Auxiliary support for assembling aircraft wings

Abstract

The invention discloses an auxiliary support for assembling aircraft wings, relates to the technical field of application of aircraft manufacturing equipment, and provides the following scheme that the auxiliary support comprises a moving vehicle and further comprises a placing plate which is arranged above the moving vehicle and used for installing and consigning the aircraft wings, and the lower portion of the placing plate comprises a clamping mechanism which is arranged at the bottom of the placing plate and used for transporting and clamping the aircraft wings; the inclination angle adjusting mechanism is arranged between the placing plate and the moving trolley and is used for adjusting the inclination angle of the placing plate; the height adjusting mechanism is arranged between the placing plate and the moving trolley and is used for adjusting the height of the placing plate; and the control assembly is arranged at the bottom of the placing plate and is used for performing driving control on the clamping mechanism. According to the aircraft wing mounting device, rapid adjustment can be conducted according to the mounting height, meanwhile, multi-angle adjustment treatment of the inclination angle can be conducted, the convenience of aircraft wing mounting and rapid clamping and fixing treatment of different aircraft wings are effectively guaranteed, and the effect and efficiency of aircraft wing mounting are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft manufacturing equipment application, in particular to an auxiliary bracket for assembling aircraft wings. Background Art

[0002] In the aircraft manufacturing process, wing assembly is a crucial link. As the key component for generating lift, the connection accuracy between the wing and the fuselage directly affects the flight performance and safety of the aircraft. At present, during wing assembly, due to the complex structure, large size and heavy weight of the wing itself, there are many problems with the existing assembly auxiliary equipment. The common lifting method makes it difficult to accurately fine-tune the attitude of the wing, and the simple support bracket cannot flexibly adapt to the shape and assembly angle requirements of different types of wings, resulting in a large amount of manpower required for position adjustment during the assembly process. This is not only inefficient, but also difficult to ensure assembly accuracy, and it is easy to have deviations in the docking between the wing and the fuselage, affecting the overall quality of the aircraft. To this end, we propose an auxiliary bracket for aircraft wing assembly. Summary of the Invention

[0003] The invention provides an auxiliary bracket for assembling an aircraft wing, which solves the above-mentioned deficiencies in the prior art.

[0004] In order to achieve the above object, the present invention adopts the following technical solutions: An auxiliary support for assembling an aircraft wing, comprising a mobile vehicle and: A placement plate is placed above the mobile vehicle and is used for the installation and transportation of aircraft wings. The placement plate includes: A clamping mechanism, located at the bottom of the placement plate, is used to clamp the aircraft wing during transportation; The tilt adjustment mechanism is located between the placement plate and the mobile vehicle and is used to adjust the tilt angle of the placement plate; Height adjustment mechanism, located between the placement plate and the mobile vehicle, used to adjust the height of the placement plate; The control component is located at the bottom of the placement plate and is used to drive and control the clamping mechanism.

[0005] Furthermore, the clamping mechanism includes two double-headed threaded rods that are rotatably connected to both sides of the bottom of the placement plate, and the two ends of the two double-headed threaded rods are threadedly connected to a movable plate, one side of the movable plate is fixedly connected to a movable frame, the inner side of the movable frame is fixedly connected to a card frame, and the interior of the card frame is hinged with extrusion plates at the upper and lower sides, and the two extrusion plates are fixedly connected to the card frames respectively, and the opposite sides of the two extrusion plates are fixedly connected to a first rubber pad respectively, and two groups of guide rods are symmetrically fixedly connected to the bottom of the placement plate, and threaded holes and guide holes are opened on the movable plate, the double-headed threaded rods are threadedly sleeved inside the threaded holes, and the guide rods are movably sleeved inside the guide holes.

[0006] Furthermore, the height adjustment mechanism includes a threaded sleeve rotatably connected to the top of the mobile vehicle, the internal thread of the threaded sleeve is connected to a threaded rod, the top of the threaded rod is fixedly connected to a linkage plate, the bottom of the threaded sleeve is fixedly connected to a first bevel gear, the top of the mobile vehicle is fixedly connected to a first motor, the output shaft of the first motor is fixedly connected to a second bevel gear, and one side of the second bevel gear is meshed with the first bevel gear for transmission.

