Aircraft fuselage skin self-adaptive riveting device

Abstract

The invention discloses an aircraft fuselage skin self-adaptive riveting device, and relates to the technical field of aircraft manufacturing, the aircraft fuselage skin self-adaptive riveting device comprises a riveting device and a frame, and the frame is provided with an adjusting mechanism and a positioning mechanism; the adjusting mechanism comprises a moving seat, a mounting block is fixedly arranged on the moving seat, and a moving groove is formed in the mounting block. When the riveting equipment moves downwards, the rolling wheels make contact with the fuselage skin first so as to improve the stability of the riveting equipment in the moving process, when the riveting equipment moves in an arc shape, the rolling wheels roll along the surface of the fuselage skin, and in the process, the rolling wheels can be adjusted in a self-adaptive mode according to the radian of the curved surface of the fuselage skin; and the mounting sleeve connected with the roller through the telescopic rod and the cylinder can gradually incline along the rolling direction of the roller, so that riveting equipment sleeved in the mounting sleeve can perform riveting operation on riveting holes in different curved surfaces on the fuselage skin, and the riveting efficiency of the fuselage skin of the airplane is greatly improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft manufacturing, in particular to a self-adaptive riveting device for aircraft fuselage skin. BACKGROUND

[0002] The aircraft fuselage skin riveting process is a key manufacturing process that connects the aircraft skin and the fuselage structure through rivets, and is widely used in the field of aviation manufacturing. Riveting is a method of connecting multiple workpieces using rivets. In aircraft fuselage skin riveting, the rivet is first inserted into the pre-made holes in the skin and the fuselage framework, and then the rivet end is hammered or extruded into a head using a rivet gun or other tool, which tightly connects the skin and the framework and achieves the fixing effect. In aircraft manufacturing and maintenance, riveting is more convenient. In manufacturing, multiple irregular-shaped skins need to be accurately cut and spliced, and riveting is easy to operate. In maintenance, the skin can be disassembled and installed by simply drilling out the rivet, while welding requires cutting equipment to cut the weld and re-weld, which is a tedious and time-consuming process.

[0003] The aircraft fuselage skin is a key structural component of the aircraft, and its connection quality directly affects the flight safety and performance of the aircraft. Currently, the riveting of the aircraft fuselage skin mainly relies on manual operation or traditional automated equipment. However, the aircraft fuselage skin often has a complex curved surface structure, and traditional automated equipment is difficult to adapt to the riveting needs of different curved surfaces, resulting in low riveting efficiency or substandard riveting quality. SUMMARY

[0004] In view of the deficiencies of the prior art, the present application provides a self-adaptive riveting device for aircraft fuselage skin.

[0005] To achieve the above-mentioned purpose, the present application provides the following technical solutions: The application discloses an aircraft fuselage skin self-adaptive riveting device which comprises a riveting device and a frame, and an adjusting mechanism and a positioning mechanism are arranged on the frame; the adjusting mechanism comprises a moving seat, the moving seat is fixedly provided with a mounting block, the mounting block is provided with a moving groove, and a moving block is slidably arranged in the moving groove; the positioning mechanism comprises a connecting plate fixedly arranged on one side of the moving block, a connecting rod fixedly connected to the bottom of the connecting plate, an installation sleeve arranged below the connecting plate, rotating shafts fixedly arranged at the two ends of the installation sleeve, and a connecting rod rotatably sleeved on the rotating shafts; a cylinder is fixedly arranged at the bottom of the installation sleeve, an expansion cavity is formed in the cylinder, a sliding block is slidably arranged in the expansion cavity, a spring fixedly connected to the expansion cavity is arranged on the sliding block, an expansion rod is fixedly connected to the bottom of the sliding block, the bottom of the expansion rod is slidably penetrated through the expansion cavity and extends below the cylinder, a sleeve shell is fixedly arranged at the bottom of the expansion rod, a roller is rotatably arranged in the sleeve shell, a fixing ring is sleeved on the cylinder, an electric cylinder is arranged at the bottom of the fixing ring, a pressing block is fixedly connected to the output rod of the electric cylinder, and an antiskid pad is attached to the bottom of the pressing block. When the riveting device moves downward, the rollers can first contact the fuselage skin to improve the stability of the riveting device during movement, and when the riveting device moves in an arc shape, the rollers roll along the surface of the fuselage skin; in this process, the rollers can be always closely attached to the surface of the fuselage skin under the elastic action of the roller springs; when the positions of the four rollers are different, the sliding block on the expansion rod can slide in the expansion cavity under the extrusion action, so that the rollers can be self-adaptively adjusted according to the curvature of the fuselage skin; the installation sleeve connected to the rollers through the expansion rod and the cylinder can gradually tilt along the rolling direction of the rollers, so that the riveting device sleeved in the installation sleeve can rivet the riveting holes on the different curved surfaces of the fuselage skin.

