Aerospace structure welding fixture and method

Abstract

The application discloses a kind of aerospace structural member welding fixing device and method, including chassis, the bottom vertical fixed connection of chassis has support frame.The application is by setting first clamping component, first clamping component is fixed to first aerospace structural member and is clamped, second clamping component is fixed to second aerospace structural member and is clamped, sliding frame rotates around mounting seat and changes the orientation of second aerospace structural member, position adjusting part controls second aerospace structural member and moves along the arc-shaped guide frame and is adjusted, the inclination of second aerospace structural member is adjusted, spacing control part controls the distance between second aerospace structural member and first aerospace structural member, fifth drive motor can drive inner ring rotation by fourth worm and fourth worm wheel, when inner ring rotates, it will drive second aerospace structural member to rotate by second clamping component to change its own rotating position, to realize the purpose of adjusting the freedom of second aerospace structural member in clamping state.

Description

Technical Field

[0001] This invention relates to the field of welding and fixing device technology, and in particular to a welding and fixing device and method for aerospace structural components. Background Technology

[0002] Aerospace structural components are the main components used in spacecraft, typically including cabin structures, heat shields, and connection and separation devices. Welding is a key process in the manufacturing of aerospace structural components, and the quality of welding directly affects the strength and precision of the aerospace structural components. During welding, aerospace structural components are fixed by fixing devices to improve their stability before the welding operation is performed.

[0003] The fixing device secures aerospace structural components by clamping. Both aerospace structural components need to be clamped and positioned. The fixed positions of the two aerospace structural components can generally only slide and dock, making it difficult to adjust the clamped aerospace structural components with multiple degrees of freedom. If the clamping position of one aerospace structural component is incorrect, it is necessary to repeat the clamping to adjust the position of the aerospace structural component.

[0004] Therefore, how to provide a welding and fixing device and method for aerospace structural components is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] One objective of this invention is to provide a welding and fixing device and method for aerospace structural components. This invention solves the problems of existing fixing devices that can only perform sliding butt welding on two aerospace structural components, making it difficult to adjust the clamped aerospace structural components to multiple degrees of freedom, and requiring repeated clamping operations if the clamping position of the aerospace structural components is incorrect.

[0006] According to an embodiment of the present invention, a welding and fixing device and method for aerospace structural components includes a chassis, a support frame vertically fixedly connected to the bottom of the chassis, a mounting seat provided at the top of the support frame, a first clamping assembly provided at the top of the mounting seat, and a first aerospace structural component clamped and connected to the first clamping assembly; a sliding frame movably sleeved on the side of the mounting seat, an arc-shaped guide frame fixedly connected to the surface of the sliding frame, a position adjusting component slidably connected to the side of the arc-shaped guide frame, a spacing control component provided on the position adjusting component, a second clamping assembly provided on the spacing control component, and a second aerospace structural component clamped and connected to the second clamping assembly.

[0007] The first clamping assembly includes a first drive motor, a first worm gear, two sets of first positioning blocks, two sets of first rotating shafts, two sets of first worm wheels, two sets of first clamping rods, and two sets of clamping plates. The first drive motor is fixedly installed inside the support frame. The output shaft of the first drive motor passes through the mounting base and extends to the top of the mounting base, where it is fixedly connected to the bottom end of the first worm gear. The two sets of first positioning blocks are fixedly connected to the top of the mounting base symmetrically about the first worm gear. The two sets of first positioning blocks are movably sleeved on the surfaces of the two sets of first rotating shafts through two sets of second bearings. The two sets of first worm wheels are fixedly sleeved on the surfaces of the two sets of first rotating shafts. The first worm gear meshes with both sets of first worm wheels. The two sets of first clamping rods are fixedly connected to the two end faces of the first rotating shafts. The two sets of clamping plates are located at the ends of the first clamping rods away from the rotating shafts. The first aerospace structural component is clamped and connected through the two sets of clamping plates.

[0008] The mounting base is a circular base with annular grooves on its top and bottom near the outermost positions. The sliding frame includes a stabilizing bracket, a tapered bearing, a fixing rod, and a fixing ring. The tapered bearing is fixedly sleeved inside the annular groove and on the side of the mounting base. The stabilizing bracket is fixedly sleeved on the side of the tapered bearing. The fixing rod is fixedly connected to the bottom of the stabilizing bracket. The fixing ring is rotatably sleeved on the surface of the support frame via a first bearing. The arc-shaped guide frame is fixedly connected to the side of the fixing ring and the bottom end of the fixing rod, respectively. The top of the mounting base is provided with an annular worm gear. The top of the mounting base is also provided with a drive assembly, which includes a sixth drive motor, a first transmission wheel, a second transmission wheel, a transmission belt, and a fifth worm. The top of the stabilizing bracket has a placement slot. The fifth worm is rotatably connected inside the placement slot. The first transmission wheel is fixedly sleeved on the surface of the fifth worm. The sixth drive motor is fixedly connected to the surface of the stabilizing bracket. The second transmission wheel is fixedly connected to the output shaft end of the sixth drive motor. The transmission belt is sleeved on the surfaces of the first and second transmission wheels, respectively. The fifth worm meshes with the annular worm gear.