[0007] Furthermore, the inclination adjustment mechanism includes two arc-shaped racks symmetrically fixedly connected to the bottom of the placement plate, the two ends of the linkage plate are respectively fixedly connected to support frames, a connecting rod is rotatably connected between the two support frames, the two ends of the connecting rod are respectively fixedly connected to first gears, one side of the two first gears are respectively engaged with two arc-shaped racks for transmission, and a third bevel gear is fixedly connected to the connecting rod.

[0008] Furthermore, a connecting rod is fixedly connected to the connecting plate, one end of the connecting rod is fixedly connected to the fourth bevel gear corresponding to the third bevel gear, one side of the fourth bevel gear is meshed with the third bevel gear for transmission, and the other end of the connecting rod is fixedly connected to the limiting block.

[0009] Furthermore, the top of the mobile vehicle is fixedly connected to a balancing frame, and a linkage sleeve is rotatably connected to the balancing frame. A movable groove is provided on the linkage sleeve corresponding to the limit block, the linkage rod is movably sleeved inside the linkage sleeve, and the limit block is movably sleeved inside the movable groove. A fifth gear is fixedly connected to the bottom of the linkage sleeve, and a second motor is fixedly connected to the bottom of the balancing frame, and an output shaft of the second motor is fixedly connected to a sixth gear. One side of the sixth gear is engaged with the fifth gear for transmission, and a mounting hole is provided on the balancing frame corresponding to the threaded sleeve, and the threaded sleeve is movably sleeved inside the mounting hole.

[0010] Furthermore, the control component includes a motor frame fixedly connected to the bottom of the placement plate, the motor frame is fixedly connected to the third motor, the output shaft of the third motor is fixedly connected to the fifth bevel gear, the bottom of the placement plate is fixedly connected to two limit plates, a transmission rod is rotatably connected between the two limit plates, a sixth bevel gear is fixedly connected to the transmission rod corresponding to the fifth bevel gear, one side of the sixth bevel gear is meshed with the fifth bevel gear for transmission, and the two ends of the transmission rod are respectively movably sleeved with a first staggered tooth plate, a limit spring is provided between the first staggered tooth plate and the limit plate, and the two ends of the transmission rod are respectively movably sleeved inside the limit spring.

[0011] Furthermore, two fixed plates are fixedly connected to the bottom of the placement plate, and auxiliary rods are respectively rotatably connected to the two fixed plates. One end of the two auxiliary rods is fixedly connected to the second staggered tooth plate corresponding to the first staggered tooth plate, and one side of the second staggered tooth plate is engaged with the first staggered tooth plate for transmission, and the other ends of the two auxiliary rods are respectively fixedly connected to the seventh bevel gear.

[0012] Furthermore, an eighth bevel gear is fixedly connected to the double-start threaded rod at a position corresponding to the seventh bevel gear, and one side of the eighth bevel gear is meshed with the seventh bevel gear for transmission.

[0013] Furthermore, a plurality of second rubber pads are fixedly connected to the top array of the placement plate.

[0014] Compared with the existing technology, the beneficial effects of the present invention are: The present invention adjusts the installation position of an aircraft wing by installing a clamping mechanism, a tilt adjustment mechanism, and a height adjustment mechanism. The tilt adjustment mechanism drives the first gear to rotate by rotating a connecting rod, thereby driving the swing of an arc-shaped rack. The swing of the arc-shaped rack drives the swing of the placement plate, thereby adjusting the installation angle of the aircraft wing. The present invention performs power output and power transmission processing on the equipment by installing a control component, wherein the control component drives the rotation of the connecting rod by starting the third motor, and the rotation of the connecting rod drives the synchronous rotation of the double-threaded rod; In summary, the device can not only be quickly adjusted according to the installation height, but also can perform multi-angle adjustment of the tilt angle, effectively ensuring the convenience of aircraft wing installation and rapid clamping and fixing of different aircraft wings, thereby improving the effect and efficiency of aircraft wing installation. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of the overall top-down perspective structure of an auxiliary bracket for assembling an aircraft wing proposed by the present invention; Figure 2 This is a schematic diagram of the overall bottom-up three-dimensional structure of an auxiliary bracket for assembling an aircraft wing proposed by the present invention; Figure 3 This is a top-down perspective structural diagram of a movable plate, a movable frame, and a clamping frame of an auxiliary bracket for assembling an aircraft wing proposed by the present invention; Figure 4 This is a top-down perspective structural diagram of a linkage sleeve and a balancing frame of an auxiliary bracket for assembling an aircraft wing proposed by the present invention; Figure 5 This is a top perspective structural diagram of an inclination adjustment mechanism of an auxiliary bracket for assembling an aircraft wing proposed by the present invention; Figure 6This is a schematic top view of a three-dimensional structure of a partial structure of a height adjustment mechanism of an auxiliary bracket for assembling an aircraft wing proposed by the present invention; Figure 7 This is a bottom-view three-dimensional structural diagram of a connecting rod, a connecting plate, and a threaded rod of an auxiliary bracket for assembling an aircraft wing proposed by the present invention; Figure 8 This is a bottom-up perspective structural diagram of a control assembly and a clamping mechanism of an auxiliary bracket for assembling an aircraft wing proposed by the present invention; Figure 9 This is a schematic diagram of the formal planar structure of a clamping mechanism of an auxiliary bracket for assembling an aircraft wing proposed by the present invention.

