A welding device for processing aircraft wall panels

Abstract

The invention relates to the technical field of welding, and discloses a welding device for processing aircraft wall panels, comprising a welding gun, a gun head is fixedly connected to the welding gun, an end of the welding gun close to the gun head is fixedly connected to a mounting ring, both sides of the mounting ring are fixedly connected to fixing frames, sleeves are rotatably connected to the fixing frames, inner rods are slidably connected to the ends of the sleeves away from the welding gun, and the end of the inner rod away from the welding gun is rotatably connected to the mounting frame, and mounting plates and limiting frames are rotatably connected to the two mounting frames respectively, a transmission belt A is arranged on the side of the mounting plate away from the mounting frame, and a transmission belt C is arranged on the side of the limiting frame away from the mounting frame. The welding device for processing aircraft wall panels can avoid the problem of contact between the gun head and the aircraft wall panels when the staff holds the welding gun to weld the aircraft wall panels, and friction is generated during the movement, resulting in scratch damage to the aircraft wall panels, and effectively improves the protection of the device for the aircraft wall panels.

Description

Technical Field

[0001] The invention relates to the technical field of welding, in particular to a welding device for processing aircraft wall panels. Background Art

[0002] Aircraft wall panels are usually composed of skins and long stringers, where the skin refers to a dimensional component that surrounds the aircraft frame structure and is fixed to the frame with adhesives or rivets to form the aircraft's aerodynamic shape, while the long stringer is a component arranged longitudinally along the fuselage or wing in the aircraft structure, used to support the skin and increase the overall strength and rigidity of the structure. When processing and producing aircraft wall panels, the skin and the long stringer are usually connected by welding or other methods;

[0003] The welding of aircraft panels is usually automated by welding robots. However, due to the complex structure of aircraft panels, workers are still required to perform manual welding in these complex places. When workers perform manual welding, they need to use welding guns. When operating, first dock the welding gun with the welding equipment, and then the worker can hold the welding gun and aim it at the connection between the skin and the long stringer on the aircraft panel to weld.

[0004] In the welding process of the existing aircraft wall panel welding device, due to the thin thickness of the aircraft skin, during the manual welding process, the worker is prone to shaking the hand, which causes the gun head of the welding gun to contact with the aircraft skin. During the welding process, the welding gun needs to move along the weld position. At the same time, the gun head of the welding gun is generally made of metal, which causes the gun head of the welding gun to easily scratch the skin surface and damage the skin when it is in contact with the skin and moves. For this reason, we propose a welding device for aircraft wall panel processing. Summary of the invention

[0005] The object of the present invention is to provide a welding device for processing aircraft wall panels to solve the problems raised in the above-mentioned background technology.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a welding device for processing aircraft wall panels, comprising a welding gun, a gun head is fixedly connected to the welding gun, a mounting ring is fixedly connected to one end of the welding gun close to the gun head, fixing frames are fixedly connected to both sides of the mounting ring, sleeves are rotatably connected to the fixing frames, inner rods are slidably connected to the ends of the sleeves away from the welding gun, the end of the inner rod away from the welding gun is rotatably connected to the mounting frame, a mounting plate and a limiting frame are rotatably connected to the two mounting frames respectively, a transmission belt A is provided on the side of the mounting plate away from the mounting frame, and a transmission belt C is provided on the side of the limiting frame away from the mounting frame;

[0007] A slide groove A and a slide groove B are respectively provided on both sides of the mounting plate, and both ends of the slide groove A are slidably connected with clamping plates, and transmission belts B are provided on opposite sides of the two clamping plates.

[0008] Preferably, the side of the splint close to the slide groove B is slidably connected to a connecting plate, the side of the connecting plate close to the slide groove B is fixedly connected to a slider A, and the slider A is slidably connected to the slide groove B, and a rack plate B is provided on the side of the slider A close to the connecting plate.

[0009] Preferably, the side of the slider A away from the connecting plate is fixedly connected to a limit spring, the end of the limit spring away from the slider A is fixedly connected to a slider B, and the slider B is slidably connected to the slide groove B.

[0010] Preferably, rack plates A are fixedly connected to both sides of the opening of the slide groove B, and the rack plate A and the rack plate B on the slider A are meshed with each other.