[0009] A connecting assembly is provided between the clamping rod and the clamping plate. The connecting assembly includes a docking conical groove, a docking cone block, a docking square tube, a second positioning block, a side clamping plate, and a tension spring. The docking conical groove is located at the end of the first clamping rod away from the first rotating shaft. The docking cone block and the docking square tube are both fixedly connected to the surface of the clamping plate. The docking cone block is located inside the docking square tube and is movably connected inside the docking conical groove. The docking square tube is movably sleeved on the end face of the first clamping rod. The second positioning block is fixedly connected to the side of the docking square tube. The side clamping plate is rotatably connected to the side of the first clamping rod through a positioning shaft. One end of the tension spring is fixedly connected to the side of the first clamping rod, and the other end of the tension spring is fixedly connected to the inner side of the side clamping plate. One end of the side clamping rod is clamped to the surface of the second positioning block.

[0010] The arc-shaped guide has toothed grooves on its side, and arc-shaped grooves are formed on both the outer and inner sides of the arc-shaped guide. The position adjustment component includes a roller assembly, a position moving frame, a second drive motor, a second worm, a second rotating shaft, and a second worm wheel. The roller assembly is tumblingly connected inside the arc-shaped groove, and the end face of the roller assembly is fixedly connected to the surface of the position moving frame. The second rotating shaft is rotatably connected to the side of the position moving frame through a third bearing. The second drive motor is fixedly mounted on the surface of the position moving frame. The second worm is fixedly connected to the output shaft end of the second drive motor. The second worm wheel is fixedly sleeved on the surface of the second rotating shaft. The second worm wheel meshes with the second worm and meshes with the toothed groove.

[0011] The spacing control component includes a guide screw, a threaded knob, a pulley, a connecting belt, a transmission gear, a drive gear, and a third drive motor. There are four sets of guide screws, evenly distributed on the second clamping assembly. The other end of each guide screw passes through the position moving frame and extends to the other side of the frame. The threaded knob is rotatably connected to the surface of the position moving frame via a fourth bearing, and its threads are threaded onto the surface of the guide screw. The pulley is fixedly connected to the end face of the threaded knob and movably sleeved on the surface of the guide screw. The connecting belt is movably sleeved on the surface of the pulley. The transmission gear is fixedly connected to the end face of one set of pulleys. The third drive motor is fixedly connected to the surface of the position moving frame, and the drive gear is fixedly connected to the output shaft end of the third drive motor. The drive gear and the transmission gear mesh with each other.

[0012] The second clamping assembly includes a fixed outer frame plate, an inner ring, a clamping slot, a second clamping rod, a driving rod, a fourth drive motor, a third worm gear, a third worm wheel, and a connecting frame. The fixed outer frame plate is fixedly connected to the end face of the guide screw. The inner ring is set on the inner wall of the fixed outer frame plate. The clamping slot is opened on the surface of the inner ring, connecting the side of the inner ring to the inner wall. One end of the second clamping rod is rotatably connected to the inside of the clamping slot through a fixed shaft. One end of the driving rod is rotatably connected to the side of the second clamping rod, and the other end of the driving rod is rotatably connected to the inner wall of the third worm wheel. The third worm wheel is rotatably sleeved on the outside of the inner ring. The connecting frame is fixedly installed on the surface of the inner ring, and the other end of the connecting frame is fixedly connected to the surface of the fourth drive motor. The third worm gear is fixedly connected to the output shaft end of the fourth drive motor, and the third worm gear and the third worm wheel mesh with each other.

[0013] The number of clamping slots is four sets, and the number of second clamping rods and driving rods is also four sets. The clamping slots are arranged in a circular array with the center of the inner circle as the array center. The number and position of the second clamping rods and driving rods match the number and position of the clamping slots.

[0014] A fifth drive motor is also provided on the side of the fixed outer frame plate. A fourth worm is rotatably connected to the side of the fixed outer frame plate corresponding to the position of the fifth drive motor. The end face of the fourth worm is fixedly connected to the output shaft of the fifth drive motor. A fourth worm wheel is fixedly sleeved on the side of the inner ring corresponding to the position of the fourth worm. The fourth worm wheel and the fourth worm mesh with each other.

[0015] The steps for using the aerospace structural component welding and fixing device are as follows:

[0016] S1. First, the first aerospace structural component and the second aerospace structural component are clamped and stabilized by the first clamping assembly and the second clamping assembly.

[0017] S3. Adjust the position of the second aerospace structural component in the clamping state as needed by using the position adjustment component and the drive component respectively. The adjustment of the position adjustment component and the drive component is not in any particular order.

[0018] S3. After the orientation of the second aerospace structural component is determined, the spacing control component is used to move the second aerospace structural component in the clamping state so that it fits tightly against the surface of the first aerospace structural component, and then the welding operation is performed.