[0006] According to the above technical scheme, the moving seat is slidably connected to the frame, one side of the frame is provided with a tooth groove, an installation plate is fixedly connected to the moving seat, a first motor is mounted on the installation plate, an output shaft of the first motor is rotatably connected to the installation plate, a gear meshing with the tooth groove is fixedly sleeved on the output shaft of the first motor, the first motor is started to drive the gear to rotate, and the moving seat can move along the surface of the frame in an arc shape under the meshing action of the gear and the tooth groove, so that the riveting device can be riveted along the curved surface of the fuselage skin.

[0007] According to the above technical scheme, the frame is provided with a guide rail, and a guide block is fixedly mounted on the moving seat and slidably connected to the guide rail, so that the moving seat can stably move along the surface of the frame in an arc shape under the guidance of the guide rail and the guide block.

[0008] According to the technical scheme, further improvement lies in that a screw rod is rotatably arranged in the moving groove, the moving block is threadedly connected with the screw rod, a second motor connected with the screw rod is arranged on the mounting block, the screw rod is rotated by starting the second motor, the moving block threadedly connected with the screw rod can drive the riveting equipment to move downwards, and thus the spacing between the riveting equipment and the riveting holes on the fuselage skin can be adjusted.

[0009] According to the technical scheme, further improvement lies in that a limiting groove is arranged on the mounting block, a limiting block is fixedly arranged on the moving block, and the limiting block is slidably connected with the limiting groove, so that the moving block can be more stably moved in the moving groove under the limiting guidance of the limiting block and the limiting groove.

[0010] According to the technical scheme, further improvement lies in that a linear module is arranged at the bottom of the frame, and the frame is arranged on the sliding block of the linear module, the transverse position of the riveting equipment is adjusted by controlling the linear module, the riveting head of the riveting equipment can be accurately aligned with the riveting holes, and the riveting equipment can sequentially rivet the riveting holes arranged on the fuselage skin.

[0011] According to the technical scheme, further improvement lies in that a reinforcing rod fixedly connected with the moving block is arranged on the connecting plate, so that the connection between the connecting plate and the moving block is more stable.

[0012] According to the technical scheme, further improvement lies in that the riveting equipment is arranged in the mounting sleeve, a fixing sleeve is fixedly arranged on the riveting equipment, and a connecting sleeve is slidably arranged on the riveting equipment below the mounting sleeve, so that the riveting equipment has the function of quick disassembly, and the riveting equipment can be conveniently maintained.

[0013] According to the technical scheme, further improvement lies in that fixing holes are arranged on the mounting sleeve and the connecting sleeve, a nut is arranged on the fixing sleeve, a bolt is inserted into the fixing hole, and the bolt is threadedly connected with the nut through the fixing hole, the bolt on the connecting sleeve is removed and taken out of the fixing hole, then the connecting sleeve is taken off from the riveting equipment, and then the riveting equipment is taken out of the mounting sleeve, so that the riveting equipment can be quickly disassembled, and the convenience of disassembly operation of the riveting equipment is greatly improved.

[0014] Compared with the prior art, the present application has the following advantages: 1. The riveting device of the present application, when moving downward, the rollers will first contact the fuselage skin to improve the stability of the riveting device during movement, when the riveting device moves in an arc, the rollers roll along the surface of the fuselage skin, and during this process, the rollers can always adhere to the surface of the fuselage skin under the elastic action of the roller spring, when the positions of the four rollers are different, the sliding block on the telescopic rod can slide in the telescopic cavity under the extrusion action, so that the rollers can be self-adaptively adjusted according to the curvature of the fuselage skin, and the mounting sleeve connected with the rollers through the telescopic rod and the cylinder can gradually incline along the rolling direction of the rollers, so that the riveting device sleeved in the mounting sleeve can rivet the riveting holes on the different curved surfaces of the fuselage skin, thereby greatly improving the riveting efficiency of the fuselage skin.