[0011] Preferably, a screw is rotatably connected inside the sleeve, the screw is threadedly connected to the inner rod, and a plurality of evenly distributed scale grooves are provided on one side of the top of the inner rod.

[0012] Preferably, a transmission cavity is opened inside the sleeve, and a bevel gear A is rotatably connected to the inner wall of the transmission cavity on one side close to the screw, and the bevel gear A is fixedly connected to one end of the screw.

[0013] Preferably, the inner top wall of the transmission cavity is rotatably connected with a bevel gear B, and the bevel gear B is meshed with the bevel gear A. The top of the sleeve is rotatably connected with a knob on one side close to the fixed frame, and the knob is fixedly connected to the bevel gear B.

[0014] Preferably, mutually connected mounting holes are provided on both sides of the knob, mutually connected connecting holes are provided between the inner bottom wall of the mounting hole and the center of the bevel gear B, pressing blocks are slidably connected to both ends of the mounting hole, transmission frames are fixedly connected to the opposite sides of the two pressing blocks, mounting springs are fixedly connected between the transmission frames, and the bottom of the transmission frame passes through the connecting hole and extends into the transmission cavity.

[0015] Preferably, the bottom wall of the transmission cavity is fixedly connected with an inner gear ring, the bottom of the transmission frame is located in the inner gear ring, and a clamping plate is fixedly connected to one side of the transmission frame close to the inner wall of the inner gear ring, and the clamping plate is meshed with the inner wall tooth blocks of the inner gear ring.

[0016] Preferably, a handle is fixedly connected to a side of the bottom of the welding gun away from the gun head, and a pipe clamp is rotatably connected to a side of the bottom of the welding gun close to the gun head through a frame.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] The present invention uses the mounting plate and the clamping plate to fit and clamp the long stringer on the aircraft wall panel, and fits the limiting frame to the skin of the aircraft wall panel. At this time, the transmission belt A of the mounting plate and the transmission belt B on the clamping plate are respectively fitted to the top and both sides of the long stringer, and the transmission belt C on the limiting frame is fitted to the surface of the aircraft skin. The friction between the mounting plate, the clamping plate and the limiting frame and the surface of the aircraft wall panel is reduced by the transmission belt A, the transmission belt B and the transmission belt C, and the distance between the gun head and the aircraft wall panel is controlled by the sleeve and the inner rod. This avoids the problem of contact between the gun head and the aircraft wall panel when the staff holds the welding gun to weld the aircraft wall panel, and friction is generated during the movement, resulting in scratch damage to the aircraft wall panel, thereby effectively improving the protection of the device for the aircraft wall panel.

[0019] The present invention presses the mounting plate, and at this time, the limit spring is squeezed and contracted, and the rack plate B is separated from the rack plate A. At this time, the clamping plate and the mounting plate can be manually moved according to the thickness of the long stringer, so that the clamping plate is attached to both sides of the long stringer, thereby cooperating with the mounting plate to complete the work of clamping the long stringer of the aircraft wall panel. After that, the mounting plate is released, and the limit spring rebounds at this time, so that the rack plate B and the rack plate A are meshed with each other, which effectively improves the auxiliary function of the device for the welding work of the aircraft wall panel;

[0020] When the telescopic length of the inner rod is adjusted, the present invention squeezes the pressing blocks on both sides of the knob to drive the transmission frame to close, so that the clamping plate is separated from the tooth block of the inner gear ring. At this time, the knob can be rotated to drive the bevel gear B and the bevel gear A to rotate, and drive the screw to rotate, so as to adjust the extension length of the inner rod. After the adjustment is completed, the knob is released, and the spring is installed to rebound, driving the transmission frame to move toward the original position. At this time, the two transmission frames are separated from each other, and each drives the clamping plate connected thereto to be clamped into the tooth block of the inner gear ring, completing the limit fixation of the knob, avoiding the problem that the telescopic length of the inner rod changes due to external factors, causing the distance between the gun head and the aircraft wall panel to change, thereby affecting the welding result, and further improving the auxiliary function of the device in the welding process of the aircraft wall panel. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0022] Figure 2 It is a schematic diagram of the casing structure of the present invention;

