Automatic welding tool for aviation parts

Abstract

The utility model relates to an automatic welding tool for aviation parts, which comprises a bottom plate and a positioning and clamping mechanism, and is characterized in that the positioning and clamping mechanism comprises a mandrel fixing component fixed at the rear part of the upper surface of the bottom plate and a clamping component fixed at the front part of the upper surface of the bottom plate; the clamping assembly comprises a left fixing base, a right fixing base, a left clamping block, a right clamping block, a left driving structure connected between the left fixing base and the left clamping block and a right driving structure connected between the right fixing base and the right clamping block, and a part clamping space is formed between the opposite faces of the left clamping block and the right clamping block; the free end of the mandrel extends to the front end of the part clamping space, a cantilever is additionally arranged above the bottom plate, the free end of the cantilever is rotatably positioned over the rear portion of the part clamping space, and an axial positioning assembly is arranged at the free end of the cantilever. The tool solves the problem that the size of a welded part is difficult to guarantee, and the percent of pass and the machining efficiency of the part are remarkably improved.

Description

Technical Field

[0001] The utility model relates to the field of aviation component manufacturing, in particular to an automatic welding tool for aviation components. Background Art

[0002] At present, some aviation parts are tubular parts that need to be welded. When welding the seams of these parts, automatic argon arc welding is usually used, but there are the following problems: 1. After each welding, the parts are deformed to a large extent, and the parts need to be manually corrected again, resulting in low processing efficiency; 2. In the absence of welding tooling, it is easy to weld through and the parts are very easy to deform. The above situation makes it difficult to guarantee the size of the parts and the qualified rate is low. Utility Model Content

[0003] The utility model aims to provide an automatic welding tool for aviation parts with reasonable structure and reliable use, so as to solve the problem that the size of parts after welding is difficult to ensure and significantly improve the qualified rate and processing efficiency of parts.

[0004] The technical solution of the utility model is:

[0005] A kind of automatic welding tool for aviation parts, including a base plate and a positioning and clamping mechanism, and its technical points are: the positioning and clamping mechanism includes a core shaft fixing assembly fixed to the rear part of the upper surface of the base plate, and a clamping assembly fixed to the front part of the upper surface of the base plate, the clamping assembly includes a left fixed seat, a right fixed seat, a left clamping block, a right clamping block, a left driving structure connected between the left fixed seat and the left clamping block, and a right driving structure connected between the right fixed seat and the right clamping block, a part clamping space is formed between the opposite surfaces of the left clamping block and the right clamping block, a core shaft is clamped and fixed in the core shaft fixing assembly, and the free end of the core shaft extends to the front end of the part clamping space, and the center line of the part clamping space coincides with the center line of the core shaft, and a cantilever is further provided above the base plate, and the free end of the cantilever can be rotatably positioned just above the rear of the part clamping space, and the free end of the cantilever is provided with an axial positioning assembly corresponding to the part.

[0006] The above-mentioned automatic welding tooling for aviation parts, the left drive structure and the right drive structure are symmetrically arranged, and the left drive structure and the right drive structure respectively include an extension tube connected to the left fixed seat or the right fixed seat, a connecting seat hinged to the outer surface of the end of the extension tube, a handle hinged to the other end of the connecting seat, and a horizontal drive rod with one end connected to the left clamping block or the right clamping block after passing through the extension tube and the other end hinged to the handle. The handle is in a right angle shape, and its inflection point is hinged to the connecting seat, the end of the short arm on one side of the inflection point is hinged to the horizontal drive rod, and the long arm on the other side of the inflection point is a hand-held section.

[0007] The above-mentioned automatic welding tooling for aviation parts, the core shaft fixing assembly includes a base, a left pressure block and a right pressure block connected to the base, the upper surface of the base is provided with a reducing groove, the bottom surface of the reducing groove is provided with a semicircular arc groove, the left pressure block and the right pressure block are located in the reducing groove, the opposite surfaces of the left pressure block and the right pressure block are provided with an arc groove matching the semicircular arc groove, the arc grooves of the left pressure block and the right pressure block and the semicircular arc groove surround to form a clamping space corresponding to the core shaft.

