Automatic aviation conduit welding device and method

Abstract

The invention belongs to the technical field of welding, particularly relates to an automatic aviation conduit welding device and method, and provides the following scheme that the automatic aviation conduit welding device comprises a welding table, one side of the top of the welding table is connected with a connecting seat through bolts, the connecting seat is annular, and a conduit welding mechanism is arranged between the inner wall and the top of the connecting seat; one side of the top of the welding table is connected with a supporting column through a bolt, the supporting column is located in the connecting base, a butt joint mechanism is arranged on one side of the top of the welding table, a supporting plate is arranged on one side of the butt joint mechanism, and the other end of the supporting plate is connected with a supporting sleeve through a bolt; threaded holes are formed in the two sides of the outer wall of the circumference of the supporting sleeve in a penetrating mode, and the inner walls of the two threaded holes are in threaded connection with fastening bolts. Two guide pipes are in vertical butt joint, so that the situation that the stability of the guide pipes is poor due to uneven stress of the guide pipes, and the welding effect of the aviation guide pipes is affected can be effectively avoided.

Description

Technical Field

[0001] This invention relates to the field of welding, and more particularly to an automatic welding device and method for aviation conduits. Background Technology

[0002] Aluminum alloy conduits are an important component of fuel system pipelines. Fuel flows through conduits to various parts of the system. Because the pipeline design needs to adapt to the system structure and meet design principles, the design of conduits is quite complex. In addition to using pipe bending machines and flaring machines to complete the manufacturing of some pipelines, some conduits need to be welded, such as connector joints, tee joints, etc.

[0003] A search revealed Chinese patent application CN118905520A, which discloses an automatic welding machine for aviation ducts. This machine improves the manufacturing efficiency and process quality of aviation ducts and frees up labor. It includes a workbench with a frame. A vertical, open-type track pressure plate is mounted on the frame. A track for mounting track gears is located on the outer periphery of the opening at the top of the track pressure plate, and the track gears are meshed and connected to the track, together forming a track-type geared disc. A planetary gear is rotatably mounted on the lower part of the track pressure plate and on each side of the track gears, and both planetary gears are meshed and connected to the external teeth of the track gears. The two planetary gears are driven to rotate by a servo motor. The internal teeth of the track gears are connected to a mounting plate, on which a welding torch is mounted. A clamping mechanism for holding and fixing the duct to be welded is provided on each side of the frame.

[0004] When welding aviation ducts, existing equipment typically places two ducts horizontally and welds the joint between them using a welding mechanism. However, during the welding process, although the ducts are fixed in place, one end of the duct will shift upwards under the influence of gravity due to its horizontal placement, causing deviation during welding. Summary of the Invention

[0005] To achieve the above objectives, the present invention adopts the following technical solution: An automatic welding device for aviation ducts includes a welding table. A connecting seat is bolted to one side of the top of the welding table. The connecting seat is annular. A duct welding mechanism is provided between the inner wall and the top of the connecting seat. A support column is bolted to one side of the top of the welding table, and the support column is located inside the connecting seat. A docking mechanism is provided on one side of the top of the welding table, and a support plate is provided on one side of the docking mechanism. A support sleeve is bolted to the other end of the support plate. Threaded holes are provided on both sides of the outer circumference of the support sleeve. Fastening bolts are threaded to the inner walls of the two threaded holes. The duct welding mechanism includes a rotating component, an annular sliding plate, a support pad, a hydraulic cylinder, and a welding torch. The annular sliding plate is slidably connected to the inner wall of the connecting seat. The bottom of the support pad is bolted to the top of the annular sliding plate. One side of the top of the support pad is bolted to the hydraulic cylinder. A pad is bolted to the top of the hydraulic cylinder, and the top of the pad is fixedly connected to the welding torch.