[0023] Figure 3 It is a schematic diagram of the cross-sectional structure of the casing of the present invention;

[0024] Figure 4 It is a schematic diagram of the internal structure of the transmission cavity of the present invention;

[0025] Figure 5 This is a schematic diagram of the structure of the helical gear B and its transmission components of the present invention;

[0026] Figure 6 This is a schematic diagram of the connection structure between the clamping plate and the inner gear ring of the present invention;

[0027] Figure 7 This is a schematic diagram of the mounting structure of the mounting plate and the clamping plate of the present invention;

[0028] Figure 8 It is a schematic diagram of the cross-sectional structure of the mounting plate of the present invention;

[0029] Fig. 9 This is a schematic diagram of the structure of the connecting plate of the present invention;

[0030] Fig.10 It is a schematic diagram of the structure of the limiting frame of the present invention;

[0031] Fig.11 For the present invention Figure 8 A schematic diagram of the enlarged structure of area A is shown.

[0032] In the figure: 1. welding gun; 11. gun head; 12. handle; 13. pipe clamp; 2. mounting ring; 21. fixing frame; 3. sleeve; 31. transmission chamber; 32. inner rod; 33. mounting frame; 34. scale groove; 4. screw; 41. bevel gear A; 5. bevel gear B; 51. knob; 52. mounting hole; 53. connecting hole; 54. pressing block; 55. transmission frame; 56. mounting spring; 57. clamping plate; 58. inner gear ring; 6. mounting plate; 61. slide A; 62. slide B; 63. rack plate A; 64. transmission belt A; 7. clamping plate; 71. transmission belt B; 72. connecting plate; 73. slider A; 74. rack plate B; 75. limit spring; 76. slider B; 8. limit frame; 81. transmission belt C. DETAILED DESCRIPTION

[0033] 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 the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0034] See also Figure 1-11The present invention provides a technical solution: a welding device for processing aircraft wall panels, including a welding gun 1. The welding gun 1 is one of the main structures of the welding device, and it needs to cooperate with the body of a laser welding machine to perform welding work. A gun head 11 is fixedly connected to the welding gun 1, and a handle 12 is fixedly connected to the side of the bottom of the welding gun 1 away from the gun head 11. A quick connector is provided at the bottom of the handle 12, and an external pipe can be quickly connected and fixed through the quick connector. At the same time, a button for control is provided on the handle 12, and the gun head 11 can be operated by pressing the button, thereby completing the welding work of the aircraft wall panel. A pipe clamp 13 is connected to the side of the bottom of the welding gun 1 close to the gun head 11 through a frame rotation.

[0035] Furthermore, the welding gun 1 is one of the main welding structures of the welding device. When in use, the connecting pipe is connected to the quick connector at the bottom of the handle 12, and connected to the body of the laser welding machine through the pipe. Then, the gun head 11 is aimed at the welding point of the aircraft wall panel, and then the button on the handle 12 is pressed. The laser ejected from the gun head 11 can be used to weld the aircraft wall panel. The pipe clamp 13 can fix the pipe for conveying welding gas so that it cooperates with the gun head 11 for welding.

[0036] Combined with Figure 1 , Figure 2 , Figure 3 , Figure 7 , Fig. 9 and Fig.10 As shown, a mounting ring 2 is fixedly connected to one end of the welding gun 1 close to the gun head 11, and a fixing frame 21 is fixedly connected to both sides of the mounting ring 2. A sleeve 3 is rotatably connected to the fixing frame 21, and a damping pad is arranged between the sleeve 3 and the fixing frame 21. The damping pad can increase the damping between the sleeve 3 and the fixing frame 21, so that the sleeve 3 will not rotate due to a small force, thereby improving its stability during the welding process. An inner rod 32 is slidably connected to the inner end of the sleeve 3 away from the welding gun 1, and a mounting frame 33 is rotatably connected to the inner end of the inner rod 32 away from the welding gun 1. A plurality of evenly distributed scale grooves 34 are arranged on one side of the top of the inner rod 32. When the inner rod 32 is extended or retracted, the scale grooves 34 are used to rotate the inner rod 32. 4 can accurately position the telescopic lengths of the two inner rods 32 respectively, so as to improve the auxiliary performance of the welding work. The two mounting frames 33 are rotatably connected with the mounting plates 6 and the limiting frames 8 respectively. The limiting frames 8 are in an inclined state. After the mounting plates 6 are placed on the long stringers of the aircraft wall panels, the inclined limiting frames 8 can make them better fit on the skin of the aircraft wall panels. A transmission belt A64 is arranged on the side of the mounting plate 6 away from the mounting frames 33, and a transmission belt C81 is arranged on the side of the limiting frames 8 away from the mounting frames 33. A slide groove A61 and a slide groove B62 are respectively provided on both sides of the mounting plate 6. Both ends of the slide groove A61 are slidably connected with the clamping plates 7. The opposite sides of the two clamping plates 7 are provided with transmission belts B71.

