Aviation structural part welding positioning device

Abstract

The utility model relates to a welding and positioning device for an aviation structural part. The welding and positioning device mainly comprises a high-strength metal base, a bearing seat, a rotating shaft, a worm gear, a worm, a first motor, a rotary table, a workbench, a connecting rod, a first gear, a second gear, a second motor, a limiting disc, a limiting column and the like. According to the device, rotation of the rotary table is achieved through transmission of the worm, the worm gear and the rotary shaft, rotation and inclination adjustment of the workbench are achieved through cooperation of the first gear, the second gear and the second motor, and therefore accurate control over welding positioning is achieved. In addition, due to the design of the limiting disc and the limiting column, the welding part can be accurately positioned in the welding process. The device is mainly used for welding positioning of aviation structural parts and has the advantages of being stable in structure, accurate in positioning, convenient to operate and the like.

Description

Technical Field

[0001] The present application relates to the field of aviation structural parts processing, and specifically to a welding positioning device for aviation structural parts. Background Art

[0002] Traditional methods for welding aerospace components typically rely on manual positioning or simple mechanical devices to adjust the weld position. However, these traditional methods have drawbacks, such as low positioning accuracy, poor adjustment efficiency, and complex operation. These issues not only affect weld quality but also increase production costs and workload. Therefore, improving the accuracy and efficiency of welding positioning for aerospace components has become a pressing issue. Utility Model Content

[0003] The purpose of this application is to provide an aviation structural part welding positioning device, which is used to solve the welding positioning problem between aviation structural parts. To achieve the above purpose, this application provides the following technical solutions: an aviation structural part welding positioning device, comprising:

[0004] A base, wherein a bearing seat is provided on the base, a rotating shaft is provided in the bearing seat, the rotating shaft is vertically arranged and one end of the rotating shaft is connected to the worm gear;

[0005] a worm, one end of which is connected to the first motor, and the worm is meshed with the worm wheel;

[0006] a turntable connected to the other end of the rotating shaft, the turntable being U-shaped, the first motor driving the worm to rotate, thereby driving the worm wheel to rotate, so that the turntable and the rotating shaft rotate coaxially;

[0007] A workbench, the workbench is arranged on the turntable, and the workbench is U-shaped;

[0008] A connecting rod, the connecting rod passing through two side surfaces of the turntable and fixedly connected to two side walls of the workbench, the connecting rod being rotatable about an axis relative to the two side surfaces;

[0009] a first gear, the first gear being disposed on the connecting rod;

[0010] The second gear, one end of the second gear is connected to the side surface, and the other end is connected to the second motor. The second gear is engaged with the first gear. The second motor can drive the second gear to rotate, thereby driving the first gear and the connecting rod to rotate, so as to realize the coaxial rotation of the workbench and the connecting rod.

[0011] Preferably, the technical solution further includes a limiting plate, which is arranged on the workbench and has a circular groove.

[0012] Preferably, the limiting disk is in a truncated cone shape, that is, it is composed of a large disk and a small disk of two different diameters, and the axial cross-section of the limiting disk is T-shaped.

[0013] Preferably, the side of the large disc is provided with a scale.

[0014] Preferably, the present technical solution further comprises a limiting post, wherein the limiting post is arranged on the limiting plate and is coaxially arranged with the limiting plate.

[0015] Preferably, the limiting column is detachably connected to the limiting disk, a through hole is provided on the side of the small disk, a through hole is provided on the limiting column, a spring piece is placed in the through hole, the spring piece has a protrusion, and the protrusion passes through the through hole and is adapted to the through hole.

[0016] Preferably, the present technical solution further comprises a support frame, which is evenly arranged along the circumference of the limiting column, wherein a first end of the support frame is connected to the limiting column, and a second end of the support frame is in contact with the inner wall of the structural member.

[0017] Preferably, in this technical solution, the second end is lower in height than the first end.

