must take into account their large size (such as the C919's 38.9m wing length), carbon fiber composite body, and precision components such as integrated winglets / engine pylons / avionics interfaces. The core principles are "maintaining attitude stability, strengthening precise protection, real-time risk monitoring, and standardizing operating procedures" to avoid stress concentration, vibration damage, or functional failure during transportation.

[0004] Specialized transport trailers are required during aircraft transportation. Ordinary trailers cannot meet the requirements for size adaptation, stress protection, and stable transportation. Specialized trailers, through customization, ultimately ensure the safety of wing transportation and the accuracy of subsequent assembly. The lifting, installation, and transfer of the wing are usually carried out in conjunction with a crane. The wing is secured with lifting ropes and then lifted by the crane. During the lifting process, the lifting ropes will inevitably sway, causing the wing to swing back and forth. It is necessary to manually pull it to prevent it from swinging too much and hitting the trailer, which would cause damage to the wing. Summary of the Invention

[0005] This invention provides an auxiliary device for lifting aircraft wing boxes, which can solve the problem of the wing swinging back and forth and hitting the trailer during the lifting process in the prior art.

[0006] An auxiliary device for lifting an aircraft wing box includes an auxiliary traction mechanism fixed to the top of a trailer, which is used to lift the wing vertically. The auxiliary traction mechanism includes several sets of slidably arranged traction mechanisms. Each traction mechanism includes a movable mounting plate slidably arranged on the top of the trailer. The movable mounting plate is rotatably provided with a U-shaped groove. A mounting head is slidably provided on the U-shaped groove. An adjustable rotating seat is rotatably provided on the mounting head. Several sets of telescopic components are rotatably provided on the rotating seat. The telescopic components have a telescopic function, and each set of telescopic components is provided with a suction cup.

[0007] Furthermore, the auxiliary traction mechanism also includes a housing, within which several sets of traction mechanisms are slidably arranged.

[0008] Furthermore, the traction mechanism includes a slide groove 802 located at the bottom of the equipment housing. A movable mounting plate is slidably mounted on the slide groove. A U-shaped groove is rotatably mounted on the movable mounting plate. A threaded rod is rotatably mounted on the U-shaped groove. A mounting head is threadedly fitted onto the threaded rod. Two second connecting pieces are rotatably mounted on the mounting head. Two gears are rotatably mounted on the mounting head. The two gears mesh and drive each other. The two gears are coaxial with and fixedly connected to the two second connecting pieces respectively. A first motor is mounted on one of the gears. The first motor is fixed to the mounting head.

[0009] Furthermore, each of the two second connecting members is fixedly equipped with a second telescopic cylinder, and the output end of each of the two second telescopic cylinders is fixedly connected to a rotating seat. A rotating block is rotatably provided inside the rotating seat, and the rotating block and the rotating seat are driven by a motor. Suction cups are fixedly provided at the ends of several sets of telescopic components.

[0010] Furthermore, the telescopic assembly includes a telescopic rod, and a spring is sleeved on the outside of the telescopic rod.

[0011] Furthermore, the U-shaped groove is provided in two sets, and sprockets are provided between the two sets of U-shaped grooves and the two sets of movable mounting plates. The sprockets are fixedly connected to the U-shaped grooves, and a chain is connected between the two sets of sprockets.

[0012] Furthermore, one set of the sprockets is equipped with a drive source.

[0013] Beneficial effects

[0014] 1. This invention provides a wing box hoisting auxiliary device. When it is necessary to install the wing onto the trailer, the suction cups can be attached to both sides of the wing to attract the wing and limit its swaying. As the hoisting mechanism adjusts the wing to descend to the installation position, the installation head moves downward under the drive of the threaded rod, avoiding swaying during the wing's descent and protecting the wing. In this process, the hoisting mechanism bears the main pulling force, and the traction mechanism provides auxiliary traction force. The two work together to achieve the wing's descent.