[0037] Furthermore, when performing welding work, first rotate the two sleeves 3 to a suitable angle, then rotate the mounting frame 33 to adjust the angles of the mounting plate 6 and the limiting frame 8, then place the mounting plate 6 on the long stringer of the aircraft, and manually close the clamping plate 7 so that the clamping plate 7 fits on both sides of the long stringer. At this time, the long stringer of the aircraft wall panel is clamped by the clamping plate 7 and the mounting plate 6. At this time, the transmission belt A64 and the transmission belt B71 are respectively fitted with the top and both sides of the long stringer. At the same time, the limiting frame 8 is fitted on the skin surface of the aircraft wall panel. At this time, the transmission belt C81 on the limiting frame 8 fits with the skin on the aircraft wall panel. At this time, the gun head 11 is fitted with the inner rod 32 through the cooperation of the two sleeves 3. The distance between the welding position of the aircraft wall panel is limited. During the welding process, the welding gun 1 is moved and the two sleeves 3 and the inner rod 32 are driven to move synchronously. At this time, through the steering function of the mounting frame 33 and the cooperation of the transmission belt A64, the transmission belt B71 and the transmission belt C81, the limiting frame 8, the mounting plate 6 and the clamping plate 7 can be moved together along the skin and the long stringer of the aircraft wall panel respectively, and during the movement, the distance between the gun head 11 and the welding position of the aircraft wall panel is always controlled to avoid contact between the gun head 11 and the aircraft wall panel when the staff holds the welding gun 1 to weld the aircraft wall panel, and friction is generated during the movement, resulting in scratches and damage to the aircraft wall panel.

[0038] Combined with Figure 7 , Figure 8 , Fig. 9 and Fig.11 As shown, a connecting plate 72 is slidably connected to one side of the clamping plate 7 close to the slide groove B62, a slider A73 is fixedly connected to one side of the connecting plate 72 close to the slide groove B62, and the slider A73 is slidably connected to the slide groove B62, a rack plate B74 is provided on one side of the slider A73 close to the connecting plate 72, a limiting spring 75 is fixedly connected to one side of the slider A73 away from the connecting plate 72, a slider B76 is fixedly connected to one end of the limiting spring 75 away from the slider A73, and the slider B76 is slidably connected to the slide groove B62, a telescopic rod is provided in the limiting spring 75, and the limiting spring 75 can be limited by the telescopic rod. , so that in the process of moving the slider A73, the slider B76 can be driven to move together through the telescopic rod without bending the limit spring 75. Rack plates A63 are fixedly connected on both sides of the opening of the slide groove B62. The rack plate A63 and the rack plate B74 on the slider A73 are meshed with each other. The spacing between the tooth blocks on the rack plate A63 and the rack plate B74 is small. Through the small spacing between the tooth blocks, it can be ensured that the rack plate B74 can be meshed with the rack plate A63 at any time after the slider A73 moves any distance, thereby completing the limiting work of the connecting plate 72.