[0006] Preferably, the rotating assembly consists of a welding motor, a rotating shaft, a gear, and a gear ring. The bottom of the rotating shaft is rotatably connected to the welding table via a bearing. The welding motor is fixed to one side of the bottom of the welding table by bolts. One end of the welding motor is fixedly connected to the rotating shaft. The gear is fixedly sleeved on the outer circumference of the rotating shaft. An annular groove is welded to the inner wall of the connecting seat. The gear ring is slidably connected inside the annular groove and fixed to the outer circumference of the annular slide plate. A meshing port is provided through one side of the annular groove, and the gear and the gear ring mesh inside the meshing port.

[0007] Preferably, the docking mechanism includes two adjusting seats, a screw, a support seat, and a docking motor. One of the adjusting seats is bolted to the welding table, and the top of the other adjusting seat is fixedly connected to the docking motor. The two ends of the screw are rotatably connected to the two adjusting seats through bearings. One end of the docking motor is fixedly connected to the screw. The top of the support seat has a threaded opening that is threaded to the screw. One side of the support seat is bolted to the support plate.

[0008] Preferably, two positioning rods are bolted between the two sides of the two adjustment seats, and positioning holes are provided through the top of the support seat on both sides, with the two positioning holes slidably connected to the two positioning rods.

[0009] Preferably, the support column has a cavity inside, and a reinforcing mechanism is provided between the cavity and the support column, and the reinforcing mechanism and the docking mechanism cooperate with each other.

[0010] Preferably, the reinforcement mechanism includes a push plate, two swing plates, two push rods, two top rods, a top plate, and two reinforcement plates. The top of the push plate has a through-hole that slides and is slidably connected to a support column. Push plate springs are welded to the support column on both sides of the bottom of the push plate. Connection ports are through-holes between the cavity and the support column on both sides. These connection ports are rotatably connected to the swing plates via bearings. The two ends of the push rods are hinged to the bottom of the push plate and one side of the top of the swing plate, respectively. The two ends of the top rods are hinged to the other side of the top of the swing plate and the top plate, respectively. The top plate is slidably connected inside the cavity. Pull-out openings are through-holes on both sides of the cavity's inner wall, and these openings are slidably connected to the reinforcement plates. Top shafts are hinged to the two reinforcement plates on both sides of the top of the top plate.

[0011] Preferably, the reinforcing plate has multiple anti-slip grooves on one side, and the reinforcing plate is made of an elastic and wear-resistant material.

[0012] Preferably, guide grooves are provided on both sides of the inner wall of the cavity, and guide blocks are slidably connected to the inner walls of the two guide grooves, and the two guide blocks are fixedly connected to the top plate.

[0013] An automatic welding method for aviation ducts, comprising the following steps: S1: When welding aviation ducts, one duct is sleeved on the outer wall of the support column, and the other duct is fixed inside the support sleeve; S2: After the two conduits are placed, start the docking mechanism. The docking mechanism will drive the conduits fixed in the support sleeve to move downward, thereby docking the two conduits. S3: After the two conduits are connected, the conduit welding mechanism is activated. The welding torch is rotated by the rotating component, so that the welding torch rotates around the two conduits while welding the connection between the two conduits. S4: When the two conduits are connected by the docking mechanism, the conduit on the support column will be subjected to pressure from the upper conduit. At this time, the conduit on the support column will push the push plate downward under the pressure. When the push plate moves downward, it will drive the push rod to move downward synchronously. When the push rod moves downward, it will push one end of the swing plate downward, while the other end of the swing plate will swing upward. When the other end of the swing plate swings upward, it will push the top plate upward through the top rod. Since the two top shafts are distributed in a T-shape, the two top shafts will push the reinforcing plate to one side of the inner wall of the conduit under the pressure, thereby fixing the reinforcing plate on the inner wall of the conduit for reinforcement. S5: After welding is completed, tighten the fastening bolt and remove the welded conduit from the device.