[0016] In the figure: 1. Moving vehicle; 2. Placing plate; 3. Clamping mechanism; 301. Double-threaded rod; 302. Moving plate; 303. Moving frame; 304. Card frame; 305. Extrusion plate; 306. Resistance spring; 307. First rubber pad; 308. Guide rod; 309. Eighth bevel gear; 4. Inclination adjustment mechanism; 401. Arc rack; 402. Connecting rod; 403. First gear; 404. Third bevel gear; 405. Support frame; 406. Linking rod; 407. Linking sleeve; 408. Fifth gear; 409. Balancing frame; 410. Second motor; 411, sixth gear; 412, movable slot; 413, fourth bevel gear; 5, height adjustment mechanism; 501, threaded sleeve; 502, threaded rod; 503, linkage plate; 504, first bevel gear; 505, second bevel gear; 506, first motor; 6, second rubber pad; 7, control assembly; 701, third motor; 702, fifth bevel gear; 703, transmission rod; 704, sixth bevel gear; 705, first staggered toothed disc; 706, auxiliary rod; 707, seventh bevel gear; 708, second staggered toothed disc; 709, limit spring. DETAILED DESCRIPTION

[0017] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0018] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and 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 direction, be constructed and operated in a specific direction, and therefore should not be understood as limiting the present invention.

[0019] Example, see Figure 1-9: An auxiliary bracket for assembling an aircraft wing, comprising a mobile vehicle 1, a placement plate 2, a clamping mechanism 3, an inclination adjustment mechanism 4, a height adjustment mechanism 5 and a control component 7; The cam 308 is fixed on the cam 309 and the cam 309 is fixed on the cam 309, and the cam 309 is fixed on the cam 309. The height adjustment mechanism 5 includes a threaded sleeve 501 rotatably connected to the top of the mobile vehicle 1, the internal thread of the threaded sleeve 501 is connected to a threaded rod 502, the top of the threaded rod 502 is fixedly connected to a linkage plate 503, the bottom of the threaded sleeve 501 is fixedly connected to a first bevel gear 504, the top of the mobile vehicle 1 is fixedly connected to a first motor 506, the output shaft of the first motor 506 is fixedly connected to a second bevel gear 505, one side of the second bevel gear 505 is meshed with the first bevel gear 504 for transmission, the start of the first motor 506 drives the rotation of the second bevel gear 505, and the rotation of the second bevel gear 505 drives the synchronous rotation of the first bevel gear 504; The inclination adjustment mechanism 4 includes two arcuate racks 401 symmetrically fixedly connected to the bottom of the placement plate 2, and the two ends of the linkage plate 503 are respectively fixedly connected to the support frames 405. A connecting rod 402 is rotatably connected between the two support frames 405, and the two ends of the connecting rod 402 are respectively fixedly connected to the first gear 403. One side of the two first gears 403 is respectively engaged with the two arcuate racks 401 for transmission. A third bevel gear 404 is fixedly connected to the connecting rod 402. The rotation of the connecting rod 402 drives the rotation of the two first gears 403, and the rotation of the first gear 403 drives the arcuate rack 401 to swing, and at the same time drives the placement plate 2 to swing, thereby driving the aircraft wings to perform synchronous angle adjustment processing.