[0039] Further, after the mounting plate 6 is placed on the long stringer of the aircraft wall panel, the connecting plate 72 can be squeezed manually. At this time, the limit spring 75 is squeezed to shrink. After the limit spring 75 shrinks, the rack plate B74 will be separated from the rack plate A63. At this time, the rack plate B74 cooperates with the rack plate A63, and the limiting effect on the connecting plate 72 and the clamping plate 7 disappears. At this time, the clamping plate 7 and the connecting plate 72 can be manually moved to make the clamping plate 7 fit on both sides of the long stringer, thereby cooperating with the mounting plate 6 to complete. The long stringer of the aircraft wall panel is clamped, and then the connecting plate 72 is released. At this time, the limit spring 75 rebounds and pushes the slider A73 to move toward the rack plate A63 until the rack plate B74 and the rack plate A63 are fitted together. At this time, the rack plate B74 and the rack plate A63 are meshed with each other. At this time, the connection plate 72 can be limited and fixed, and the position of the splint 7 is limited by the connecting plate 72, making it more convenient to adjust the distance between the splints 7 according to the thickness of the long stringer.

[0040] Combined with Figure 3 , Figure 4 , Figure 5 and Figure 6 As shown, a screw rod 4 is rotatably connected inside the sleeve 3, and the screw rod 4 is threadedly connected to the inner rod 32. A transmission chamber 31 is opened inside the sleeve 3, and a bevel gear A41 is rotatably connected to the inner wall of the transmission chamber 31 near the screw rod 4, and the bevel gear A41 is fixedly docked with one end of the screw rod 4. A bevel gear B5 is rotatably connected to the inner top wall of the transmission chamber 31, and the bevel gear B5 and the bevel gear A41 are meshed with each other. A knob 51 is rotatably connected to the side of the top of the sleeve 3 near the fixed frame 21, and the knob 51 is fixedly connected to the bevel gear B5. Both sides of the knob 51 are provided with mutually connected mounting holes 52, and a connecting hole 53 that is interconnected is provided between the inner bottom wall of the mounting hole 52 and the center of the bevel gear B5, and both ends of the mounting hole 52 are slidably connected with pressing blocks 54 , the two pressing blocks 54 are fixedly connected to the opposite sides with a transmission frame 55, and a mounting spring 56 is fixedly connected between the transmission frames 55. The bottom of the transmission frame 55 passes through the connecting hole 53 and extends into the transmission cavity 31. The inner bottom wall of the transmission cavity 31 is fixedly connected with an inner gear ring 58. The bottom of the transmission frame 55 is located in the inner gear ring 58. A clamping plate 57 is fixedly connected to the side of the transmission frame 55 close to the inner wall of the inner gear ring 58. The clamping plates 57 are meshed with the inner wall tooth blocks of the inner gear ring 58. The spacing between the tooth blocks on the inner wall of the inner gear ring 58 is the same as the thickness of the clamping plate 57. When the clamping plate 57 is inserted between the tooth blocks on the inner wall of the inner gear ring 58, the fit between the inner gear ring 58 and the clamping plate 57 can be improved, thereby improving the limiting effect on the knob 51 and the bevel gear B5.

[0041] Furthermore, when adjusting the telescopic length of the inner rod 32, the staff can press the pressing blocks 54 on both sides of the knob 51 with two fingers to close the two pressing blocks 54 to each other, and squeeze and contract the mounting spring 56 through the two pressing blocks 54. At this time, the two pressing blocks 54 will drive the transmission frame 55 to close to each other, thereby driving the clamping plate 57 to disengage from the tooth block on the inner wall of the inner gear ring 58 through the transmission frame 55. At this time, the knob 51 can be rotated to drive the bevel gear B5 to rotate, and the rotating bevel gear B5 drives the bevel gear A41 to rotate. When the bevel gear A41 rotates, it can drive the screw rod 4 connected thereto to rotate. During the rotation of the screw rod 4, the inner rod 32 is limited by the sleeve 3, so that the inner rod 32 cannot rotate normally. Therefore, at this time, the rotation force of the screw rod 4 can be converted into a straight line through the limiting effect. The moving force drives the inner rod 32 to extend and retract along the sleeve 3. The telescopic state of the inner rod 32 can be changed by changing the rotation direction of the knob 51. When the telescopic length of the inner rod 32 is adjusted, the knob 51 is released. At this time, the extrusion force on the mounting spring 56 disappears and begins to rebound, driving the transmission frame 55 and the pressing block 54 back to their original positions. At this time, the transmission frame 55 can drive the clamping plate 57 to be clamped between the tooth blocks of the inner gear ring 58 in the process of returning to its original position. At this time, the clamping plate 57 cooperates with the inner gear ring 58 to complete the automatic limiting of the knob 51, and the bevel gear B5 is limited by the fixed knob 51 to prevent the inner rod 32 from extending and retracting by itself due to external factors, resulting in the gun head 11 touching the aircraft wall panel during the welding process, thereby causing scratches and damage to the aircraft wall panel.