[0015] 2. When the wing is transported to the designated location and needs to be unloaded, the wing must first be secured using a lifting mechanism. Then, the airbag is deflated to allow operating space for lifting. Then, the same adjustment method as above is used to attract the upper and lower surfaces of the suction cup wing. The lifting mechanism lifts the wing upwards, and the traction mechanism moves upwards in coordination with the lifting mechanism to smoothly lift the wing to the trailer area, avoiding swaying of the wing during the lifting process and collision with the trailer. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the trailer structure of the present invention; Figure 2 For the present invention Figure 1 Enlarged structure of section A; Figure 3 This is a schematic diagram showing the distribution of protection zone a and protection zone b in this invention; Figure 4 This is a side view of the first protective component of the present invention; Figure 5 This is a schematic diagram of the structure of the first protective component of the present invention; Figure 6 This is a schematic diagram of the protective cover structure of the present invention; Figure 7 This is a front view of the interior of the protective cover of the present invention; Figure 8 This is a schematic diagram of the semi-protective shield structure of the present invention; Figure 9 For the present invention Figure 8 Enlarged schematic diagram of section B; Figure 10 This is a schematic diagram of the overall structure of the auxiliary traction mechanism of the present invention; Figure 11 This is a schematic diagram of the internal structure of the auxiliary traction mechanism of the present invention; Figure 12 This is a top view of the auxiliary traction mechanism of the present invention; Figure 13 This is a schematic diagram of the auxiliary traction mechanism of the present invention.

[0017] Explanation of reference numerals in the attached figures: 1. Vehicle body; 2. Wing door; 3. Front door; 4. First fixed bracket; 5. Support base; 6. Third fixed bracket; 7. Pressure plate; 8. Auxiliary traction mechanism; 9. Second fixed bracket; 10. Mounting bracket; 11. Positioning hole; 12. Mounting hole; 13. First splicing bracket; 14. Second splicing bracket; 15. First connector; 16. First mounting plate; 17. First telescopic cylinder; 18. Mounting back plate; 19. Protective airbag; 20. Semi-protective cover; 801. Equipment shell; 802. Slide groove; 803. U 804. Slot; 805. Movable mounting plate; 806. Threaded rod; 807. Mounting head; 808. Second connecting piece; 809. Gear; 8001. First motor; 810. Second telescopic cylinder; 811. Rotating seat; 812. Rotating block; 813. Telescopic rod; 814. Spring; 815. Suction cup; 816. Chain; 201. Arc-shaped protective shell; 202. Tail end; 203. Connecting seat; 204. Slot; 205. Pneumatic pin; 206. Air inlet pipe; 207. Positioning rod; 208. Buffer zone. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] Due to their large size (e.g., the C919's wing is 38.9m long), high value, composite material body, and precision components such as engine pylons and avionics interfaces, aircraft wings cannot be adequately supported by ordinary trailers in terms of size adaptation, stress protection, and stable transportation. Specialized trailers, through customized load-bearing frames, airfoil-adaptive flexible supports, dynamic shock absorption, and precise attitude control systems, can match the wing's center of gravity and installation angle, preventing stress concentration, vibration damage, or failure of precision components during transportation. They are also suitable for narrow paths and loading / unloading scenarios in airports and workshops, ultimately ensuring the safety of wing transportation and the accuracy of subsequent assembly.

[0020] like Figure 1 As shown, this is an aircraft wing box transport trailer. The trailer includes a vehicle body 1 adapted to the shape of the wing. Both sides of the vehicle body 1 are equipped with automatically opening and closing wing doors 2. Both sides of the front of the vehicle body 1 are also equipped with rotatable front doors 3. When the wing doors 2 are fully opened, they can be placed horizontally on the ground. When the wing doors 2 and front doors 3 on the same side are fully closed, they form a complete side door. The wing doors 2 on both sides of the vehicle body 1 are used to fix the two wings respectively. When in use, the wing door 2 and front door 3 on one side must be fully opened first. Then, the wing is horizontally hoisted to the wing door 2 by a crane and fixed to the wing door 2. Only after the wing door 2 and front door 3 on one side are fixed can the other wing be hoisted and fixed to avoid the trailer tilting on one side and causing damage to the wing.