[0020] In the present invention, a connecting rod 406 is fixedly connected to the connecting plate 503, and one end of the connecting rod 406 is fixedly connected to the fourth bevel gear 413 corresponding to the third bevel gear 404. One side of the fourth bevel gear 413 is engaged with the third bevel gear 404 for transmission, and the other end of the connecting rod 406 is fixedly connected to the limiting block. The rotation of the fourth bevel gear 413 drives the third bevel gear 404 to rotate synchronously, and at the same time drives the connecting rod 402 to rotate synchronously.

[0021] In the present invention, the top of the mobile vehicle 1 is fixedly connected with a balance frame 409, and the linkage sleeve 407 is rotatably connected to the balance frame 409. A moving groove 412 is provided on the linkage sleeve 407 at the corresponding limit block. The linkage rod 406 is movably sleeved inside the linkage sleeve 407, and the limit block is movably sleeved inside the moving groove 412. The fifth gear 408 is fixedly connected to the bottom of the linkage sleeve 407, and the second motor 410 is fixedly connected to the output shaft of the second motor 410. The sixth gear 411 is meshed with the fifth gear 408 for transmission. A mounting hole is provided on the balance frame 409 at the corresponding threaded sleeve 501, and the threaded sleeve 501 is movably sleeved inside the mounting hole. The rotation of the linkage sleeve 407 drives the linkage rod 406 to rotate synchronously through the limit block, and at the same time, the linkage rod 406 is smoothly lifted and lowered along the linkage sleeve 407.

[0022] In the present invention, the control component 7 includes a motor frame fixedly connected to the bottom of the placement plate 2, and a third motor 701 is fixedly connected to the motor frame. The output shaft of the third motor 701 is fixedly connected to the fifth bevel gear 702, and the bottom of the placement plate 2 is fixedly connected to two limit plates. A transmission rod 703 is rotatably connected between the two limit plates, and a sixth bevel gear 704 is fixedly connected to the transmission rod 703 corresponding to the fifth bevel gear 702. One side of the sixth bevel gear 704 is meshed with the fifth bevel gear 702 for transmission. The two ends of the transmission rod 703 are respectively movably sleeved with a first staggered tooth plate 705, and a limit spring 709 is provided between the first staggered tooth plate 705 and the limit plate. The two ends of the transmission rod 703 are respectively movably sleeved inside the limit spring 709. The start of the third motor 701 drives the rotation of the fifth bevel gear 702, and at the same time drives the rotation processing of the transmission rod 703.

[0023] In the present invention, two fixed plates are fixedly connected to the bottom of the placement plate 2, and auxiliary rods 706 are rotatably connected to the two fixed plates. One end of the two auxiliary rods 706 is fixedly connected to the second staggered tooth plate 708 corresponding to the first staggered tooth plate 705, and one side of the second staggered tooth plate 708 is engaged with the first staggered tooth plate 705 for transmission. The other ends of the two auxiliary rods 706 are respectively fixedly connected to the seventh bevel gear 707, and the eighth bevel gear 309 is fixedly connected to the seventh bevel gear 707 corresponding to the double-headed threaded rod 301. One side of the eighth bevel gear 309 is engaged with the seventh bevel gear 707 for transmission. A plurality of second rubber pads 6 are fixedly connected to the top array of the placement plate 2, and the placement of the aircraft wing is protected by the second rubber pads 6.

