Airplane beam assembly turnover device

Abstract

The utility model relates to an airplane beam assembly turnover device which comprises a turnover table, a turnover support is arranged at the upper end of the turnover table, a turnover arm is arranged at one end of the turnover table, a supporting arm is arranged at the other end of the turnover table, and the turnover arm is connected with a turnover motor through the turnover support. The overturning arm is overturned through the overturning motor, so that the labor intensity of processing personnel is reduced, and the production efficiency is improved; the overturning arm is provided with a magnet and a clamping device, the supporting arm is provided with a magnet, it is guaranteed that the aircraft beams cannot fall off in the overturning process, the personal safety of machining personnel is guaranteed, meanwhile, the supporting arm and the overturning arm are each provided with an adjusting hand wheel, corresponding adjustment can be conducted according to the sizes of the different aircraft beams, and the universal design is achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of automobile manufacturing, in particular to an aircraft beam assembly turning device. Background Art

[0002] The aircraft beam assembly of a heavy truck frame is generally made of riveted crossbeams and connecting plates. It is assembled at the rear axle position of the frame and is an important load-bearing structure of the frame. During assembly, the processing personnel place the crossbeam on the workbench, place the lower left and right connecting plates according to the drawings, insert rivets and rivet. Then two processing personnel hold the connecting plates on both sides of the crossbeam and flip the aircraft beam assembly over. Then install the upper left and right connecting plates according to the drawings, insert rivets and rivet. After the aircraft beam assembly is riveted, it is hoisted to the storage area with a hoist. The weight of aircraft beam assemblies of different structures is different, about 80-230kg. Its weight is relatively large, so manual flipping is labor-intensive. Utility Model Content

[0003] The utility model aims to provide an aircraft beam assembly flipping device in view of the deficiencies in the prior art.

[0004] The utility model is realized by adopting the following technical solutions:

[0005] An aircraft beam assembly flipping device comprises a flipping platform, wherein a flip bracket is provided at the upper end of the flipping platform, a flip arm is provided at one end of the flipping platform, a support arm is provided at the other end of the flipping platform, and the flip arm is connected to a flip motor through the flip bracket.

[0006] Preferably, one end of the flip arm is connected to the flip motor through the flip bracket, and the other end of the flip arm is provided with a first adjusting slide rail and a first adjusting handwheel, the first adjusting slide rail is provided with a first adjusting slider, the upper end of the first adjusting slider is provided with a mounting plate, the mounting plate is provided with a clamping device and a magnet, and the lower end of the first adjusting slider is connected to the first adjusting handwheel through a first connecting block.

[0007] Preferably, the clamping device includes two groups of clamping cylinders, the two groups of clamping cylinders are arranged opposite to each other, the magnet includes a longitudinal magnet and a first transverse magnet, the lower end of the clamping cylinder is fixedly connected to the mounting plate, the upper end of the clamping cylinder is provided with a limit plate, longitudinal magnets are provided on both sides of the limit plate, the lower end of the longitudinal magnet is provided with a first transverse magnet, the aircraft beam is provided between the two groups of clamping cylinders, and the aircraft beam is located at the upper end of the first transverse magnet.

[0008] Preferably, the first adjusting slider is further provided with a width ruler, the flip arm is provided with a protective cover, an opening is provided on the outer side of the protective cover, and the width ruler passes through the opening and is located outside the protective cover.

[0009] Preferably, a height adjustment rail and a limit latch are provided at one end of the support arm, and the turning platform is provided with a height adjustment slider and a plurality of latch holes, the height adjustment rail is connected to the height adjustment slider, and is limited by the limit latch and the latch hole; a second adjustment rail is provided at the other end of the support arm, the second adjustment rail is provided with a second adjustment slider, a second transverse magnet is provided at the upper end of the second adjustment slider, a second connecting block is provided at the lower end of the second adjustment slider, the second connecting block is connected to the second width adjustment hand wheel, and the aircraft beam is provided at the upper end of the second transverse magnet.