[0021] like Figure 1As shown, a first fixed bracket 4 is also fixedly installed in the middle of the vehicle body 1. The first fixed bracket 4 is constructed from multiple steel components, and its shape is adapted to the shape of the wing. After the wing door 2 and the front door 3 are closed, the wing is located between the wing door 2 and the first fixed bracket 4. Several support seats 5 are also fixedly installed on the wing door 2. The support seats 5 cooperate with the designated positions of the wing to fix the wing. The support seats 5 are custom-made parts for the wing to ensure that they are absolutely matched with the shape and installation position of the wing. A second fixed bracket 9 is also installed on the surface of the wing door 2 and the front door 3. The second fixed bracket 9 is fixed to the inner surface of the wing door 2 and the front door 3. The structure is constructed from several steel components. The wing door 2 is also equipped with a movable bracket for fixing the wing. The movable bracket includes a third fixed bracket 6 on a fixed second fixed bracket 9. A pressure plate 7 is rotatably mounted on the third fixed bracket 6. In use, the wing is horizontally hoisted onto several support seats 5 and the third fixed bracket 6 on the wing door 2 using hoisting equipment. Then, the wing door 2 is connected and fixed to several support seats 5 at a designated position. The pressure plate 7 is then rotated to the upper surface of the wing to fix the wing between the third fixed bracket 6 and the pressure plate 7. The wing door 2 and the front door 3 are then closed. The same steps are then used to install the wing on the other side.

[0022] However, in the above-mentioned fixing method, the wing is directly fixed between several support seats 5 and movable brackets. However, there is a gap between the several support seats 5 and movable brackets and the second fixed bracket 9 on the wing door 2, and the edge of the wing is close to the edge of the wing door 2. During transportation, the wing may collide with the door due to inertia, causing contact damage to the wing. Therefore, this embodiment also has a special protective device to provide all-round protection for the wing.

[0023] Specifically, such as Figure 3 As shown, this embodiment adds a protective zone a to the gap between the wing door 2 and the first fixed bracket 4 and the wing, including a1 protective zone, a2 protective zone, a3 protective zone, a4 protective zone, a5 protective zone and a6 protective zone. Among them, the a1-a5 protective zones are located at the wing door 2, and the a6 protective zone is located at the first fixed bracket 4. Each of a1-a6 is equipped with a first protective component that is adapted to the shape of the area, which can protect both sides of the wing respectively and avoid contact damage to the wing during transportation.

[0024] like Figure 4 and Figure 5As shown, the first protective component includes a first splicing bracket 13 and a second splicing bracket 14. The first splicing bracket 13 and the second splicing bracket 14 are connected by a first connector 15. The first connector 15 is made of rubber and can be installed at different angles. A first telescopic cylinder 17 is fixedly mounted on both the first splicing bracket 13 and the second splicing bracket 14 by a first mounting plate 16. A silicone protective layer is also provided between the first mounting plate 16 and the first telescopic cylinder 17 for further buffering and protection. The output end of the first telescopic cylinder 17 is fixedly provided with a mounting backplate 18. The same protective airbag 19 is installed on both mounting backplates 18. In use, the first splicing bracket 13 is fixed on the first fixed bracket 4 at the horizontal position of the wing door 2, and the second splicing bracket 14 is fixed on the first fixed bracket 4 at the edge of the wing door 2. Since there is a curvature at the edge of the wing door 2 and at the horizontal position, the first splicing bracket 13 and the second splicing bracket 14 are adapted to it. The first splicing bracket 13 and the second splicing bracket 14 can be adjusted to any angle to adapt to it through the first connector 15. The protective airbag 19 has a built-in high-precision pressure sensor and automatically adjusts the airbag inflation volume through the hydraulic system to completely fit the curvature of the wing surface and avoid stress concentration on the composite material wing surface.

[0025] In this embodiment, the protective airbag 19 has a preset airfoil reference curve (e.g., extracted from a 3D model of the C919 wing surface). After inflation, its initial shape conforms to the median curvature of the airfoil. Several miniature pressure sensors are evenly distributed on the surface of the protective airbag 19 to detect the contact pressure with the wing in real time. When the pressure in a certain area is too low, the controller drives the corresponding zone to inflate; when the pressure is too high, it automatically depressurizes to ensure uniform pressure across the entire contact surface. A displacement sensor is located at the bottom of the protective airbag 19 to collect real-time height data, which is compared with the theoretical height on the wing surface. A hydraulic cylinder dynamically compensates for this height difference, and by controlling the extension and retraction of the first telescopic cylinder 17, it ensures that the protective airbag 19 is completely fitted to the wing.