[0019] The beneficial effects of this invention are:

[0020] By setting a first clamping assembly to fix and clamp the first aerospace structural component, and then a second clamping assembly to fix and clamp the second aerospace structural component, the sliding frame rotates around the mounting base to change the orientation of the second aerospace structural component. The position adjustment component controls the movement of the second aerospace structural component along the arc-shaped guide frame to adjust its position, thereby adjusting the inclination of the second aerospace structural component. Then, the distance between the second aerospace structural component and the first aerospace structural component is controlled by the spacing control component. The fifth drive motor drives the inner ring to rotate through the fourth worm and the fourth worm wheel. When the inner ring rotates, it drives the second aerospace structural component to rotate through the second clamping assembly to change its own rotational position, thereby achieving the purpose of adjusting the degrees of freedom of the second aerospace structural component in the clamped state. This solves the problem that the existing fixing device can only perform sliding butt welding on two aerospace structural components, and it is difficult to perform multi-degree-of-freedom adjustment on the clamped aerospace structural component, and the need to repeat the clamping operation if the clamping position of the aerospace structural component is incorrect. Attached Figure Description

[0021] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings:

[0022] Figure 1 This is a schematic diagram of the overall three-dimensional structure of a welding and fixing device and method for aerospace structural components proposed in this invention.

[0023] Figure 2 This is a cross-sectional three-dimensional structural diagram of the position of the first clamping component in the welding and fixing device and method for aerospace structural components proposed in this invention.

[0024] Figure 3 This is a three-dimensional cross-sectional structural diagram of the connecting component position in a welding and fixing device and method for aerospace structural components proposed in this invention.

[0025] Figure 4 This is a partial three-dimensional structural diagram of the arc-shaped guide frame, the second clamping assembly, the position adjusting component, and the spacing control assembly in the connection state of a welding and fixing device and method for aerospace structural components proposed in this invention.

[0026] Figure 5 This is a partial three-dimensional structural diagram of the position of the second clamping component in a welding and fixing device and method for aerospace structural components proposed in this invention.

[0027] Figure 6 This is a three-dimensional cross-sectional view of the fifth drive motor position in the aerospace structural component welding and fixing device and method proposed in this invention.

[0028] Figure 7 This is a three-dimensional cross-sectional structural diagram of the driving component position in a welding and fixing device and method for aerospace structural components proposed in this invention.

[0029] Figure 8 This is a structural schematic diagram of the position of the spacing control component in a welding and fixing device and method for aerospace structural components proposed in this invention.

[0030] The attached diagram shows: 1. Chassis; 2. Support frame; 3. Mounting base; 4. First clamping assembly; 5. First aerospace structural component; 6. Sliding frame; 7. Arc-shaped guide frame; 8. Position adjustment component; 9. Spacing control component; 10. Second clamping assembly; 11. Second aerospace structural component; 12. First drive motor; 13. First worm gear; 14. First positioning block; 15. First rotating shaft; 16. First worm wheel; 17. First clamping rod; 18. Clamping plate; 19. Annular groove; 20. Stabilizing bracket; 21. Conical bearing; 22. Fixing rod; 23. Fixing ring; 24. Annular worm wheel; 25. Sixth drive motor; 26. First transmission wheel; 27. Second transmission wheel; 28. Transmission belt; 29. ​​Fifth worm gear; 30. Docking conical groove; 31. Docking. 32. Conical block; 33. Connecting square tube; 34. Second positioning block; 35. Side clamping plate; 36. Tension spring; 37. Tooth groove; 38. Arc groove; 39. Roller assembly; 40. Position moving frame; 41. Second drive motor; 42. Second worm gear; 43. Second rotating shaft; 44. Second worm wheel; 45. Guide screw; 46. Threaded knob; 47. Pulley; 48. Connecting belt; 49. Transmission gear; 50. Drive gear; 51. Third drive motor; 52. Fixed outer frame plate; 53. Inner ring; 54. Clamping through groove; 55. Second clamping rod; 56. Driving rod; 57. Fourth drive motor; 58. Third worm gear; 59. Connecting frame; 60. Fifth drive motor; 61. Fourth worm gear; 62. Fourth worm wheel. Detailed Implementation

[0031] The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic diagrams, illustrating only the basic structure of the invention, and therefore only show the components relevant to the invention.

[0032] refer to Figure 1-8In this embodiment, a chassis 1 is included. A support frame 2 is vertically fixedly connected to the bottom of the chassis 1. A mounting base 3 is provided on the top of the support frame 2. A first clamping assembly 4 is provided on the top of the mounting base 3. A first aerospace structural component 5 is clamped and connected to the first clamping assembly 4. The first clamping assembly 4 includes a first drive motor 12, a first worm gear 13, two sets of first positioning blocks 14, two sets of first rotating shafts 15, two sets of first worm wheels 16, two sets of first clamping rods 17, and two sets of clamping plates 18. The first drive motor 12 is fixedly installed inside the support frame 2. The output shaft of the first drive motor 12 passes through the mounting base 3 and extends to the top of the mounting base 3. The top is fixedly connected to the bottom end of the first worm gear 13. Two sets of first positioning blocks 14 are fixedly connected to the top of the mounting base 3 in an axially symmetrical manner with the first worm gear 13 as the axis of symmetry. The two sets of first positioning blocks 14 are movably sleeved on the surface of the two sets of first rotating shafts 15 through two sets of second bearings. Two sets of first worm wheels 16 are fixedly sleeved on the surface of the two sets of first rotating shafts 15. The first worm gear 13 meshes with the two sets of first worm wheels 16. Two sets of first clamping rods 17 are fixedly connected to the two end faces of the first rotating shaft 15. Two sets of clamping plates 18 are set at the end of the first clamping rod 17 away from the rotating shaft. The first aerospace structural component 5 is clamped and connected through the two sets of clamping plates 18.