[0010] Compared with the prior art, the utility model has the following beneficial technical effects:

[0011] The flipping motor is used to flip the flip arm, which reduces the labor intensity of the processing personnel and improves the production efficiency. The flip arm is equipped with a magnet and a clamping device, and the support arm is equipped with a magnet to ensure that the aircraft beam will not fall during the flipping process, thereby ensuring the personal safety of the processing personnel. At the same time, the support arm and the flip arm are equipped with adjustment hand wheels, which can be adjusted accordingly according to the sizes of different aircraft beams to achieve a universal design. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0013] Figure 2 It is a structural schematic diagram of the flip arm in the utility model;

[0014] Figure 3 for Figure 2 The enlarged view of point A in the middle;

[0015] Figure 4 It is a structural schematic diagram of the support arm in the utility model;

[0016] Figure 5 This is a schematic diagram of the structure of the second embodiment of the present utility model.

[0017] Reference numerals

[0018] 1. Flip arm; 11. First adjustment rail; 12. First adjustment hand wheel; 13. First adjustment slider; 14. Mounting plate; 15. First connecting block; 17. Clamping cylinder; 18. Longitudinal magnet; 19. First transverse magnet; 20. Limit plate; 21. Width ruler; 22. Protective cover; 2. Aircraft beam; 3. Flip motor; 4. Support arm; 41. Height adjustment rail; 42. Second adjustment rail; 43. Second adjustment slider; 44. Second transverse magnet; 45. Second connecting block; 46. Second width adjustment hand wheel; 5. Flip table; 51. Flip bracket; 6. Height adjustment slider. DETAILED DESCRIPTION

[0019] In order to enable those skilled in the art to better understand the technical solutions in the present invention, the following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0020] Embodiment 1

[0021] like Figure 1-4 As shown, an aircraft beam assembly flipping device includes a flipping platform 5, a flipping bracket 51 is provided at the upper end of the flipping platform 5, a flipping arm 1 is provided at one end of the flipping platform 5, and a support arm 4 is provided at the other end of the flipping platform 5. The flipping arm 1 is connected to the flipping motor 3 through the flipping bracket 51.

[0022] One end of the flip arm 1 is connected to the flip motor 3 through the flip bracket 51, and the other end of the flip arm 1 is provided with a first adjusting slide rail 11 and a first adjusting hand wheel 12. The first adjusting slide rail 11 is provided with a first adjusting slider 13. The upper end of the first adjusting slider 13 is provided with a mounting plate 14. The mounting plate 14 is provided with a clamping device and a magnet. The lower end of the first adjusting slider 13 is connected to the first adjusting hand wheel 12 through a first connecting block 15.

[0023] The first adjusting hand wheel 12 drives the first adjusting slider 13 provided on the first adjusting slide rail 11, and then drives the mounting plate 14 to move, so that the clamping device can be adjusted according to the size of the aircraft beam 2, achieving a universal design.

[0024] The clamping device includes two groups of clamping cylinders 17, which are arranged opposite to each other. The magnets include a longitudinal magnet 18 and a first transverse magnet 19. The lower end of the clamping cylinder 17 is fixedly connected to the mounting plate 14. A limit plate 20 is provided at the upper end of the clamping cylinder 17. Longitudinal magnets 18 are provided on both sides of the limit plate 20. A first transverse magnet 19 is provided at the lower end of the longitudinal magnet 18. An aircraft beam 2 is provided between the two groups of clamping cylinders 17, and the aircraft beam 2 is located at the upper end of the first transverse magnet 19.

[0025] The first adjusting slider 13 is further provided with a width ruler 21 , and the flip arm 1 is provided with a protective cover 22 . An opening is provided on the outer side of the protective cover 22 , and the width ruler 21 passes through the opening and is located outside the protective cover 22 .