[0008] The above-mentioned automatic welding tooling for aviation parts, one end of the cantilever is supported above the base plate by a vertical shaft, the axial positioning assembly includes a Z-shaped seat fixed to the upper surface of the cantilever, a longitudinal tightening bolt passing through the horizontal surface on the Z-shaped seat and threadedly connected to the cantilever, the center line of the longitudinal tightening bolt and the center line of the part clamping space are located in the same vertical plane, the longitudinal tightening bolt is provided with an anti-loosening spring, and the anti-loosening spring is clamped between the horizontal surface on the Z-shaped seat and the cantilever.

[0009] The above-mentioned automatic welding tooling for aviation parts has a stop column corresponding to the cantilever on one side of the vertical axis, a horizontal through hole is provided on the cantilever, a positioning screw is provided in the horizontal through hole, and the tip of the positioning screw passes through the horizontal through hole and is connected and fixed to the stop column.

[0010] The above-mentioned automatic welding tooling for aviation parts, the left fixing seat and the right fixing seat are symmetrically provided with horizontal guide holes, the left clamping block and the right clamping block are respectively provided with horizontal guide rods matching with the horizontal guide holes, and the top surfaces of the left fixing seat and the right fixing seat are provided with top screws corresponding to the horizontal guide rods.

[0011] In the above-mentioned automatic welding tool for aviation parts, the upper surface of the core shaft is provided with a groove extending along its length direction to avoid the welding position.

[0012] The beneficial effects of the utility model are:

[0013] During welding, the mandrel of the tool is used to support the inner cavity of the pipe to be welded, the left clamping block and the right clamping block are used to clamp the pipe to be welded to close the seam position, and then the axial positioning component is used to press down to prevent axial displacement during welding. When the welding is about to be completed, the axial positioning is released and the welding is complete. Due to the support of the mandrel, the radial compression of the left clamping block and the right clamping block, and the axial positioning of the axial positioning component, the deformation of the parts due to welding is prevented each time, making the processing of the parts convenient and easy, solving the problem of difficult to ensure the size of the parts after welding, and significantly improving the qualified rate and processing efficiency of the parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a structural schematic diagram of the utility model;

[0015] Figure 2 yes Figure 1 Middle AA section view;

[0016] Figure 3 yes Figure 1 Middle BB section.

[0017] In the figure: 1. bottom plate, 2. base, 3. left pressure block, 4. core shaft, 401. groove, 5. right pressure block, 6. stop column, 7. cantilever, 8. vertical shaft, 9. positioning screw, 10. right fixing seat, 11. connecting seat, 12. top screw, 13. horizontal guide rod, 14. right clamping block, 15. left clamping block, 16. horizontal driving rod, 17. left fixing seat, 18. extension tube, 19. handle, 1901. short arm, 20. longitudinal tightening bolt, 21. Z-shaped seat, 22. anti-loosening spring. DETAILED DESCRIPTION

[0018] The utility model is described in detail according to the accompanying drawings of the specification.

[0019] like Figure 1 to Figure 3 As shown, the automatic welding tool for aviation parts includes a base plate 1 and a positioning clamping mechanism.

[0020] The positioning and clamping mechanism includes a spindle fixing assembly fixed to the rear of the upper surface of the bottom plate 1 and a clamping assembly fixed to the front of the upper surface of the bottom plate 1. The clamping assembly includes a left fixed seat 17, a right fixed seat 10, a left clamping block 15, a right clamping block 14, a left driving structure connected between the left fixed seat 17 and the left clamping block 15, and a right driving structure connected between the right fixed seat 10 and the right clamping block 14. A part clamping space is formed between the opposite surfaces of the left clamping block 15 and the right clamping block 14. A spindle 4 is clamped and fixed in the spindle fixing assembly, and the free end of the spindle 4 extends to the front end of the part clamping space, and the center line of the part clamping space coincides with the center line of the spindle 4. A cantilever 7 is also provided above the bottom plate 1, and the free end of the cantilever 7 can be rotatably positioned just above the rear of the part clamping space, and the free end of the cantilever 7 is provided with an axial positioning assembly corresponding to the part.