[0033] In specific implementation, the mounting base 3 is a circular base. When the first drive motor 12 is started, the first drive motor 12 will drive the first worm gear 13 to rotate. The rotation of the first worm gear 13 will drive the two sets of first worm wheels 16 on the two sets of first rotating shafts 15 to rotate. The synchronous rotation of the two sets of first worm wheels 16 will drive the two sets of first rotating shafts 15 to rotate. The rotation of the two sets of first rotating shafts 15 will drive the first clamping rods 17 to move closer to each other. The two sets of first clamping rods 17 moving closer to each other will drive the two sets of clamping plates 18 to clamp and stabilize the first aerospace structural component 5.

[0034] refer to Figure 1-8 In this embodiment, a connecting assembly is provided between the clamping rod and the clamping plate 18. The connecting assembly includes a docking conical groove 30, a docking conical block 31, a docking square tube 32, a second positioning block 33, a side clamping plate 34, and a tension spring 35. The docking conical groove 30 is opened at the end of the first clamping rod 17 away from the first rotating shaft 15. The docking conical block 31 and the docking square tube 32 are both fixedly connected to the surface of the clamping plate 18. The docking conical block 31 is located inside the docking square tube 32 and is movably connected inside the docking conical groove 30. The docking square tube 32 is movably sleeved on the end face of the first clamping rod 17. The second positioning block 33 is fixedly connected to the side of the docking square tube 32. The side clamping plate 34 is rotatably connected to the side of the first clamping rod 17 through a positioning shaft. One end of the tension spring 35 is fixedly connected to the side of the first clamping rod 17, and the other end of the tension spring 35 is fixedly connected to the inner side of the side clamping plate 34. One end of the side clamping rod is clamped to the surface of the second positioning block 33.

[0035] In practice, the clamping plate 18 can be replaced according to the actual object being clamped. To facilitate replacement, a connecting assembly is designed. When the clamping plate 18 needs to be removed, first, the side clamping plates 34 on both sides of the first clamping rod 17 need to be pinched, causing one end of the two side clamping plates 34 to rotate around the connection between the side clamping rod and the first clamping rod 17. When one end of the two side clamping plates 34 moves closer to each other, the other ends of the two side clamping plates 34 move further apart. In this way, the two side clamping plates 34 will separate synchronously with the second positioning block 33. Then, the clamping plate 18 is moved, causing it to drive the docking cone block 31 and... The square tube 32 is separated from the end face of the first clamping rod 17. Then, the other clamping plates 18 are operated in reverse order and fitted onto the end face of the first clamping rod 17. The clamping plate 18 is then positioned by two side clamping plates 34 on the second positioning block 33 on the side of the square tube 32. The purpose of the docking cone block 31 is to increase the stability of the clamping plate 18. During the clamping process, the docking cone block 31 is tightly inserted into the docking cone groove 30 under the clamping of the side clamping plates 34 to reduce the gap at that position, thereby improving the stability of the clamping plate 18.

[0036] refer to Figure 1-8 In this embodiment, a sliding frame 6 is movably sleeved on the side of the mounting base 3. The mounting base 3 is a circular base, and annular grooves 19 are formed on the top and bottom of the mounting base 3 near the outermost position. The sliding frame 6 includes a stabilizing bracket 20, a tapered bearing 21, a fixing rod 22, and a fixing ring 23. The tapered bearing 21 is fixedly sleeved inside the annular groove 19 and on the side of the mounting base 3. The stabilizing bracket 20 is fixedly sleeved on the side of the tapered bearing 21. The fixing rod 22 is fixedly connected to the bottom of the stabilizing bracket 20. The fixing ring 23 is rotatably sleeved on the surface of the support frame 2 through a first bearing. The arc-shaped guide frame 7 is fixedly connected to the side of the fixing ring 23 and the bottom end of the fixing rod 22, respectively. The top of the mounting base 3... The mounting base 3 is equipped with an annular worm gear 24 and a drive assembly on its top. The drive assembly includes a sixth drive motor 25, a first transmission wheel 26, a second transmission wheel 27, a drive belt 28, and a fifth worm 29. The top of the stabilizing bracket 20 has a placement slot. The fifth worm 29 is rotatably connected inside the placement slot. The first transmission wheel 26 is fixedly sleeved on the surface of the fifth worm 29. The sixth drive motor 25 is fixedly connected to the surface of the stabilizing bracket 20. The second transmission wheel 27 is fixedly connected to the output shaft end of the sixth drive motor 25. The drive belt 28 is respectively sleeved on the surfaces of the first transmission wheel 26 and the second transmission wheel 27. The fifth worm 29 meshes with the annular worm gear 24.