[0026] The first splicing bracket 13 and the second splicing bracket 14 on the first fixed bracket 4 are installed vertically. After the wing door 2 is closed, the protective airbag 19 on the first fixed bracket 4 can protect the bottom and sides of the wing, and together with the protective airbag 19 on the wing door 2, it can achieve full-wrap protection for one side of the wing.

[0027] Because the wingtip area is structurally fragile and integrates precision critical components, it is susceptible to collision damage during transportation, loading and unloading, and ground parking. Therefore, this embodiment also adds an additional second protective component to the wingtip area to prevent wing failure, reduce maintenance costs, and ensure flight safety and assembly accuracy.

[0028] Specifically, such as Figure 3As shown, the second protective component is located in protective zone b, which includes protective zone b2 located at the front door 3 and protective zone b1 located at the front end of the first fixed bracket 4. During hoisting, the tip of the wing is located at the front door 3, as shown... Figure 1 and Figure 2 As shown, the front door 3 and the corresponding first fixed bracket 4 are both provided with mounting brackets 10. The mounting brackets 10 are fixedly mounted on the front door 3 and the first fixed bracket 4. The mounting brackets 10 are provided with positioning holes 11 and several mounting holes 12.

[0029] like Figure 6 As shown, protective covers for protecting the wingtips are installed on the mounting brackets 10 at both locations. The protective covers are formed by splicing two half-protective covers 20. One half-protective cover 20 is fixed on the mounting bracket 10 on the first fixed bracket 4, and the other half-protective cover 20 is installed on the mounting bracket 10 on the front door 3. A pneumatic latch is provided at the splicing point of the two half-protective covers 20, that is, the two half-protective covers 20 can be automatically locked after splicing to achieve splicing.

[0030] Specifically, such as Figure 7-9 As shown, the semi-protective cover 20 includes an arc-shaped protective shell 201. One end of the arc-shaped protective shell 201 is connected to a tail end 202. The arc-shaped protective shell 201 is provided with a connecting component. The semi-protective cover 20 is connected to two mounting brackets 10 through the connecting component. Specifically, the connecting component includes a connecting seat 203 fixed to the outside of the arc-shaped protective shell 201. The connecting seat 203 has a slot 204. A positioning rod 207 is also fixed in the slot 204. Pneumatic pins 205 are also provided on both sides of the slot 204 on the connecting seat 203. The connecting seat 203 is provided with several air inlet pipes 206. In use, the mounting bracket 10 is snapped into the slot 204, and the positioning rod 207 is engaged with the positioning hole 11 on the mounting bracket 10. The pneumatic pins 205 are then inserted into the mounting hole 12 on the mounting bracket 10 to lock the mounting bracket 10, thereby fixing the arc-shaped protective shell 201 to the mounting bracket 10.

[0031] In this embodiment, the arc-shaped protective shell 201 is also equipped with a second protective airbag, and a buffer zone 208 is fixedly installed inside the two arc-shaped protective shells 201. The buffer zone 208 is connected to the tail end 202. The buffer zone 208 is not equipped with a second protective airbag. In use, the two arc-shaped protective shells 201 are first fixed to the mounting brackets 10 at two locations. After the wing door 2 is closed, the wing tip moves to the fixed end of the arc-shaped protective shell 201. Then the front door 3 is closed to achieve splicing of the two arc-shaped protective shells 201. The second protective airbag is inflated and fits against the wing tip. The tip of the wing is located at the position of the buffer zone 208. The buffer zone 208 is a reserved buffer area to allow for the movement of the wing tip and prevent the tip from contacting the transport vehicle under inertia, thus avoiding damage to the precision equipment at the tip. When the wing is transported to the designated location and needs to be unloaded and installed, the two arc-shaped protective shells 201 can be directly removed from the mounting bracket 10, so that the protective shell is fixed at the tip of the wing and lifted synchronously with the wing, avoiding the wing from shaking during the lifting process and causing damage to the wing tip.

[0032] Since the lifting and installation of aircraft wings are usually carried out in conjunction with a crane, the wing is fixed with a sling and then lifted by the crane. During the lifting process, the sling will inevitably sway, causing the wing to swing back and forth. It is necessary to manually pull it to prevent the swing amplitude from being too large. In view of this situation, this embodiment also proposes an aircraft wing box lifting auxiliary device to assist in the lifting of the wing and avoid excessive swaying of the wing during the process.