[0021] In this embodiment, the left driving structure and the right driving structure are arranged symmetrically. The left driving structure and the right driving structure respectively include an extension tube 18 connected to the left fixing seat 17 or the right fixing seat 10, a connecting seat 11 hinged to the outer surface of the end of the extension tube 18, a handle 19 hinged to the other end of the connecting seat 11, and a horizontal driving rod 16 having one end connected to the left clamping block 15 or the right clamping block 14 after passing through the extension tube 18 and the other end hinged to the handle 19. The handle 19 is in a right angle shape, and its inflection point is hinged to the connecting seat 11, and the end of the short arm 1901 on one side of the inflection point is hinged to the horizontal driving rod 16, and the long arm on the other side of the inflection point is a hand-held section.

[0022] The mandrel fixing assembly includes a base 2, a left pressing block 3 and a right pressing block 5 connected to the base 2, the upper surface of the base 2 is provided with a reduction groove, the bottom surface of the reduction groove is provided with a semicircular arc groove, the left pressing block 3 and the right pressing block 5 are located in the reduction groove, the opposite surfaces of the left pressing block 3 and the right pressing block 5 are provided with an arc groove matched with the semicircular arc groove, and the arc grooves of the left pressing block 3 and the right pressing block 5 and the semicircular arc groove surround to form a clamping space corresponding to the mandrel 4. The upper surface of the mandrel 4 is provided with a groove 401 extending along its length direction to avoid the welding position.

[0023] One end of the cantilever 7 is supported on the bottom plate 1 by a vertical shaft 8. The axial positioning assembly includes a Z-shaped seat 21 fixed to the upper surface of the cantilever 7, a longitudinal jacking bolt 20 passing through the horizontal surface of the Z-shaped seat 21 and threadedly connected to the cantilever 7, the center line of the longitudinal jacking bolt 20 and the center line of the part clamping space are located in the same vertical plane, and a locking spring 22 is sleeved on the longitudinal jacking bolt 20, and the locking spring 22 is clamped between the horizontal surface of the Z-shaped seat 21 and the cantilever 7. A stopper column 6 corresponding to the cantilever 7 is provided on one side of the vertical shaft 8, and a horizontal through hole is provided on the cantilever 7, and a positioning screw 9 is provided in the horizontal through hole, and the tip of the positioning screw 9 passes through the horizontal through hole and is connected and fixed to the stopper column 6.

[0024] The left fixing seat 17 and the right fixing seat 10 are symmetrically provided with horizontal guide holes, respectively. The left clamping block 15 and the right clamping block 14 are respectively provided with horizontal guide rods 13 that cooperate with the horizontal guide holes. The top surfaces of the left fixing seat 17 and the right fixing seat 10 are provided with top screws 12 corresponding to the horizontal guide rods 13.

[0025] Working principle:

[0026] During operation, the pipe to be welded is sleeved on the core shaft 4 with the slit facing upwards, and then the handle 19 is moved. The short arm ends of the two handles 19 push the two horizontal drive rods 16 towards each other, thereby driving the left clamping block 15 and the right clamping block 14 to clamp the parts towards each other, so that the slit of the parts is closed and exposed to the outside, and then the top screw 12 is used to tighten the horizontal guide rod 13 to limit the position of the left and right clamping blocks, and then the longitudinal tightening bolt 20 of the axial positioning assembly is used to press the parts to avoid axial displacement or rotational displacement.