[0037] In practice, after the second aerospace structural component 11 is clamped by the second clamping assembly 10, the sixth drive motor 25 is started. The start of the sixth drive motor 25 will drive the first transmission wheel 26 to rotate. The first transmission wheel 26 drives the second transmission wheel 27 to rotate through the transmission belt 28. The rotation of the second transmission wheel 27 will drive the fifth worm gear 29 to rotate. The rotation of the fifth worm gear 29 will drive the annular worm wheel 24 to rotate. Since the annular worm wheel 24 is stationary, the rotation of the fifth worm wheel will drive the stabilizing bracket 20 to rotate around the side of the mounting base 3. The rotation of the stabilizing bracket 20 will drive the fixing rod 22 to rotate. The arc-shaped guide 7 rotates on the support frame 2 via the fixing ring 23. The fixing ring 23 is used to improve the stability of the arc-shaped guide 7. The rotation of the arc-shaped guide 7 will drive the second aerospace structural component 11 to rotate around the mounting base 3 through the position adjustment component 8 and the second clamping component 10, thereby adjusting the orientation of the second aerospace structural component 11. After the second aerospace structural component 11 is fixed, only the orientation of the first aerospace structural component 5 needs to be changed. It is not necessary for both to have orientation adjustment functions. In this way, changing the orientation of the second aerospace structural component 11 achieves the orientation adjustment of the second aerospace structural component 11 in the clamping state.

[0038] refer to Figure 1-8 In this embodiment, an arc-shaped guide frame 7 is fixedly connected to the surface of the sliding frame 6, and a position adjustment component 8 is slidably connected to the side of the arc-shaped guide frame 7. The side of the arc-shaped guide frame 7 is provided with toothed grooves 36, and arc-shaped grooves 37 are provided on both the outer and inner sides of the arc-shaped guide frame. The position adjustment component 8 includes a roller assembly 38, a position moving frame 39, a second drive motor 40, a second worm 41, a second rotating shaft 42, and a second worm wheel 43. The roller assembly 38 is rotatably connected to the inside of the arc-shaped grooves 37, and the end face of the roller assembly 38 is fixedly connected to the surface of the position moving frame 39. The second rotating shaft 42 is rotatably connected to the side of the position moving frame 39 through a third bearing. The second drive motor 40 is fixedly installed on the surface of the position moving frame 39. The second worm 41 is fixedly connected to the output shaft end of the second drive motor 40. The second worm wheel 43 is fixedly sleeved on the surface of the second rotating shaft 42. The second worm wheel 43 meshes with the second worm 41 and meshes with the toothed grooves 36.

[0039] In specific implementation, when it is necessary to change the longitudinal position and angle of the clamped second aerospace structural component 11, the second drive motor 40 is first started. The second drive motor 40 drives the second worm gear 41 to rotate, which in turn drives the second worm wheel 43 to rotate. The rotation of the second worm wheel 43 drives the second rotating shaft 42 to rotate, which in turn drives another second worm wheel 43 to rotate. The two second worm wheels 43 mesh with the tooth groove 36. Thus, the rotation of the two second worm wheels 43 drives the position moving frame 39 to move along the arc-shaped guide frame 7 via the roller group 38 through the tooth groove 36. The movement of the position moving frame 39 along the arc-shaped guide frame 7 drives the second clamping assembly 10 and the clamped second aerospace structural component 11 to move along the arc-shaped guide frame 7, thereby changing the pitch angle and height position of the second clamping assembly 10 in the clamping state. In this way, the second aerospace structural component 11 can be welded to the first aerospace structural component 5 in an inclined state, increasing the degree of freedom of welding.

[0040] refer to Figure 1-8 In this embodiment, the position adjusting component 8 is provided with a spacing control component 9, which includes a guide screw 44, a threaded knob 45, a pulley 46, a connecting belt 47, a transmission gear 48, a drive gear 49, and a third drive motor 50. There are four sets of guide screws 44, which are evenly arranged on the second clamping assembly 10. The other end of each guide screw 44 passes through the position moving frame 39 and extends to the other side of the position moving frame 39. The threaded knob 45 is rotatably connected to the position moving frame 39 via a fourth bearing. On the surface of the frame 39, a threaded knob 45 is threaded onto the surface of the guide screw 44, a pulley 46 is fixedly connected to the end face of the threaded knob 45 and is movably sleeved on the surface of the guide screw 44, a connecting belt 47 is movably sleeved on the surface of the pulley 46, a transmission gear 48 is fixedly connected to the end face of a set of pulleys 46, a third drive motor 50 is fixedly connected to the surface of the position moving frame 39, and a drive gear 49 is fixedly connected to the output shaft end of the third drive motor 50. The drive gear 49 and the transmission gear 48 mesh with each other.