[0018] Compared with the prior art, the present invention has the following advantages:

[0019] The present invention uses a design in which the worm is meshed with the worm wheel, and the first motor drives the worm wheel to rotate, thereby realizing the coaxial rotation of the turntable and the rotating shaft. This design effectively improves the rotation accuracy of the turntable, allowing the turntable and the workbench to rotate horizontally during the welding process. Secondly, the design in which the first gear is meshed with the second gear, and the workbench and the connecting rod rotate coaxially, allows the second motor to drive the gear to drive the connecting rod and the workbench to rotate along the axial direction of the connecting rod. The rotation in two directions improves the positioning requirements during the welding of aviation structural parts while also meeting the requirements of multi-angle positioning, thereby improving work efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the use status of an aviation structural component welding positioning device proposed in this application;

[0021] Figure 2 This is a schematic structural diagram of a welding positioning device for aviation structural parts proposed in this application;

[0022] Figure 3 This is a partial structural diagram of a welding positioning device for aviation structural parts proposed in this application;

[0023] Figure 4 Schematic diagram of the limiting column and support frame structure;

[0024] Figure 5Schematic diagram of the shrapnel structure;

[0025] Figure 6 This application applies to aviation structural parts to be welded and fixed;

[0026] In the figure: 1. base; 2. bearing seat; 3. rotating shaft; 4. worm gear; 5. worm; 6. first motor; 7. turntable; 8. workbench; 9. connecting rod; 10. side; 11. side wall; 12. first gear; 13. second gear; 14. second motor; 15. limit plate; 16. circular groove; 17. large disc; 18. small disc; 19. limit column; 20. through hole; 21. through hole; 22. spring piece; 23. protrusion; 24. support frame; 25. first end; 26. second end. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0028] It should be noted that, in the description of this application, the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they cannot be understood as a limitation on this application.

[0029] Furthermore, it should be understood that for ease of description, the sizes of the various components shown in the drawings are not drawn according to actual proportions. For example, the thickness or width of certain layers may be exaggerated relative to other layers.

[0030] It should be noted that like numbers and letters represent similar items in the following figures, so once an item is defined or described in one figure, it will not need to be further discussed and described in detail in the description of the subsequent figures.

[0031] In order to solve the technical problems in the background technology, such as Figure 1-6 As shown, the present application provides a technical solution: a welding positioning device for aviation structural parts, which has the following characteristics:

[0032] The base 1 of the present invention is made of high-strength metal material, offering excellent stability and impact resistance. A bearing seat 2 is provided on the base 1. The bearing seat 2 is fixed to the base 1 and supports the rotating shaft 3. The rotating shaft 3 is vertically arranged, with one end fixedly connected to the worm gear 4 and the other end fixedly connected to the turntable 7. The rotating shaft 3 is made of high-strength stainless steel, offering high wear resistance and bending resistance. One end of the worm 5 is connected to the first motor 6, and the other end meshes with the worm gear 4. The worm 5 is made of high-quality alloy steel or stainless steel, offering high strength and wear resistance. The worm gear 4 is connected to the rotating shaft 3 to transmit power. The first motor 6 is connected to one end of the worm 5 to drive the worm 5 to rotate. The first motor 6 is a reduction motor with excellent speed regulation performance. The turntable 7 is connected to the other end of the rotating shaft 3 and has a U-shaped structure. The turntable 7 is made of high-strength metal or hard plastic, offering excellent support. The turntable 7 is fixedly connected to the rotating shaft 3, so that the turntable 7 rotates coaxially with the rotating shaft 3. The workbench 8 is arranged on the turntable 7 and has a U-shaped structure. Specifically, the workbench 8 is connected to the turntable 7 in an inverted U shape. The workbench 8 is flat, which is convenient for welding. The connecting rod 9 passes through the two side surfaces 10 of the turntable 7 and is fixedly connected to the two side walls 11 of the workbench 8. In other words, the connecting rod 9 can rotate within the two side surfaces 10, so the turntable 7 does not move accordingly; instead, the workbench 8 rotates with the rotation of the connecting rod 9. The first gear 12 is arranged on the connecting rod 9, and the two are fixedly connected to transmit power. When the first gear 12 rotates, it drives the connecting rod 9 to rotate. One end of the second gear 13 is connected to the side surface 10 of the turntable 7, and the other end is connected to the second motor 14. The second gear 13 can rotate within the side surface 10. The second gear 13 meshes with the first gear 12 and is used to transmit the power of the second motor 14 to the first gear 12. The second motor 14 uses a DC reduction motor with good speed regulation performance.