[0014] The beneficial effects of this invention are as follows: 1. This invention, through its docking mechanism, support column, support sleeve, and fastening bolt, allows for the welding of aviation ducts. One duct is fitted onto the outer wall of the support column, while the other is fixed inside the support sleeve. After both ducts are in place, the docking mechanism is activated, causing the duct fixed inside the support sleeve to move downwards, thus docking the two ducts. Once docking is complete, the duct welding mechanism is activated, using a rotating component to rotate the welding torch. This allows the welding torch to rotate around the two ducts while simultaneously welding the docking point. Vertical docking effectively avoids uneven stress on the ducts, which could lead to poor stability and negatively impact the welding effect. Compared to lateral docking, in this application, the vertical docking of the two ducts is caused by their own weight, resulting in a downward force and a smaller stress area. Therefore, the ducts do not deflect during docking, effectively improving the welding effect. 2. This invention, through its docking and reinforcing mechanisms, allows for the docking of two conduits. During docking, the conduit on the support column experiences pressure from the upper conduit. This pressure causes the push plate to move downwards, simultaneously moving the push rod downwards. The push rod, in turn, causes one end of the swing plate to deflect downwards, while the other end deflects upwards. This upward deflection of the swing plate then pushes the top plate upwards via a top rod. Since the two top shafts are arranged in a V-shape, the pressure causes the reinforcing plate to move towards one side of the conduit's inner wall, thus fixing the reinforcing plate to the inner wall for reinforcement. This improves the docking effect and, consequently, the welding effect. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of an automatic welding device for aviation conduits proposed in this invention; Figure 2 This is a schematic diagram of the main structure of an automatic welding device for aviation conduits proposed in this invention; Figure 3 This is a cross-sectional view of the duct welding mechanism of an automatic duct welding device for aviation ducts proposed in this invention; Figure 4 This is a schematic diagram of the duct welding mechanism of an automatic welding device for aviation ducts proposed in this invention; Figure 5 This is a schematic diagram of the duct docking mechanism of an automatic welding device for aviation ducts proposed in this invention; Figure 6 This is a schematic diagram of the reinforcement mechanism structure of an automatic welding device for aviation ducts proposed in this invention; Figure 7 This is a partial structural schematic diagram of an automatic welding device for aviation conduits proposed in this invention.

[0016] In the attached diagram: 1. Welding table; 2. Connecting seat; 3. Conduit welding mechanism; 4. Support column; 5. Support sleeve; 6. Fastening bolt; 7. Docking mechanism; 8. Support plate; 9. Annular groove; 10. Annular sliding plate; 11. Support pad; 12. Welding motor; 13. Rotating shaft; 14. Gear; 15. Hydraulic cylinder; 16. Pad plate; 17. Welding torch; 18. Gear ring; 19. Adjusting seat; 20. Screw; 21. Positioning rod; 22. Support seat; 23. Docking motor; 24. Reinforcing mechanism; 25. Cavity; 26. Connecting port; 27. Pull-out port; 28. Push plate; 29. ​​Push plate spring; 30. Top plate; 31. Swing plate; 32. Top rod; 33. Push rod; 34. Guide block; 35. Top shaft; 36. Reinforcing plate. Detailed Implementation

[0017] Example 1, referring to Figures 1-5 An automatic welding device for aviation ducts includes a welding table 1. A connecting seat 2, which is annular, is bolted to one side of the top of the welding table 1. A duct welding mechanism 3 is disposed between the inner wall and the top of the connecting seat 2. A support column 4, located inside the connecting seat 2, is bolted to one side of the top of the welding table 1. A docking mechanism 7 is disposed on one side of the docking mechanism 7, and a support plate 8 is disposed on one side of the docking mechanism 7. A support sleeve 5 is bolted to the other end of the support plate 8. Threaded holes are drilled through both sides of the outer circumference of the support sleeve 5, and fasteners are threaded into the inner walls of the two threaded holes. The welding mechanism 3 for the conduit includes a rotating assembly, an annular slide plate 10, a support pad 11, a hydraulic cylinder 15, and a welding torch 17. The annular slide plate 10 is slidably connected to the inner wall of the connecting seat 2. The bottom of the support pad 11 is bolted to the top of the annular slide plate 10. One side of the top of the support pad 11 is bolted to the hydraulic cylinder 15. The top of the hydraulic cylinder 15 is bolted to a pad 16, and the top of the pad 16 is fixedly connected to the welding torch 17. By vertically connecting the two conduits, the stability of the conduits due to uneven force on the conduits can be effectively avoided, thus preventing the welding effect of the aviation conduits from being affected.