[0041] In practice, because the second aerospace structural component 11 needs to be adjusted, there is a certain distance between the second aerospace structural component 11 and the first aerospace structural component 5. After the position of the second aerospace structural component 11 is adjusted, the third drive motor 50 is started. The start of the third drive motor 50 will drive the drive gear 49 to rotate. The rotation of the drive gear 49 will drive the transmission gear 48 to rotate. The rotation of the transmission gear 48 will drive the pulley 46 at that position to rotate. The rotation of the pulley 46 at that position will drive the pulleys 46 at other positions to rotate through the connecting belt 47. In this way, the four pulleys 46 rotate synchronously to drive the threaded knob 45 to rotate synchronously. Under the synchronous rotation of the threaded knob 45, the guide screw 44 is driven to approach the first aerospace structural component 5. The movement of the guide screw 44 will drive the clamped second aerospace structural component 11 to be tightly attached to the surface of the second aerospace structural component 11 through the second clamping assembly 10. After the two come into contact, the welding operation can be performed.

[0042] refer to Figure 1-8 In this embodiment, the spacing control component 9 is provided with a second clamping assembly 10, on which a second aerospace structural component 11 is clamped and connected. The second clamping assembly 10 includes a fixed outer frame plate 51, an inner ring 52, a clamping through groove 53, a second clamping rod 54, a driving rod 55, a fourth drive motor 56, a third worm gear 57, a third worm wheel 58, and a connecting frame 59. The fixed outer frame plate 51 is fixedly connected to the end face of the guide screw 44. The inner ring 52 is disposed on the inner wall of the fixed outer frame plate 51. The clamping through groove 53 is formed on the surface of the inner ring 52, connecting the side surface of the inner ring 52 to the inner wall. One end of the second clamping rod 54 is rotatably connected to the inside of the clamping through groove 53 through a fixed shaft. One end of the driving rod 55 is connected to the second clamping rod 54. The side of the holding rod 54 is rotatably connected to the inner wall of the third worm wheel 58 at the other end of the driving rod 55. The third worm wheel 58 is rotatably sleeved on the outside of the inner ring 52. The connecting frame 59 is fixedly installed on the surface of the inner ring 52. The other end of the connecting frame 59 is fixedly connected to the surface of the fourth drive motor 56. The third worm 57 is fixedly connected to the output shaft end of the fourth drive motor 56. The third worm 57 and the third worm wheel 58 mesh with each other. There are four sets of clamping through slots 53. There are four sets of second clamping rods 54 and driving rods 55. The clamping through slots 53 are arranged in a ring array with the center of the inner ring 52 as the array center. The number and position of the second clamping rods 54 and driving rods 55 match the number and position of the clamping through slots 53.

[0043] In specific implementation, the fourth drive motor 56 is started, which drives the third worm gear 57 to rotate. The rotation of the third worm gear 57 drives the third worm wheel 58 to rotate. When the third worm wheel 58 rotates, it drives the driving rod 55 to move. The movement of the driving rod 55 will squeeze the second clamping rod 54. The second clamping rod 54 is squeezed and rotates around the fixed axis. The four sets of second clamping rods 54 rotate synchronously and fit against the surface of the second aerospace structural component 11, thereby realizing the clamping operation of the second aerospace structural component 11. It should be noted that the width of the second clamping rod 54 is relatively wide, which can improve the clamping stability of the second aerospace structural component 11.

[0044] refer to Figure 1-8 In this embodiment, a fifth drive motor 60 is also provided on the side of the fixed outer frame plate 51. A fourth worm gear 61 is rotatably connected to the side of the fixed outer frame plate 51 corresponding to the position of the fifth drive motor 60. The end face of the fourth worm gear 61 is fixedly connected to the output shaft of the fifth drive motor 60. A fourth worm wheel 62 is fixedly sleeved on the side of the inner ring 52 corresponding to the position of the fourth worm gear 61. The fourth worm wheel 62 and the fourth worm gear 61 mesh with each other.

[0045] In practice, when the fifth drive motor 60 starts, it drives the fourth worm gear 61 to rotate. The rotation of the fourth worm gear 61 drives the fourth worm wheel 62 to rotate. The rotation of the fourth worm wheel 62 drives the inner ring 52 and the components on the inner ring 52 to rotate synchronously, thereby realizing the rotation operation of the second aerospace structural component 11 in the clamping state.

[0046] refer to Figure 1-8 In this embodiment, the steps for using the aerospace structural component welding and fixing device are as follows:

[0047] S1. First, the first aerospace structural component 5 and the second aerospace structural component 11 are clamped and stabilized by the first clamping assembly 4 and the second clamping assembly 10.

[0048] S2. The position of the second aerospace structural component 11 in the clamping state is adjusted by the position adjustment component 8 and the drive component as needed. The adjustment of the position adjustment component 8 and the drive component is not in any particular order.