[0015] 2. The riveting device of the present application, when moving downward, the rollers will first contact the fuselage skin to improve the stability of the riveting device during movement, when the riveting device moves in an arc, the rollers roll along the surface of the fuselage skin, and during this process, the rollers can always adhere to the surface of the fuselage skin under the elastic action of the roller spring, when the positions of the four rollers are different, the sliding block on the telescopic rod can slide in the telescopic cavity under the extrusion action, so that the rollers can be self-adaptively adjusted according to the curvature of the fuselage skin, and the mounting sleeve connected with the rollers through the telescopic rod and the cylinder can gradually incline along the rolling direction of the rollers, so that the riveting device sleeved in the mounting sleeve can rivet the riveting holes on the different curved surfaces of the fuselage skin, thereby greatly improving the riveting efficiency of the fuselage skin.

[0016] 3. The riveting device of the present application, when moving downward, the rollers will first contact the fuselage skin to improve the stability of the riveting device during movement, when the riveting device moves in an arc, the rollers roll along the surface of the fuselage skin, and during this process, the rollers can always adhere to the surface of the fuselage skin under the elastic action of the roller spring, when the positions of the four rollers are different, the sliding block on the telescopic rod can slide in the telescopic cavity under the extrusion action, so that the rollers can be self-adaptively adjusted according to the curvature of the fuselage skin, and the mounting sleeve connected with the rollers through the telescopic rod and the cylinder can gradually incline along the rolling direction of the rollers, so that the riveting device sleeved in the mounting sleeve can rivet the riveting holes on the different curved surfaces of the fuselage skin, thereby greatly improving the riveting efficiency of the fuselage skin. BRIEF DESCRIPTION OF DRAWINGS

[0017] The accompanying drawings are included to provide a further understanding of the present application, and constitute a part of the specification, illustrate the present application and are used to explain the present application, and do not constitute a limitation on the present application.

[0018] In the drawings: Figure 1 is a perspective structural schematic view of a fuselage skin self-adaptive riveting device in an embodiment of the present application; Figure 2 is a perspective structural schematic view of a frame in an embodiment of the present application; Figure 3 is a perspective structural schematic view of a moving seat in an embodiment of the present application; Figure 4Figure is a schematic view of the three-dimensional structure of the mounting block in the embodiment of the present application; Figure 5 Figure is a schematic view of the three-dimensional structure of the positioning mechanism in the embodiment of the present application; Figure 6 Figure is an exploded view of the structure of the mounting sleeve, the fixing sleeve and the connecting sleeve in the embodiment of the present application; Figure 7 Figure is a schematic view of the three-dimensional structure of the mounting sleeve in the embodiment of the present application; Figure 8 Figure is a schematic view of the sectional structure of the cylinder in the embodiment of the present application.

[0019] In the figure: 1, riveting equipment; 2, frame; 3, adjusting mechanism; 31, linear module; 32, tooth groove; 33, moving seat; 34, mounting plate; 35, first motor; 36, gear; 37, guide rail; 38, guide block; 39, mounting block; 310, moving groove; 311, screw rod; 312, second motor; 313, moving block; 314, limiting groove; 315, limiting block; 4, positioning mechanism; 41, connecting plate; 42, reinforcing rod; 43, mounting sleeve; 44, rotating shaft; 45, connecting rod; 46, fixing sleeve; 47, connecting sleeve; 48, fixing hole; 49, nut; 410, bolt; 411, cylinder; 412, telescopic rod; 413, casing; 414, roller; 415, telescopic cavity; 416, sliding block; 417, spring; 418, fixing ring; 419, electric cylinder; 420, pressing block; 421, non-slip pad. DETAILED DESCRIPTION

[0020] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0021] In order to better understand the above technical solutions, the above technical solutions will be described in detail below with reference to the drawings in the specification and the specific embodiments.

[0022] The utility model discloses a kind of aircraft fuselage skin self-adaptive riveting devices, which can improve the riveting efficiency of aircraft fuselage skin, and the utility model provides technical solutions: a kind of aircraft fuselage skin self-adaptive riveting device, including riveting equipment 1 and frame 2, frame 2 is provided with adjusting mechanism 3 and positioning mechanism 4.

[0023] Embodiment one In combination Figures 1-8 The utility model provides technical solutions: a kind of aircraft fuselage skin self-adaptive riveting device, including riveting equipment 1 and frame 2, frame 2 is provided with adjusting mechanism 3 and positioning mechanism 4.