[0033] like Figure 1 As shown, the auxiliary traction mechanism 8 is fixedly mounted on the top of the vehicle body 1, as... Figure 10 As shown, the auxiliary traction mechanism 8 includes a housing 801, within which several sets of traction mechanisms are slidably arranged. All sets of traction mechanisms have identical structures. Taking one set of traction mechanisms as an example, the traction mechanism includes a sliding groove 802 located at the bottom of the housing 801. Figure 11As shown, a movable mounting plate 804 is slidably mounted on the slide groove 802. A U-shaped groove 803 is rotatably mounted on the movable mounting plate 804. A threaded rod 805 is rotatably mounted on the U-shaped groove 803. A mounting head 806 is threadedly fitted onto the threaded rod 805. Two second connecting parts 807 are rotatably mounted on the mounting head 806. Two gears 808 are rotatably mounted on the mounting head 806. The two gears 808 mesh and transmit power to each other. The two gears 808 are coaxial with and fixedly connected to the two second connecting parts 807 respectively. A first motor 809 is mounted on one of the gears 808. The first motor 809 is fixed to the mounting head 806. The first motor 809 drives the gear 808 to rotate, thereby realizing the opening and closing movement of the two second connecting parts 807. The second connector 807 is fixedly provided with a second telescopic cylinder 810. The output ends of the two second telescopic cylinders 810 are fixedly connected to a rotating seat 811. A rotating block 812 is rotatably provided inside the rotating seat 811. The rotating block 812 and the rotating seat 811 are driven by a motor. Several sets of telescopic components are fixedly provided on the rotating seat 811. The ends of the several sets of telescopic components are fixedly provided with suction cups 815. In this embodiment, one set of telescopic components is used as an example. However, when implementing this technical solution, the number of telescopic components can be any number greater than one set. The telescopic component includes a telescopic rod 813. A spring 814 is sleeved on the outside of the telescopic rod 813. In this embodiment, the suction cup 815 is a flexible vacuum suction cup. The shape of the suction cup 815 can change with the shape of the adsorption position.

[0034] In this embodiment, there are two sets of traction mechanisms. However, in implementing this technical solution, the number of traction mechanisms can be any number greater than one set. In this embodiment, the sliding method between the two sets of traction mechanisms and the slide groove 802 includes, but is not limited to, using gear and rack transmission. The sliding method between the traction mechanism and the slide groove 802 is a conventional technical means well known to those skilled in the art, and will not be described in detail here.

[0035] In this embodiment, the U-shaped groove 803 is also provided in two sets, and the two sets of U-shaped grooves 803 rotate synchronously. This embodiment provides one method of rotation of the U-shaped groove 803, but other methods of achieving rotation of the U-shaped groove 803 are also included in the implementation of this technical solution. Specifically, as follows... Figure 12 As shown, sprockets are provided between the two sets of U-shaped grooves 803 and the two sets of movable mounting plates 804. The sprockets are fixedly connected to the U-shaped grooves 803, that is, the rotation of the sprockets can realize the rotation of the U-shaped grooves 803. A chain 816 is connected between the two sets of sprockets. One set of sprockets is equipped with a drive source. The drive source drives the two sets of sprockets to rotate synchronously, thereby realizing the rotation of the two sets of U-shaped grooves 803.

[0036] like Figure 11 and 13As shown, during use, when the wing needs to be installed onto the trailer, firstly, the two sets of movable mounting plates 804 are moved outside the equipment housing 801, and then the two sets of U-shaped grooves 803 are driven to rotate 90 degrees, so that the U-shaped grooves 803 rotate to a position perpendicular to the equipment housing 801. The first motor 809 drives the two second telescopic cylinders 810 to rotate, so that they rotate to their maximum angle. As the wing is hoisted above the wing door 2, the second telescopic cylinders 810 rotate and change length accordingly, thereby adjusting the position of the rotating seat 811. The rotating seat 811 is brought close to the upper and lower surfaces of the wing. Then, the telescopic rod 813 is rotated to make the suction cup 815 fit against the two sides of the wing and attract the wing, limiting the wing from swaying. As the lifting mechanism adjusts the wing to the installation position, the installation head 806 moves downward under the drive of the threaded rod 805, avoiding swaying during the wing's descent. The wing plays a protective role. During this process, the lifting mechanism bears the main pulling force, and the traction mechanism provides auxiliary traction force. The two work together to achieve the wing's descent.