[0049] S3. After the orientation of the second aerospace structural component 11 is determined, the spacing control component 9 is controlled to move the second aerospace structural component 11 in the clamped state so that it fits tightly against the surface of the first aerospace structural component 5. Then the welding operation can be performed. It should be noted that if the position of the first aerospace structural component 5 deviates after adjustment, the clamping operation can be repeated. In this way, the final adjustment is made without having to repeat the clamping operation.

[0050] It should be noted that the clamping operation of the first aerospace structural component 5 and the second aerospace structural component 11 does not need to be performed first, and can be performed at any time according to the actual situation.

[0051] 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. A welding and fixing device for aerospace structural components, characterized in that, The chassis (1) is vertically fixed to a support frame (2) at its bottom. A mounting base (3) is provided on the top of the support frame (2). A first clamping assembly (4) is provided on the top of the mounting base (3). A first aerospace structural component (5) is clamped and connected to the first clamping assembly (4). The first clamping assembly (4) includes a first drive motor (12), a first worm gear (13), two sets of first positioning blocks (14), two sets of first rotating shafts (15), two sets of first worm wheels (16), two sets of first clamping rods (17), and two sets of clamping plates (18). The first drive motor (12) is fixedly installed inside the support frame (2). The output shaft of the first drive motor (12) extends to the mounting base (3) after passing through the mounting base (3). 3) The top of the first worm (13) is fixedly connected to the bottom of the first worm (13). Two sets of first positioning blocks (14) are fixedly connected to the top of the mounting base (3) with the first worm (13) as the axis of symmetry. Two sets of first positioning blocks (14) are movably sleeved on the surface of two sets of first rotating shafts (15) through two sets of second bearings. Two sets of first worm wheels (16) are fixedly sleeved on the surface of two sets of first rotating shafts (15). The first worm (13) meshes with the two sets of first worm wheels (16). Two sets of first clamping rods (17) are fixedly connected to the two ends of the first rotating shaft (15). Two sets of clamping plates (18) are set at the end of the first clamping rod (17) away from the rotating shaft. The first aerospace structural component (5) is clamped and connected through the two sets of clamping plates (18). The mounting base (3) is movably sleeved with a sliding frame (6), and an arc-shaped guide frame (7) is fixedly connected to the surface of the sliding frame (6). A position adjustment component (8) is slidably connected to the side of the arc-shaped guide frame (7). A spacing control component (9) is provided on the position adjustment component (8). The spacing control component (9) includes a guide screw (44), a threaded knob (45), a pulley (46), a connecting belt (47), a transmission gear (48), a drive gear (49), and a third drive motor (50). There are four sets of guide screws (44). The four sets of guide screws (44) are evenly arranged on the second clamping assembly (10). The other end of the guide screw (44) passes through the position moving frame (39) and extends to the position moving frame (3). On the other side of 9), the threaded knob (45) is rotatably connected to the surface of the position moving frame (39) through the fourth bearing. The threaded knob (45) is threaded onto the surface of the guide screw (44). The pulley (46) is fixedly connected to the end face of the threaded knob (45) and is movably connected to the surface of the guide screw (44). The connecting belt (47) is movably connected to the surface of the pulley (46). The transmission gear (48) is fixedly connected to the end face of a set of pulleys (46). The third drive motor (50) is fixedly connected to the surface of the position moving frame (39). The drive gear (49) is fixedly connected to the output shaft end of the third drive motor (50). The drive gear (49) and the transmission gear (48) mesh with each other. The spacing control component (9) is provided with a second clamping assembly (10), and a second aerospace structural component (11) is clamped and connected to the second clamping assembly (10).

2. The aerospace structural component welding and fixing device according to claim 1, characterized in that, The mounting base (3) is a circular base. The top and bottom of the mounting base (3) are provided with annular grooves (19) near the outermost position. The sliding frame (6) includes a stabilizing bracket (20), a tapered bearing (21), a fixing rod (22) and a fixing ring (23). The tapered bearing (21) is fixedly sleeved inside the annular groove (19) and on the side of the mounting base (3). The stabilizing bracket (20) is fixedly sleeved on the side of the tapered bearing (21). The fixing rod (22) is fixedly connected to the bottom of the stabilizing bracket (20). The fixing ring (23) is rotatably sleeved on the surface of the support frame (2) through the first bearing. The arc-shaped guide frame (7) is fixedly connected to the side of the fixing ring (23) and the bottom of the fixing rod (22) respectively. The top of the mounting base (3) is provided with an annular worm gear (24), and the top of the mounting base (3) is also provided with a drive assembly, which includes a sixth drive motor (25), a first transmission wheel (26), a second transmission wheel (27), a transmission belt (28) and a fifth worm (29). The top of the stabilizing card seat (20) is provided with a placement slot, and the fifth worm (29) is rotatably connected inside the placement slot. The first transmission wheel (26) is fixedly sleeved on the surface of the fifth worm (29). The sixth drive motor (25) is fixedly connected on the surface of the stabilizing card seat (20). The second transmission wheel (27) is fixedly connected to the output shaft end of the sixth drive motor (25). The transmission belt (28) is respectively sleeved on the surfaces of the first transmission wheel (26) and the second transmission wheel (27). The fifth worm (29) meshes with the annular worm gear (24).