[0018] Based on the above, the rotating assembly consists of a welding motor 12, a rotating shaft 13, a gear 14, and a gear ring 18. The bottom of the rotating shaft 13 is rotatably connected to the welding table 1 via a bearing. The welding motor 12 is fixed to one side of the bottom of the welding table 1 by bolts. One end of the welding motor 12 is fixedly connected to the rotating shaft 13. The gear 14 is fixedly sleeved on the outer circumference of the rotating shaft 13. An annular groove 9 is welded to the inner wall of the connecting seat 2. The gear ring 18 is slidably connected inside the annular groove 9. The gear ring 18 is fixed to the outer circumference of the annular slide plate 10. A meshing port is opened through one side of the annular groove 9. The gear 14 and the gear ring 18 mesh inside the meshing port.

[0019] Based on the above, the docking mechanism 7 includes two adjusting seats 19, a screw 20, a support seat 22, and a docking motor 23. One of the adjusting seats 19 is bolted to the welding table 1, and the top of the other adjusting seat 19 is fixedly connected to the docking motor 23. The two ends of the screw 20 are rotatably connected to the two adjusting seats 19 through bearings. One end of the docking motor 23 is fixedly connected to the screw 20. The top of the support seat 22 has a threaded opening, which is threaded to the screw 20. One side of the support seat 22 is bolted to the support plate 8.

[0020] Based on the above, two positioning rods 21 are bolted between the two sides of the two adjustment seats 19, and positioning holes are provided through the top of the support seat 22 on both sides, and the two positioning holes are slidably connected to the two positioning rods 21.

[0021] Example 2, refer to Figures 1-7 An automatic welding device for aviation ducts, compared with Embodiment 1, has a cavity 25 inside the support column 4, and a reinforcing mechanism 24 is provided between the cavity 25 and the support column 4, and the reinforcing mechanism 24 and the docking mechanism 7 cooperate with each other.

[0022] Based on the above, the reinforcement mechanism 24 includes a push plate 28, two swing plates 31, two push rods 33, two top rods 32, a top plate 30, and two reinforcement plates 36. The top of the push plate 28 has a through-hole, which is slidably connected to the support column 4. Push plate springs 29 are welded between the two sides of the bottom of the push plate 28 and the support column 4. Connection ports 26 are through-holes between the two sides of the cavity 25 and the support column 4. The connection ports 26 are rotatably connected to the swing plates 31 via bearings. The two ends of the movable plate 31 and the push rod 33 are respectively connected to the bottom of the push plate 28 and one side of the top of the swing plate 31 by hinges. The two ends of the top rod 32 are respectively connected to the other side of the top of the swing plate 31 and the top plate 30 by hinges. The top plate 30 is slidably connected inside the cavity 25. Pull-out openings 27 are provided through both sides of the inner wall of the cavity 25. The pull-out openings 27 are slidably connected to the reinforcing plate 36. The top two sides of the top of the top plate 30 are connected to the two reinforcing plates 36 by hinges. Top shafts 35 are connected to the two reinforcing plates 36 by hinges.

[0023] Based on the above, multiple anti-slip grooves are provided on one side of the reinforcing plate 36, and the reinforcing plate 36 is made of elastic and wear-resistant material.

[0024] Based on the above, guide grooves are provided on both sides of the inner wall of the cavity 25, and guide blocks 34 are slidably connected to the inner walls of the two guide grooves. The two guide blocks 34 are fixedly connected to the top plate 30.