[0037] When the wing is transported to the designated location and needs to be unloaded, the lifting mechanism is first used to fix the wing in place. Then, the airbag is deflated to make room for the lifting operation. Then, the same adjustment method as above is used to attract the upper and lower surfaces of the suction cup 815 wing. The lifting mechanism lifts the wing upward, and the traction mechanism moves upward in coordination with the lifting mechanism to smoothly lift the wing to the trailer area, avoiding swaying of the wing and collision with the trailer during the lifting process.

[0038] In the description of this invention, it should be understood that the terms "upper," "lower," "left," and "right," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or a specific orientational structure and operation. Therefore, they should not be construed as limitations on the invention. Furthermore, "first" and "second" are only for descriptive purposes and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "multiple" means two or more.

[0039] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0040] The foregoing has provided a detailed description of one embodiment of the present invention, but this description is merely a preferred embodiment and should not be construed as limiting the scope of the invention. All equivalent variations and modifications made within the scope of the claims of this invention should still fall within the patent coverage of this invention.

Claims

1. An auxiliary device for hoisting aircraft wing boxes, characterized in that, Includes an auxiliary traction mechanism (8) fixed to the top of the trailer, which is used to pull the wings up and down; The auxiliary traction mechanism (8) includes several sets of slidably arranged traction mechanisms. The traction mechanism includes a movable mounting plate (804) slidably arranged on the top of the trailer. The movable mounting plate (804) is rotatably provided with a U-shaped groove (803). A mounting head (806) is slidably provided on the U-shaped groove (803). A rotating seat (811) with adjustable length is rotatably provided on the mounting head (806). Several sets of telescopic components are rotatably provided on the rotating seat (811). The telescopic components have telescopic functions. Each set of telescopic components is provided with a suction cup (815). The lifting mechanism bears the main pulling force, and the auxiliary traction mechanism (8) provides auxiliary traction force. The two work together to lift or lower the wing. The auxiliary traction mechanism (8) also includes a housing (801), and several sets of traction mechanisms are slidably arranged inside the housing (801); The traction mechanism includes a slide groove (802) located at the bottom of the equipment housing (801), a movable mounting plate (804) slidably mounted on the slide groove (802), a U-shaped groove (803) rotatably mounted on the movable mounting plate (804), a threaded rod (805) rotatably mounted on the U-shaped groove (803), a mounting head (806) threadedly fitted on the threaded rod (805), two second connecting pieces (807) rotatably mounted on the mounting head (806), and two gears (808) rotatably mounted on the mounting head (806). The two gears (808) mesh and drive each other, and the two gears (808) are coaxial and fixedly connected to the two second connecting pieces (807) respectively. A first motor (809) is mounted on one of the gears (808), and the first motor (809) is fixed on the mounting head (806). Two second connecting parts (807) are each fixedly provided with a second telescopic cylinder (810), and the output end of the two second telescopic cylinders (810) is fixedly connected with a rotating seat (811). A rotating block (812) is rotatably provided inside the rotating seat (811). The rotating block (812) and the rotating seat (811) are driven by a motor. Suction cups (815) are fixedly provided at the ends of several sets of telescopic components.

2. The aircraft wing box hoisting auxiliary device as described in claim 1, characterized in that, The telescopic assembly includes a telescopic rod (813), and a spring (814) is sleeved on the outside of the telescopic rod (813).

3. The aircraft wing box hoisting auxiliary device as described in claim 1, characterized in that, The suction cup (815) is a flexible vacuum suction cup.

4. The aircraft wing box hoisting auxiliary device as described in claim 1, characterized in that, The U-shaped groove (803) is provided in two sets. A sprocket is provided between the two sets of U-shaped grooves (803) and the two sets of movable mounting plates (804). The sprocket is fixedly connected to the U-shaped groove (803), and a chain (816) is connected between the two sets of sprockets.

5. The aircraft wing box hoisting auxiliary device as described in claim 4, characterized in that, One set of sprockets is equipped with a drive source.

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