[0024] Working principle: When in use, place the aircraft wing on the placement plate 2, and at the same time, use the second rubber pad 6 to protect the paint surface of the aircraft wing. The third motor 701 is started to drive the fifth bevel gear 702 to rotate. The rotation of the fifth bevel gear 702 is engaged with the sixth bevel gear 704 to rotate. The rotation of the sixth bevel gear 704 drives the transmission rod 703 to rotate synchronously. The rotation of the transmission rod 703 drives the rotation of the first staggered tooth plate 705, and at the same time, it is engaged with the second staggered tooth plate 708 to drive the rotation of the auxiliary rod 706. The rotation of the auxiliary rod 706 The second bevel gear 707 is driven to rotate, and the rotation of the second bevel gear 707 is meshed with the eighth bevel gear 309, thereby driving the double-threaded rod 301 to rotate. The rotation of the double-threaded rod 301 drives the movable plates 302 at both ends to move smoothly along the guide rod 308. The movement of the movable plate 302 drives the clamping frame 304 to move synchronously through the movable frame 303. When the clamping frame 304 moves, the extrusion plate 305 abuts against the outer surface of the aircraft wing, and the paint surface of the aircraft wing is protected by the first rubber pad 307. When any one of the clamping frames 304 contacts the aircraft wing, the movable plate 302 cannot move further, thereby stopping the double-threaded rod 301 and separating the first staggered toothed disc 705 from the second staggered toothed disc 708 (the staggered toothed disc belongs to the prior art, and the operating principle of the staggered toothed disc is not described in detail here), so that the transmission rod 703 continues to rotate until all the clamping frames 304 clamp and fix the aircraft wing, and the third motor 701 stops running; The first motor 506 is started to drive the second bevel gear 505 to rotate, and at the same time meshes with the first bevel gear 504. The rotation of the first bevel gear 504 drives the rotation of the threaded sleeve 501, so that the threaded rod 502 moves and rises. The movement and rise of the threaded rod 502 drives the linkage plate 503 to move. The movement of the linkage plate 503 drives the support frame 405 to move synchronously. The movement of the support frame 405 drives the placement plate 2 to move and rise synchronously. After the height is adjusted to the installation position, the first motor 506 stops working. When angle tilting is required, the second motor 410 starts to drive the sixth gear 411 to rotate, and the rotation of the sixth gear 411 is engaged with the fifth gear 408 for transmission. The rotation of the fifth gear 408 drives the linkage sleeve 407 to rotate, and at the same time drives the rotation of the linkage rod 406 through the limit block, and the rotation of the linkage rod 406 drives the fourth bevel gear 413 to rotate, and the rotation of the fourth bevel gear 413 is engaged with the third bevel gear 404 for transmission. The rotation of the third bevel gear 404 drives the rotation of the connecting rod 402, and the rotation of the connecting rod 402 drives the rotation of the two first gears 403. The rotation of the first gear 403 drives the arc-shaped rack 401 to swing, and the swing of the arc-shaped rack 401 drives the placement plate 2 to swing. The inclination angle of the aircraft wing is adjusted by the swing of the placement plate 2. After the angle adjustment is completed, the second motor 410 stops running.

[0025] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. An auxiliary support for assembling an aircraft wing, comprising a mobile vehicle (1), characterized in that: Also includes: A placement plate (2) is placed above the mobile vehicle (1) and is used for the installation and transportation of aircraft wings. The placement plate (2) includes: A clamping mechanism (3) is located at the bottom of the placement plate (2) and is used to clamp the aircraft wing during transportation; An inclination adjustment mechanism (4) is located between the placement plate (2) and the mobile vehicle (1) and is used to adjust the inclination angle of the placement plate (2); A height adjustment mechanism (5) is located between the placement plate (2) and the mobile vehicle (1) and is used to adjust the height of the placement plate (2); The control component (7) is located at the bottom of the placement plate (2) and is used to drive and control the clamping mechanism (3). One side of the control component (7) is connected to the clamping mechanism (3).

2. The auxiliary bracket for assembling an aircraft wing according to claim 1, characterized in that: The clamping mechanism (3) comprises two double-headed threaded rods (301) rotatably connected to the two sides of the bottom of the placement plate (2), the two ends of the two double-headed threaded rods (301) are respectively threadedly connected to the movable plate (302), one side of the movable plate (302) is fixedly connected to the movable frame (303), the inner side of the movable frame (303) is fixedly connected to the clamping frame (304), the inner side of the clamping frame (304) is respectively hinged with an extrusion plate (305) at the top and bottom, the two extrusion plates (305) are respectively fixedly connected to the clamping frame (304), the opposite sides of the two extrusion plates (305) are respectively fixedly connected to the first rubber pad (307), the bottom of the placement plate (2) is symmetrically fixedly connected to two groups of guide rods (308), the movable plate (302) is provided with a threaded hole and a guide hole, the double-headed threaded rod (301) is threadedly sleeved inside the threaded hole, and the guide rod (308) is movably sleeved inside the guide hole.