[0024] Referring to Figures 2-5 Further, adjusting mechanism 3 includes moving seat 33, moving seat 33 is fixedly provided with mounting block 39, mounting block 39 is opened with moving groove 310, moving groove 310 is slidably provided with moving block 313;Moving seat 33 is slidably connected with frame 2, one side of frame 2 is opened with gear slot 32, mounting plate 34 is fixedly connected on moving seat 33, first motor 35 is installed on mounting plate 34, the output shaft of first motor 35 is rotatably connected with mounting plate 34, the output shaft of first motor 35 is fixedly sleeved with gear 36 engaged with gear slot 32, guide rail 37 is opened on frame 2, guide block 38 is fixedly installed on moving seat 33, guide block 38 is slidably connected with guide rail 37, screw rod 311 is rotatably arranged in moving groove 310, moving block 313 is threadedly connected with screw rod 311, second motor 312 connected with screw rod 311 is installed on mounting block 39, limiting slot 314 is opened on mounting block 39, limiting block 315 is fixedly arranged on moving block 313, limiting block 315 is slidably connected with limiting slot 314, linear module 31 is arranged on the bottom of frame 2, frame 2 is installed on the sliding block of linear module 31.

[0025] Specifically, by starting the first motor 35 to rotate the gear 36, under the meshing action of the gear 36 and the tooth groove 32, the moving seat 33 can be arcuately moved along the surface of the frame 2 under the guiding action of the guide rail 37 and the guide block 38, facilitating the riveting equipment 1 to rivet along the curved surface of the fuselage skin. By starting the second motor 312 to rotate the lead screw 311, the moving block 313 threaded with the lead screw 311 can be guided and limited by the limiting block 315 and the limiting groove 314 to move the riveting equipment 1 downward, thereby facilitating the adjustment of the distance between the riveting equipment 1 and the riveting hole on the fuselage skin. By controlling the linear module 31 to adjust the transverse position of the riveting equipment 1, the riveting head of the riveting equipment 1 can be accurately aligned with the riveting hole, and the riveting equipment 1 can rivet the riveting holes arranged on the fuselage skin in sequence.

[0026] Referring to Figures 5-8 Further, the positioning mechanism 4 includes a connecting plate 41 fixedly arranged on one side of the moving block 313, the bottom of the connecting plate 41 is fixedly connected with a connecting rod 45, a mounting sleeve 43 is arranged below the connecting plate 41, both ends of the mounting sleeve 43 are fixedly provided with a rotating shaft 44, and the connecting rod 45 is rotatably sleeved on the rotating shaft 44; a cylinder body 411 is fixedly arranged at the bottom of the mounting sleeve 43, an expansion cavity 415 is formed in the cylinder body 411, a sliding block 416 is slidably arranged in the expansion cavity 415, a spring 417 fixedly connected with the expansion cavity 415 is arranged on the sliding block 416, a telescopic rod 412 is fixedly connected with the bottom of the sliding block 416, the bottom of the telescopic rod 412 slidably penetrates through the expansion cavity 415 and extends below the cylinder body 411, a sleeve 413 is fixedly arranged at the bottom of the telescopic rod 412, a roller 414 is rotatably arranged in the sleeve 413, a fixed ring 418 is sleeved on the cylinder body 411, an electric cylinder 419 is mounted at the bottom of the fixed ring 418, a pressing block 420 is fixedly connected with the output rod of the electric cylinder 419, and an antiskid pad 421 is bonded to the bottom of the pressing block 420.

[0027] Specifically, when the riveting device 1 moves downward, the rollers 414 will first contact the fuselage skin to improve the stability of the riveting device 1 during movement, and when the riveting device 1 moves in an arc, the rollers 414 roll along the surface of the fuselage skin. During this process, the rollers 414 can always be in close contact with the surface of the fuselage skin under the elastic action of the springs 417. When the positions of the four rollers 414 are different, the sliding blocks 416 on the telescopic rods 412 can slide in the telescopic cavities 415 under the extrusion action, so that the rollers 414 can be self-adaptively adjusted according to the curvature of the fuselage skin. The mounting sleeve 43 connected with the rollers 414 through the telescopic rods 412 and the cylinder 411 can gradually tilt along the rolling direction of the rollers 414, so that the riveting device 1 sleeved in the mounting sleeve 43 can rivet the riveting holes on different curved surfaces of the fuselage skin, thereby greatly improving the riveting efficiency of the fuselage skin. When the riveting device 1 is riveting, the moving seat 33 is in a stationary state. At this time, the pressing blocks 420 are extruded in contact with the surface of the fuselage skin by starting the electric cylinder 419. The four groups of pressing blocks 420 can fix the tilt direction of the mounting sleeve 43 to prevent the riveting device 1 from deviating, so that the riveting device 1 can be stably positioned at this position. At the same time, the anti-skid pads 421 provided on the pressing blocks 420 can prevent the pressing blocks 420 from deviating and slipping off, ensuring the stability of the riveting device 1 during riveting operation.