[0025] An automatic welding method for aviation ducts, comprising the following steps: S1: When welding the aviation duct, one of the ducts is sleeved on the outer wall of the support column 4, and the other duct is fixed inside the support sleeve 5; S2: After the two conduits are placed, start the docking mechanism 7. The docking mechanism 7 will drive the conduits fixed in the support sleeve 5 to move downward, thereby allowing the two conduits to be docked. S3: After the two conduits are connected, the conduit welding mechanism 3 is started. The welding gun 17 is driven to rotate by the rotating component, so that the welding gun 17 rotates around the two conduits and welds the connection between the two conduits. S4: When the two conduits are connected by the docking mechanism 7, the conduit on the support column 4 will be subjected to pressure from the upper conduit. At this time, the conduit on the support column 4 will push the push plate 28 downward under the pressure. When the push plate 28 moves downward, it will drive the push rod 33 to move downward synchronously. When the push rod 33 moves downward, it will push one end of the swing plate 31 to deflect downward, while the other end of the swing plate 31 will deflect upward. At this time, when the other end of the swing plate 31 deflects upward, it will push the top plate 30 upward through the top rod 32. Since the two top shafts 35 are distributed in a V-shape, the two top shafts 35 will push the reinforcing plate 36 to move to one side of the inner wall of the conduit under the pressure, so that the reinforcing plate 36 is fixed on the inner wall of the conduit for reinforcement. S5: After welding is completed, tighten the fastening bolt 6 to remove the welded conduit from the device.

[0026] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. An automatic welding device for aviation ducts, comprising a welding station (1), characterized in that, The side of the top of the welding platform (1) is provided with a connecting seat (2) through bolt connection, the connecting seat (2) is annular, the inner wall of the connecting seat (2) is provided with a pipe welding mechanism (3) between the top, the side of the top of the welding platform (1) is provided with a supporting column (4) through bolt connection, and the supporting column (4) is located in the inside of the connecting seat (2), the top of the welding platform (1) is provided with a docking mechanism (7), and the side of the docking mechanism (7) is provided with a supporting plate (8), the other end of the supporting plate (8) is provided with a supporting sleeve (5) through bolt connection, and the both sides of the circumferential outer wall of the supporting sleeve (5) are provided with threaded holes, the inner wall of the two threaded holes is provided with a fastening bolt (6) through threaded connection, the pipe welding mechanism (3) comprises a rotating assembly, an annular slide plate (10), a supporting pad (11), a hydraulic cylinder (15) and a welding gun (17), and the inner wall of the connecting seat (2) is slidably connected with the annular slide plate (10), the bottom of the supporting pad (11) is connected with the top of the annular slide plate (10) through bolt connection, the side of the top of the supporting pad (11) is connected with the hydraulic cylinder (15) through bolt connection, and the top of the hydraulic cylinder (15) is provided with a pad (16) through bolt connection, and the top of the pad (16) is fixedly connected with the welding gun (17).

2. An apparatus for automatic welding of aircraft ducts as claimed in claim 1, wherein, The rotating assembly is composed of a welding motor (12), a rotating shaft (13), a gear (14) and a gear ring (18), the bottom of the rotating shaft (13) is rotatably connected with the welding platform (1) through a bearing, the welding motor (12) is fixedly connected with the bottom of the welding platform (1) through bolt connection, one end of the welding motor (12) is fixedly connected with the rotating shaft (13), the gear (14) is fixedly sleeved on the circumferential outer wall of the rotating shaft (13), the inner wall of the connecting seat (2) is welded with an annular sliding groove (9), the gear ring (18) is slidably connected in the inside of the annular sliding groove (9), the gear ring (18) is fixedly connected on the circumferential outer wall of the annular slide plate (10), and the side of the annular sliding groove (9) is provided with an engaging hole, and the gear (14) and the gear ring (18) are engaged in the inside of the engaging hole.

3. An apparatus for automatic welding of aircraft ducts as claimed in claim 1, wherein, The docking mechanism (7) comprises two adjusting seats (19), a screw rod (20), a supporting seat (22) and a docking motor (23), one of the adjusting seats (19) is connected with the welding platform (1) through bolt connection, the top of the other adjusting seat (19) is fixedly connected with the docking motor (23), the both ends of the screw rod (20) are rotatably connected with the two adjusting seats (19) through bearings, one end of the docking motor (23) is fixedly connected with the screw rod (20), the top of the supporting seat (22) is provided with a threaded hole, the threaded hole is threadedly connected with the screw rod (20), and the side of the supporting seat (22) is connected with the supporting plate (8) through bolt connection.