[0026] A height adjustment rail 41 and a limit latch are provided at one end of the support arm 4, and a height adjustment slider 6 and a plurality of latch holes are provided at the turning table 5. The height adjustment rail 41 is connected to the height adjustment slider 6, and is limited by the limit latch and the latch hole. A second adjustment rail 42 is provided at the other end of the support arm 4, and a second adjustment slider 43 is provided at the second adjustment rail 42. A second transverse magnet 44 is provided at the upper end of the second adjustment slider 43, and a second connecting block 45 is provided at the lower end of the second adjustment slider 43. The second connecting block 45 is connected to the second width adjustment hand wheel 46, and an aircraft beam 2 is provided at the upper end of the second transverse magnet 44.

[0027] The height adjustment rail 41 cooperates with the height adjustment slider 6 to adjust the height of the support arm 4 to meet the needs of aircraft beams 2 of different sizes, thereby achieving a universal design.

[0028] Embodiment 2

[0029] The operation process of this utility model:

[0030] like Figure 5 As shown, the connecting plate and the crossbeam are sequentially placed in the flip arm 1, and the upper part is riveted to form the aircraft beam 2; wherein, the connecting plate is adsorbed and limited by the longitudinal magnet 18, and the crossbeam is adsorbed and limited by the first transverse magnet 19. After the riveting is completed, the two sets of clamping cylinders 17 are actuated to drive the limit plate 20 to clamp the aircraft beam 2, and then the flip motor 3 drives the aircraft beam 2 to flip, flip to the support arm 4, and rivet the lower part.

Claims

1. An aircraft beam assembly flipping device, characterized in that: The invention comprises a turning platform (5), wherein a turning bracket (51) is provided at the upper end of the turning platform (5), a turning arm (1) is provided at one end of the turning platform (5), and a supporting arm (4) is provided at the other end of the turning platform (5); the turning arm (1) is connected to a turning motor (3) via the turning bracket (51).

2. The aircraft beam assembly flipping device according to claim 1, characterized in that: One end of the flip arm (1) is connected to the flip motor (3) via the flip bracket (51); the other end of the flip arm (1) is provided with a first adjustment rail (11) and a first adjustment hand wheel (12); the first adjustment rail (11) is provided with a first adjustment slider (13); the upper end of the first adjustment slider (13) is provided with a mounting plate (14); the mounting plate (14) is provided with a clamping device and a magnet; the lower end of the first adjustment slider (13) is connected to the first adjustment hand wheel (12) via a first connecting block (15).

3. The aircraft beam assembly flipping device according to claim 2, characterized in that: The clamping device comprises two groups of clamping cylinders (17), the two groups of clamping cylinders (17) are arranged opposite to each other, the magnets comprise a longitudinal magnet (18) and a first transverse magnet (19), the lower end of the clamping cylinder (17) is fixedly connected to the mounting plate (14), the upper end of the clamping cylinder (17) is provided with a limit plate (20), the longitudinal magnets (18) are arranged on both sides of the limit plate (20), the lower end of the longitudinal magnet (18) is provided with a first transverse magnet (19), an aircraft beam (2) is arranged between the two groups of clamping cylinders (17), and the aircraft beam (2) is located at the upper end of the first transverse magnet (19).

4. The aircraft beam assembly flipping device according to claim 2, characterized in that: The first adjusting slider (13) is also provided with a width ruler (21), the flip arm (1) is provided with a protective cover (22), an opening is provided on the outside of the protective cover (22), and the width ruler (21) passes through the opening and is located outside the protective cover (22).

5. The aircraft beam assembly flipping device according to claim 1, characterized in that: A height adjustment slide rail (41) and a limit pin are provided at one end of the support arm (4); a height adjustment slider (6) and a plurality of pin holes are provided on the flip platform (5); the height adjustment slide rail (41) is connected to the height adjustment slider (6) and is limited by the limit pin and the pin hole; a second adjustment slide rail (42) is provided at the other end of the support arm (4); a second adjustment slider (43) is provided on the second adjustment slide rail (42); a second transverse magnet (44) is provided at the upper end of the second adjustment slider (43); a second connecting block (45) is provided at the lower end of the second adjustment slider (43); the second connecting block (45) is connected to a second width adjustment hand wheel (46); and the aircraft beam (2) is provided at the upper end of the second transverse magnet (44).

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