[0028] Referring to Figure 6 Further, the connecting plate 41 is fixedly provided with a reinforcing rod 42 fixedly connected with the moving block 313. The riveting device 1 is sleeved in the mounting sleeve 43. The riveting device 1 is fixedly sleeved with a fixed sleeve 46. The riveting device 1 is slidingly sleeved with a connecting sleeve 47 below the mounting sleeve 43. The mounting sleeve 43 and the connecting sleeve 47 are both provided with fixed holes 48. The fixed sleeve 46 is provided with a nut 49. The fixed holes 48 are inserted with bolts 410. The bolts 410 are threadedly connected with the nut 49 through the fixed holes 48.

[0029] Specifically, by removing the bolts 410 on the connecting sleeve 47 and taking out the bolts 410 from the fixed holes 48, then taking off the connecting sleeve 47 from the riveting device 1, and then taking out the riveting device 1 from the mounting sleeve 43, the quick disassembly of the riveting device 1 can be completed, which is convenient for the maintenance of the riveting device 1.

[0030] In actual operation: the device is set in the designated position, and the aircraft fuselage skin to be processed is placed below the frame 2, the fuselage skin is pre-drilled and the rivets are inserted in the holes, the first motor 35 is started to rotate the gear 36, under the meshing action of the gear 36 and the tooth groove 32, the moving seat 33 can move along the surface of the frame 2 under the guidance of the guide rail 37 and the guide block 38, after the moving seat 33 is moved to the highest position of the frame 2, the second motor 312 is started to rotate the lead screw 311, so that the moving block 313 connected with the lead screw 311 can move downward under the limiting and guiding of the limiting block 315 and the limiting groove 314, so that the riveting equipment 1 can be located above the highest riveting hole on the fuselage skin, then the linear module 31 is controlled to adjust the transverse position of the riveting equipment 1, so that the riveting head of the riveting equipment 1 is accurately aligned with the riveting hole, then the riveting equipment 1 can pull the rivet in the riveting hole for riveting, and the riveting operation is completed, then the second motor 312 is controlled to reset the riveting equipment 1, and the first motor 35 is controlled to adjust the position of the riveting equipment 1, then the above operation is repeated, and the curved surface of the fuselage skin can be riveted, when the riveting operation of a row on the fuselage skin is completed, the linear module 31 is controlled to drive the riveting equipment 1 to the next row of riveting position for riveting operation; When the riveting equipment 1 moves downward, the rollers 414 at the bottom of the telescopic rod 412 will contact the fuselage skin first to improve the stability of the riveting equipment 1 during movement, when the riveting equipment 1 moves in an arc, the rollers 414 roll along the surface of the fuselage skin, and during this process, the rollers 414 can always be in close contact with the surface of the fuselage skin under the elastic action of the spring 417, when the positions of the four rollers 414 are different, the sliding block 416 on the telescopic rod 412 can slide in the telescopic cavity 415 under the extrusion action, so that the rollers 414 can be self-adaptively adjusted according to the curvature of the curved surface of the fuselage skin, and the mounting sleeve 43 connected with the rollers 414 through the telescopic rod 412 and the cylinder 411 can gradually incline along the rolling direction of the rollers 414, so that the riveting equipment 1 sleeved in the mounting sleeve 43 can rivet the riveting holes on different curved surfaces of the fuselage skin, when the riveting equipment 1 performs riveting operation, the moving seat 33 is in a stationary state, at this time, the electric cylinder 419 is started to make the pressing block 420 extrude and contact the surface of the fuselage skin, and the anti-skid pad 421 provided on the pressing block 420 can prevent the pressing block 420 from slipping and deviating, so as to ensure the stability of the riveting equipment 1 during riveting operation; By removing the bolts 410 from the connecting sleeve 47 and taking them out of the fixing holes 48, then taking the connecting sleeve 47 off the riveting equipment 1, and then taking the riveting equipment 1 out of the mounting sleeve 43, the quick disassembly of the riveting equipment 1 can be completed, which is convenient for the maintenance of the riveting equipment 1.

[0031] In the description of the application, it should be understood that the terms "center", "front", "back", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the scope of protection of the application.