[0033] During use, place the aviation structure to be welded on the workbench 8, and adjust the position of the workbench 8 so that it is fixed in a position that is convenient for workers to weld. Start the first motor 6 to drive the worm 5 to rotate, thereby driving the worm wheel 4 to rotate, and realizing the coaxial rotation of the turntable 7 and the rotating shaft 3. Rotate the workbench 8 around the rotating shaft 3 and adjust it to a suitable position. Start the second motor 14 and drive the second gear 13 to rotate, thereby driving the first gear 12 and the connecting rod 9 to rotate, and realizing the coaxial rotation of the workbench 8 and the connecting rod 9. Adjust the workbench 8 to a suitable inclination. During the welding process, hold the welding gun at the starting position, and achieve precise control of the welding positioning device by adjusting the speed of the first motor 6 and / or the second motor 14. After welding is completed, turn off the first motor 6 and the second motor 14, and remove the aviation structure from the workbench 8.

[0034] It should be noted that, as shown in the figure, the limiting plate 15 is provided on the workbench 8 and has a circular groove 16. When welding a structural member with an arc shape on the outside, the structural member can be clamped into the circular groove 16 for positioning, making it convenient to weld its upper part.

[0035] Furthermore, the main structure of the limiting disk 15 is in the shape of a truncated cone, consisting of two large disks 17 and a small disk 18 of different diameters, forming a T-shaped structure in the axial section, specifically as follows: the axial section of the limiting disk 15 is T-shaped, with the large disk 17 at the upper end and the small disk 18 at the lower end. The large disk 17 and the small disk 18 have different diameters, forming a truncated cone shape. The one-piece molding design between the large disk 17 and the small disk 18 ensures the overall stability and strength of the limiting disk 15. The large disk 17 is used to contact with mechanical parts, increasing the contact area. The small disk 18 is used to support the limiting disk 15 and maintain its stability.

[0036] It should be noted that the scale is set on the side 10 of the large disk 17 for positioning the weld. The scale spacing is determined according to actual needs to ensure the positioning accuracy of the weld. By observing the scale on the side 10 of the large disk 17, the precise position of the weld can be determined.

[0037] Furthermore, the limiting post 19 is a cylindrical member positioned centrally within the limiting plate 15 and coaxially with the plate. The height of the limiting post 19 can be adjusted as needed to ensure accurate positioning of the aviation structural component during welding. A hole coaxial with the limiting post 19 is provided in the center of the limiting plate 15 to facilitate connection between the limiting post 19 and the plate 15.

[0038] It should be noted that the limiting post 19 is connected to the limiting disk 15 by a detachable connection. Specifically, a through hole 21 is provided at the lower end of the limiting post 19, which cooperates with the through hole 20 on the side 10 of the small disk 18. A spring piece 22 is placed in the through hole 21. The spring piece 22 has a protrusion 23. The protrusion 23 passes through the through hole 21 and adapts to the through hole 20 of the small disk 18, thereby realizing the detachable connection between the limiting post 19 and the limiting disk 15. The through hole 20 is arranged along the radial direction of the small disk 18, and the through hole 21 is arranged along the radial direction of the limiting post 19. The material of the spring piece 22 is selected from stainless steel with good elasticity and corrosion resistance to ensure its stability and reliability during use. During assembly, the spring piece 22 is first placed in the through hole 21 of the limiting post 19, and the protrusion 23 passes through the through hole 21. Press the protrusion 23 and insert the limiting column 19 into the hole at the center of the limiting plate 15. Due to the elastic force of the spring 22, the protrusion 23 will extend out of the hole 21 again and adjust its position so that it passes through the through hole 20 of the small disc 18, thereby achieving fixation.