[0042] Working principle: When in use, connect the connecting pipe at the quick connector at the bottom of the handle 12, and connect it to the body of the laser welding machine through the pipe. Then the staff can press the pressing blocks 54 on both sides of the knob 51 with two fingers to make the two pressing blocks 54 close to each other, and squeeze and contract the installation spring 56 through the two pressing blocks 54. At this time, the two pressing blocks 54 will drive the transmission frame 55 to close to each other, so as to drive the card plate 57 to disengage from the tooth block on the inner wall of the inner gear ring 58 through the transmission frame 55. At this time, the knob 51 can be rotated, and the bevel gear B5 can be driven to rotate. The rotating bevel gear B5 drives the bevel gear A41 to rotate. When the bevel gear A41 rotates, it can drive the screw 4 connected to it. The inner rod 32 is driven to extend out of the sleeve 3 through the cooperation of the rotating screw rod 4 and the limiting function of the sleeve 3. At this time, the extension lengths of the two inner rods 32 can be respectively positioned through the scale grooves 34 on the inner rod 32. When the telescopic length of the inner rod 32 is adjusted, the knob 51 is released. At this time, the squeezing force on the mounting spring 56 disappears and starts to rebound, driving the transmission frame 55 and the pressing block 54 back to the original position. At this time, the transmission frame 55 can drive the clamping plate 57 to be clamped between the tooth blocks of the inner gear ring 58 in the process of returning to the original position. At this time, the clamping plate 57 cooperates with the inner gear ring 58 to complete the automatic limit of the knob 51, and the bevel gear B5 is limited by the fixed knob 51;

[0043] Then, the mounting frame 33 is rotated to adjust the angles of the mounting plate 6 and the limiting frame 8, and then the mounting plate 6 is placed on the long stringer of the aircraft. After the mounting plate 6 is placed on the long stringer of the aircraft wall panel, the connecting plate 72 can be manually squeezed, and the limiting spring 75 is squeezed to shrink it. After the limiting spring 75 shrinks, the rack plate B74 will be separated from the rack plate A63. At this time, the rack plate B74 cooperates with the rack plate A63, and the limiting effect of the connecting plate 72 and the clamping plate 7 disappears. At this time, the clamping plate 7 and the connecting plate 72 can be manually moved to make the clamping plate 7 fit on both sides of the long stringer, thereby cooperating with the mounting plate 6 to complete the work of clamping the long stringer of the aircraft wall panel, and then the connecting plate 72 is released. At this time, the limiting spring 75 rebounds and pushes the slider A 73 moves toward the rack plate A63 until the rack plate B74 and the rack plate A63 fit together. At this time, the rack plate B74 and the rack plate A63 mesh with each other. At this time, the limiting fixation of the connecting plate 72 can be completed, and the position of the clamping plate 7 is limited by the connecting plate 72. At this time, the clamping plate 7 and the mounting plate 6 cooperate to clamp the long stringer of the aircraft wall panel. At this time, the transmission belt A64 and the transmission belt B71 are respectively fitted with the top and both sides of the long stringer. At the same time, the limiting frame 8 is fitted on the skin surface of the aircraft wall panel. At this time, the transmission belt C81 on the limiting frame 8 fits with the skin on the aircraft wall panel. At this time, the distance between the gun head 11 and the welding point of the aircraft wall panel is limited by the cooperation of the two sleeves 3 and the inner rod 32;

[0044] In the subsequent welding process, the welding gun 1 is moved and the two sleeves 3 and the inner rod 32 are driven to move synchronously. At this time, through the steering function of the mounting frame 33 and the cooperation of the transmission belt A64, the transmission belt B71 and the transmission belt C81, the limit frame 8, the mounting plate 6 and the clamping plate 7 can be moved together along the skin and the long stringer of the aircraft wall panel respectively, and during the movement, the distance between the gun head 11 and the welding position of the aircraft wall panel is always controlled, and then the button on the handle 12 is pressed to weld the aircraft wall panel through the laser ejected from the gun head 11.