[0032] The basic principles, main features and advantages of the present application are shown and described above. Those skilled in the art should understand that the present application is not limited by the above examples, and the above examples and descriptions in the specification are only to illustrate the principles of the present application. Without departing from the spirit and scope of the present application, various changes and improvements can be made to the present application, and these changes and improvements all fall within the scope of the claimed present application. The scope of protection of the present application is defined by the appended claims and their equivalents.

Claims

1. An aircraft fuselage skin adaptive riveting device, comprising a riveting device (1) and a frame (2), characterized in that: The frame (2) is provided with an adjustment mechanism (3) and a positioning mechanism (4); The adjustment mechanism (3) comprises a movable seat (33), a mounting block (39) is fixedly provided on the movable seat (33), a movable groove (310) is provided on the mounting block (39), and a movable block (313) is slidably provided in the movable groove (310); The positioning mechanism (4) includes a connecting plate (41) fixedly arranged on one side of the moving block (313), a connecting rod (45) fixedly connected to the bottom of the connecting plate (41), a mounting sleeve (43) provided below the connecting plate (41), rotating shafts (44) fixedly provided at both ends of the mounting sleeve (43), and the connecting rod (45) rotatably sleeved on the rotating shaft (44); The bottom of the mounting sleeve (43) is fixedly provided with a cylinder (411), a telescopic cavity (415) is provided in the cylinder (411), a sliding block (416) is slidably provided in the telescopic cavity (415), a spring (417) fixedly provided on the sliding block (416) and connected to the telescopic cavity (415), the bottom of the sliding block (416) is fixedly connected to a telescopic rod (412), the bottom of the telescopic rod (412) slides through the telescopic cavity (415) and extends The telescopic rod (412) extends to the bottom of the cylinder (411), and a sleeve (413) is fixedly provided at the bottom of the telescopic rod (412). A roller (414) is rotatably provided in the sleeve (413). A fixing ring (418) is sleeved on the cylinder (411), and an electric cylinder (419) is installed at the bottom of the fixing ring (418). A pressure block (420) is fixedly connected to the bottom of the output rod of the electric cylinder (419), and an anti-slip pad (421) is bonded to the bottom of the pressure block (420).

2. The aircraft fuselage skin adaptive riveting device according to claim 1, characterized in that: The movable seat (33) is slidably connected to the frame (2), a tooth groove (32) is provided on one side of the frame (2), a mounting plate (34) is fixedly connected to the movable seat (33), a first motor (35) is mounted on the mounting plate (34), an output shaft of the first motor (35) is rotatably connected to the mounting plate (34), and a gear (36) meshing with the tooth groove (32) is fixedly sleeved on the output shaft of the first motor (35).

3. The aircraft fuselage skin adaptive riveting device according to claim 2, characterized in that: A guide rail (37) is provided on the frame (2), a guide block (38) is fixedly mounted on the movable seat (33), and the guide block (38) is slidably connected to the guide rail (37).

4. The aircraft fuselage skin adaptive riveting device according to claim 2, characterized in that: A screw rod (311) is rotatably provided in the movable groove (310), the movable block (313) is threadedly connected to the screw rod (311), and a second motor (312) connected to the screw rod (311) is mounted on the mounting block (39).

5. The aircraft fuselage skin adaptive riveting device according to claim 4, characterized in that: A limiting groove (314) is provided on the installation block (39), a limiting block (315) is fixedly provided on the moving block (313), and the limiting block (315) is slidably connected to the limiting groove (314).

6. The aircraft fuselage skin adaptive riveting device according to claim 2, characterized in that: A linear module (31) is provided at the bottom of the frame (2), and the frame (2) is mounted on a slider of the linear module (31).

7. The aircraft fuselage skin adaptive riveting device according to claim 1, characterized in that: A reinforcing rod (42) fixedly connected to the moving block (313) is fixedly provided on the connecting plate (41).

8. The aircraft fuselage skin adaptive riveting device according to claim 1, characterized in that: The riveting device (1) is sleeved in the installation sleeve (43), a fixed sleeve (46) is fixedly sleeved on the riveting device (1), and a connecting sleeve (47) is slidably sleeved below the installation sleeve (43) on the riveting device (1).

9. The aircraft fuselage skin adaptive riveting device according to claim 8, characterized in that: The mounting sleeve (43) and the connecting sleeve (47) are both provided with fixing holes (48), a nut (49) is provided on the fixing sleeve (46), a bolt (410) is inserted into the fixing hole (48), and the bolt (410) passes through the fixing hole (48) and is threadedly connected to the nut (49).

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