3. The aerospace structural component welding and fixing device according to claim 2, characterized in that, A connecting assembly is provided between the clamping rod and the clamping plate (18). The connecting assembly includes a docking conical groove (30), a docking conical block (31), a docking square tube (32), a second positioning block (33), a side clamping plate (34), and a tension spring (35). The docking conical groove (30) is opened at the end of the first clamping rod (17) away from the first rotating shaft (15). The docking conical block (31) and the docking square tube (32) are both fixedly connected to the surface of the clamping plate (18). The docking conical block (31) is located inside the docking square tube (32). 31) The docking square tube (32) is movably connected inside the docking conical groove (30), and is movably sleeved on the end face of the first clamping rod (17). The second positioning block (33) is fixedly connected to the side of the docking square tube (32). The side clamping plate (34) is rotatably connected to the side of the first clamping rod (17) through the positioning shaft. One end of the tension spring (35) is fixedly connected to the side of the first clamping rod (17), and the other end of the tension spring (35) is fixedly connected to the inner side of the side clamping plate (34). One end of the side clamping rod is clamped to the surface of the second positioning block (33).

4. The aerospace structural component welding and fixing device according to claim 3, characterized in that, The arc-shaped guide frame (7) has toothed grooves (36) on its side, and arc-shaped grooves (37) are provided on both the outer and inner sides of the arc-shaped guide frame. The position adjustment component (8) includes a roller assembly (38), a position moving frame (39), a second drive motor (40), a second worm gear (41), a second rotating shaft (42), and a second worm wheel (43). The roller assembly (38) is tumblingly connected inside the arc-shaped groove (37), and the end face of the roller assembly (38) is fixed to the surface of the position moving frame (39). The second rotating shaft (42) is rotatably connected to the side of the position moving frame (39) through the third bearing. The second drive motor (40) is fixedly installed on the surface of the position moving frame (39). The second worm (41) is fixedly connected to the output shaft end of the second drive motor (40). The second worm wheel (43) is fixedly sleeved on the surface of the second rotating shaft (42). The second worm wheel (43) meshes with the second worm (41) and meshes with the tooth groove (36).

5. The aerospace structural component welding and fixing device according to claim 4, characterized in that, The second clamping assembly (10) includes a fixed outer frame plate (51), an inner ring (52), a clamping slot (53), a second clamping rod (54), a driving rod (55), a fourth drive motor (56), a third worm gear (57), a third worm wheel (58), and a connecting frame (59). The fixed outer frame plate (51) is fixedly connected to the end face of the guide screw (44). The inner ring (52) is set on the inner wall of the fixed outer frame plate (51). The clamping slot (53) is opened on the surface of the inner ring (52) to connect the side of the inner ring (52) and the inner wall. One end of the second clamping rod (54) is connected to the fixed shaft. The drive rod (55) is rotatably connected inside the clamping slot (53). One end of the drive rod (55) is rotatably connected to the side of the second clamping rod (54). The other end of the drive rod (55) is rotatably connected to the inner wall of the third worm wheel (58). The third worm wheel (58) is rotatably sleeved on the outside of the inner ring (52). The connecting frame (59) is fixedly installed on the surface of the inner ring (52). The other end of the connecting frame (59) is fixedly connected to the surface of the fourth drive motor (56). The third worm (57) is fixedly connected to the output shaft end of the fourth drive motor (56). The third worm (57) and the third worm wheel (58) mesh with each other.

6. The aerospace structural component welding and fixing device according to claim 5, characterized in that, The number of clamping slots (53) is four sets, the number of second clamping rods (54) and driving rods (55) is four sets, the clamping slots (53) are arranged in a ring array with the center of the inner circle (52) as the array center, and the number and position of the second clamping rods (54) and driving rods (55) match the number and position of the clamping slots (53).

7. The aerospace structural component welding and fixing device according to claim 6, characterized in that, The side of the fixed outer frame plate (51) is also provided with a fifth drive motor (60). The side of the fixed outer frame plate (51) is rotatably connected to the position of the fifth drive motor (60). The end face of the fourth worm (61) is fixedly connected to the output shaft of the fifth drive motor (60). The side of the inner ring (52) is fixedly sleeved with a fourth worm wheel (62) corresponding to the position of the fourth worm (61). The fourth worm wheel (62) and the fourth worm (61) mesh with each other.

8. A method for welding and fixing aerospace structural components according to any one of claims 1-7, characterized in that, The specific steps are as follows: S1. First, the first aerospace structural component (5) and the second aerospace structural component (11) are clamped and stabilized by the first clamping assembly (4) and the second clamping assembly (10); S2. The position of the second aerospace structural component (11) in the clamping state is adjusted by the position adjustment component (8) and the drive component as needed. The adjustment of the position adjustment component (8) and the drive component is not in any particular order. S3. After the orientation of the second aerospace structural component (11) is determined, the spacing control component (9) is controlled to move the second aerospace structural component (11) in the clamping state so that it fits tightly against the surface of the first aerospace structural component (5), and then welding is performed.

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