[0045] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0046] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A welding device for processing aircraft panels, comprising a welding gun (1), to which a gun head (11) is fixedly connected, characterized in that: The end of the welding gun (1) close to the gun head (11) is fixedly connected to a mounting ring (2), and both sides of the mounting ring (2) are fixedly connected to a fixing frame (21), and a sleeve (3) is rotatably connected to the fixing frame (21), and an inner rod (32) is slidably connected to the end of the sleeve (3) away from the welding gun (1), and the end of the inner rod (32) away from the welding gun (1) is rotatably connected to the mounting frame (33), and a screw rod (4) is rotatably connected to the sleeve (3), and the screw rod (4) is threadedly connected to the inner rod (32), and a plurality of evenly distributed scale grooves (34) are provided on one side of the top of the inner rod (32), and a transmission cavity (31) is opened in the sleeve (3), and the transmission cavity (31) is close to the screw rod ( The inner wall of one side of the transmission chamber (4) is rotatably connected to a bevel gear A (41), and the bevel gear A (41) is fixedly connected to one end of the screw rod (4); the inner top wall of the transmission chamber (31) is rotatably connected to a bevel gear B (5), and the bevel gear B (5) and the bevel gear A (41) are meshed with each other; the top of the sleeve (3) is rotatably connected to a knob (51) on a side close to the fixing frame (21), and the knob (51) is fixedly connected to the bevel gear B (5); the two mounting frames (33) are rotatably connected to a mounting plate (6) and a limiting frame (8), respectively; a transmission belt A (64) is provided on a side of the mounting plate (6) away from the mounting frame (33), and a transmission belt C (81) is provided on a side of the limiting frame (8) away from the mounting frame (33); The mounting plate (6) is provided with a slide groove A (61) and a slide groove B (62) on both sides, and the two ends of the slide groove A (61) are slidably connected to a clamping plate (7). The two opposite sides of the two clamping plates (7) are provided with a transmission belt B (71). The side of the clamping plate (7) close to the slide groove B (62) is slidably connected to a connecting plate (72). The side of the connecting plate (72) close to the slide groove B (62) is fixedly connected to a slider A (73). The slider A (73) is slidably connected to the slide groove B (62). The slider A (73) is close to the slide groove B (62). A rack plate B (74) is provided on one side near the connecting plate (72); a side of the slider A (73) away from the connecting plate (72) is fixedly connected to a limit spring (75); an end of the limit spring (75) away from the slider A (73) is fixedly connected to a slider B (76); the slider B (76) is slidably connected to the slide groove B (62); both sides of the opening of the slide groove B (62) are fixedly connected to the rack plate A (63); the rack plate A (63) and the rack plate B (74) on the slider A (73) are meshed with each other.

2. A welding device for processing aircraft wall panels according to claim 1, characterized in that: Both sides of the knob (51) are provided with mutually communicating mounting holes (52); a mutually communicating connecting hole (53) is provided between the inner bottom wall of the mounting hole (52) and the center of the bevel gear B (5); both ends of the mounting hole (52) are slidably connected with a pressing block (54); opposite sides of the two pressing blocks (54) are fixedly connected with a transmission frame (55); mounting springs (56) are fixedly connected between the transmission frames (55); and the bottom of the transmission frame (55) passes through the connecting hole (53) and extends into the transmission cavity (31).

3. A welding device for processing aircraft wall panels according to claim 2, characterized in that: An inner gear ring (58) is fixedly connected to the inner bottom wall of the transmission chamber (31), the bottom of the transmission frame (55) is located in the inner gear ring (58), and a clamping plate (57) is fixedly connected to one side of the transmission frame (55) close to the inner wall of the inner gear ring (58), and the clamping plate (57) is meshed with the inner wall tooth blocks of the inner gear ring (58).

4. The welding device for processing aircraft wall panels according to claim 1, characterized in that: A handle (12) is fixedly connected to a side of the bottom of the welding gun (1) away from the gun head (11), and a pipe clamp (13) is rotatably connected to a side of the bottom of the welding gun (1) close to the gun head (11) via a frame.

Images