[0027] The above is a detailed description of the embodiments of the utility model, but the above contents are only preferred embodiments of the utility model and cannot be considered to limit the scope of implementation of the utility model. All equivalent changes and improvements made within the scope of the invention of the utility model should still fall within the scope of this patent.

Claims

1. An automatic welding tool for aviation parts, comprising a base plate and a positioning clamping mechanism, characterized in that: The positioning and clamping mechanism includes a spindle fixing assembly fixed to the rear part of the upper surface of the base plate, and a clamping assembly fixed to the front part of the upper surface of the base plate. The clamping assembly includes a left fixed seat, a right fixed seat, a left clamping block, a right clamping block, a left driving structure connected between the left fixed seat and the left clamping block, and a right driving structure connected between the right fixed seat and the right clamping block. A part clamping space is formed between the opposite surfaces of the left clamping block and the right clamping block. A spindle is clamped and fixed in the spindle fixing assembly, and the free end of the spindle extends to the front end of the part clamping space. The center line of the part clamping space coincides with the center line of the spindle. A cantilever is further provided above the base plate. The free end of the cantilever can be rotatably positioned just above the rear of the part clamping space, and the free end of the cantilever is provided with an axial positioning assembly corresponding to the part.

2. The automatic welding tool for aviation parts according to claim 1 is characterized in that: The left driving structure and the right driving structure are arranged symmetrically, and the left driving structure and the right driving structure respectively include an extension tube connected to the left fixing seat or the right fixing seat, a connecting seat hinged to the outer surface of the end of the extension tube, a handle hinged to the other end of the connecting seat, and a horizontal driving rod with one end connected to the left clamping block or the right clamping block after passing through the extension tube and the other end hinged to the handle. The handle is right-angled and is hinged to the connecting seat at its inflection point. The end of the short arm on one side of the inflection point is hinged to the horizontal driving rod, and the long arm on the other side of the inflection point is a hand-held section.

3. The automatic welding tool for aviation parts according to claim 1 is characterized in that: The core shaft fixing assembly includes a base, a left pressure block and a right pressure block connected to the base, the upper surface of the base is provided with a reducing groove, the bottom surface of the reducing groove is provided with a semicircular arc groove, the left pressure block and the right pressure block are located in the reducing groove, the opposite surfaces of the left pressure block and the right pressure block are provided with an arc groove matching the semicircular arc groove, the arc grooves of the left pressure block and the right pressure block are surrounded by the semicircular arc groove to form a clamping space corresponding to the core shaft.

4. The automatic welding tool for aviation parts according to claim 1 is characterized in that: One end of the cantilever is supported above the base plate by a vertical shaft, and the axial positioning assembly includes a Z-shaped seat fixed to the upper surface of the cantilever, a longitudinal tightening bolt passing through the horizontal surface of the Z-shaped seat and threadedly connected to the cantilever, the center line of the longitudinal tightening bolt and the center line of the part clamping space are located in the same vertical plane, and an anti-loosening spring is sleeved on the longitudinal tightening bolt, and the anti-loosening spring is clamped between the horizontal surface of the Z-shaped seat and the cantilever.

5. The automatic welding tool for aviation parts according to claim 4 is characterized in that: A stop column corresponding to the cantilever is provided on one side of the vertical axis, a horizontal through hole is provided on the cantilever, a positioning screw is provided in the horizontal through hole, and the tip of the positioning screw passes through the horizontal through hole and is connected and fixed to the stop column.

6. The automatic welding tool for aviation parts according to claim 1, characterized in that: The left fixing seat and the right fixing seat are symmetrically provided with horizontal guide holes respectively, the left clamping block and the right clamping block are respectively provided with horizontal guide rods matched with the horizontal guide holes, and the top surfaces of the left fixing seat and the right fixing seat are provided with top screws corresponding to the horizontal guide rods.

7. The automatic welding tool for aviation parts according to claim 1 is characterized in that: The upper surface of the core shaft is provided with a groove extending along the length direction thereof.

Images