3. The auxiliary bracket for assembling an aircraft wing according to claim 1, characterized in that: The height adjustment mechanism (5) comprises a threaded sleeve (501) rotatably connected to the top of the mobile vehicle (1); the internal thread of the threaded sleeve (501) is connected to a threaded rod (502); the top of the threaded rod (502) is fixedly connected to a linkage plate (503); the bottom of the threaded sleeve (501) is fixedly connected to a first bevel gear (504); the top of the mobile vehicle (1) is fixedly connected to a first motor (506); the output shaft of the first motor (506) is fixedly connected to a second bevel gear (505); and one side of the second bevel gear (505) is meshed with the first bevel gear (504) for transmission.

4. The auxiliary bracket for assembling an aircraft wing according to claim 3, characterized in that: The tilt adjustment mechanism (4) comprises two arc-shaped racks (401) symmetrically fixedly connected to the bottom of the placement plate (2); the two ends of the linkage plate (503) are respectively fixedly connected to support frames (405); a connecting rod (402) is rotatably connected between the two support frames (405); the two ends of the connecting rod (402) are respectively fixedly connected to first gears (403); one side of the two first gears (403) is respectively meshed with the two arc-shaped racks (401) for transmission; and a third bevel gear (404) is fixedly connected to the connecting rod (402).

5. The auxiliary bracket for assembling an aircraft wing according to claim 4, characterized in that: A connecting rod (406) is fixedly connected to the connecting plate (503); one end of the connecting rod (406) is fixedly connected to a fourth bevel gear (413) corresponding to the third bevel gear (404); one side of the fourth bevel gear (413) is meshed with the third bevel gear (404) for transmission; and the other end of the connecting rod (406) is fixedly connected to a limit block.

6. The auxiliary bracket for assembling an aircraft wing according to claim 5, characterized in that: The top of the mobile vehicle (1) is fixedly connected to a balancing frame (409), and a linkage sleeve (407) is rotatably connected to the balancing frame (409). A movable groove (412) is provided on the linkage sleeve (407) at a position corresponding to the limit block. The linkage rod (406) is movably sleeved inside the linkage sleeve (407), and the limit block is movably sleeved inside the movable groove (412). A fifth gear (408) is fixedly connected below the linkage sleeve (407). The bottom of the balancing frame (409) is fixedly connected to a second motor (410), and an output shaft of the second motor (410) is fixedly connected to a sixth gear (411). One side of the sixth gear (411) is meshed with the fifth gear (408) for transmission. A mounting hole is provided on the balancing frame (409) at a position corresponding to the threaded sleeve (501), and the threaded sleeve (501) is movably sleeved inside the mounting hole.

7. The auxiliary bracket for assembling an aircraft wing according to claim 2, characterized in that: The control assembly (7) comprises a motor frame fixedly connected to the bottom of the placement plate (2), a third motor (701) fixedly connected to the motor frame, an output shaft of the third motor (701) fixedly connected to a fifth bevel gear (702), two limit plates fixedly connected to the bottom of the placement plate (2), a transmission rod (703) rotatably connected between the two limit plates, a sixth bevel gear (704) fixedly connected to the transmission rod (703) at a position corresponding to the fifth bevel gear (702), one side of the sixth bevel gear (704) meshing with the fifth bevel gear (702) for transmission, first staggered toothed discs (705) movably sleeved on both ends of the transmission rod (703), a limit spring (709) provided between the first staggered toothed disc (705) and the limit plate, and two ends of the transmission rod (703) movably sleeved inside the limit spring (709).

8. The auxiliary bracket for assembling an aircraft wing according to claim 7, characterized in that: The bottom of the placement plate (2) is fixedly connected to two fixed plates, and the two fixed plates are rotatably connected to auxiliary rods (706), one end of the two auxiliary rods (706) is fixedly connected to a second staggered toothed disc (708) corresponding to the first staggered toothed disc (705), one side of the second staggered toothed disc (708) is meshed with the first staggered toothed disc (705) for transmission, and the other ends of the two auxiliary rods (706) are fixedly connected to a seventh bevel gear (707).

9. The auxiliary bracket for assembling an aircraft wing according to claim 8, characterized in that: An eighth bevel gear (309) is fixedly connected to the double-ended threaded rod (301) at a position corresponding to the seventh bevel gear (707), and one side of the eighth bevel gear (309) is meshed with the seventh bevel gear (707) for transmission.

10. The auxiliary bracket for assembling an aircraft wing according to claim 1, characterized in that: A plurality of second rubber pads (6) are fixedly connected to the top array of the placement plate (2).

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