4. An aircraft duct automatic welding apparatus according to claim 3, wherein The both sides of the two adjusting seats (19) are provided with two positioning rods (21) through bolt connection, the both sides of the top of the supporting seat (22) are provided with positioning holes, and the two positioning holes are slidably connected with the two positioning rods (21).

5. An apparatus for automatic welding of aircraft ducts as defined in claim 1, wherein, The support column (4) is internally provided with a cavity (25), and a reinforcing mechanism (24) is arranged between the cavity (25) and the support column (4), and the reinforcing mechanism (24) is in cooperation with the docking mechanism (7).

6. An aircraft duct automatic welding apparatus according to claim 5, wherein The reinforcing mechanism (24) comprises a push plate (28), two swing plates (31), two push rods (33), two jacks (32), a top plate (30) and two reinforcing plates (36), the top of the push plate (28) is provided with a sliding opening, the sliding opening is in sliding connection with the support column (4), push plate springs (29) are welded between the two sides of the bottom of the push plate (28) and the support column (4), connecting openings (26) are provided through the two sides of the support column (4) and the cavity (25), the connecting openings (26) are in rotary connection with the swing plates (31) through bearings, the two ends of the push rods (33) are connected with the bottom of the push plate (28) and one side of the top of the swing plates (31) through hinges respectively, the two ends of the jacks (32) are connected with the other side of the top of the swing plates (31) and the top plate (30) through hinges respectively, the top plate (30) is in sliding connection inside the cavity (25), pull-out openings (27) are provided through the two sides of the inner wall of the cavity (25), the pull-out openings (27) are in sliding connection with the reinforcing plates (36), top shafts (35) are connected between the two sides of the top of the top plate (30) and the two reinforcing plates (36) through hinges.

7. An aircraft duct automatic welding apparatus according to claim 6, wherein The reinforcing plate (36) is provided with a plurality of anti-skid grooves on one side, and is made of elastic wear-resistant material.

8. An aircraft duct automatic welding apparatus according to claim 6, wherein The two sides of the inner wall of the cavity (25) are provided with guide grooves, and the inner walls of the two guide grooves are in sliding connection with guide blocks (34), and the two guide blocks (34) are fixedly connected with the top plate (30).

9. An automatic welding method of an aircraft duct, characterized by, The aviation conduit automatic welding device according to any one of claims 1-8, comprising the following specific steps: S1: when welding the aviation conduit, one conduit is sleeved on the outer wall of the support column (4), and the other conduit is fixed in the support sleeve (5); S2: after the two conduits are placed, the docking mechanism (7) is started, and the conduit fixed in the support sleeve (5) is driven to move downward, so that the two conduits are docked; S3: when the two conduits are docked, the conduit welding mechanism (3) is started, and the welding gun (17) is driven to rotate by the rotating assembly, so that the welding gun (17) rotates around the two conduits while welding the docking part of the two conduits; S4: When the two pipes are docked by the docking mechanism (7), the pipe on the support column (4) will be pressed by the upper pipe, at this time, the pipe on the support column (4) will push the push plate (28) to move down under the action of the pressure, and the push plate (28) will drive the push rod (33) to move down synchronously when moving down, the push rod (33) will push one end of the swing plate (31) to deflect downward while moving down, and the other end of the swing plate (31) will deflect upward, at this time, the other end of the swing plate (31) will push the top plate (30) upward through the top rod (32) when deflecting upward, since the two top shafts (35) are distributed in the shape of a Chinese character, therefore, the two top shafts (35) will push the reinforcing plate (36) to move to one side of the inner wall of the pipe under the action of the pressure, so as to fix the reinforcing plate (36) on the inner wall of the pipe, so as to facilitate the reinforcement treatment of the pipe; S5: After welding, turn the fastening bolt (6), and take out the welded pipe from the device.

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