[0039] It should be noted that when encountering a cylindrical component, support frames 24 are evenly arranged around the circumference of the limiting column 19. The first end 25 of the support frame 24 is designed as a connection structure, which is tightly connected to the limiting column 19. The connection method can be welding, bolting, or other strong connection methods to ensure the stability between the support frame 24 and the limiting column 19. The second end 26 of the support frame 24 is designed to be a structure that contacts the inner wall of the structural component. This contact structure can be a flat contact or a curved surface contact, and is contoured according to the shape of the inner wall of the structural component to ensure effective contact between the support frame 24 and the inner wall of the structural component.

[0040] It should be noted that the second end 26 is lower than the first end 25. That is, the free end of the support frame 24 is lower than the fixed end. The design of the support frame 24 with one side high and the other side low is conducive to the cylindrical structure being installed on the limit column 19. Figure 6 As shown, a fan-shaped component needs to be welded to a cylindrical tube.

[0041] Although the embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A welding positioning device for aviation structural parts, characterized in that: include: A base (1), a bearing seat (2) is provided on the base (1), a rotating shaft (3) is provided in the bearing seat (2), and the rotating shaft (3) is vertically arranged and one end of the rotating shaft is connected to a worm gear (4); a worm (5), one end of the worm (5) being connected to a first motor (6), and the worm (5) being meshed with the worm wheel (4); A turntable (7), the turntable (7) is connected to the other end of the rotating shaft (3), the turntable (7) is U-shaped, the first motor (6) drives the worm (5) to rotate, thereby driving the worm wheel (4) to rotate, so that the turntable (7) and the rotating shaft (3) can rotate coaxially; A workbench (8), the workbench (8) is arranged on the turntable (7), and the workbench (8) is U-shaped; a connecting rod (9), the connecting rod (9) passing through two side surfaces (10) of the turntable (7) and fixedly connected to two side walls (11) of the workbench (8), the connecting rod (9) being rotatable about an axis relative to the two side surfaces (10); a first gear (12), the first gear (12) being arranged on the connecting rod (9); A second gear (13), one end of the second gear (13) is connected to the side surface (10), and the other end is connected to a second motor (14), the second gear (13) is meshed with the first gear (12), and the second motor (14) can drive the second gear (13) to rotate, thereby driving the first gear (12) and the connecting rod (9) to rotate, so as to realize the coaxial rotation of the workbench (8) and the connecting rod (9).

2. The welding positioning device for aviation structural parts according to claim 1, characterized in that: It also includes a limiting plate (15), which is arranged on the workbench (8) and has a circular groove (16).

3. The welding positioning device for aviation structural parts according to claim 2, characterized in that: The limiting disk (15) is in a truncated cone shape, namely, it is composed of a large disk (17) and a small disk (18) with two different diameters. The axial cross section of the limiting disk (15) is T-shaped.

4. The welding positioning device for aviation structural parts according to claim 3, characterized in that: The side surface (10) of the large disc (17) is provided with scales.

5. The welding positioning device for aviation structural parts according to claim 4, characterized in that: It also includes a limiting column (19), which is arranged on the limiting plate (15) and is coaxially arranged with the limiting plate (15).

6. The welding positioning device for aviation structural parts according to claim 5, characterized in that: The limiting column (19) is detachably connected to the limiting disk (15); a through hole (20) is provided on the side surface (10) of the small disk (18); a through hole (21) is provided on the limiting column (19); a spring piece (22) is placed in the through hole (21); the spring piece (22) has a protrusion (23); the protrusion (23) passes through the through hole (21) and is adapted to the through hole (20).

7. The welding positioning device for aviation structural parts according to claim 6, characterized in that: It also includes a support frame (24), which is evenly arranged along the circumference of the limiting column (19), and a first end (25) of the support frame (24) is connected to the limiting column (19), and a second end (26) is in contact with the inner wall of the structural member.

8. The welding positioning device for aviation structural parts according to claim 7, characterized in that: The second end (26) is lower in height than the first end (25).

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