Aircraft skin repairing structure and rapid repairing method based on self-piercing riveting technology

Abstract

The invention relates to the technical field of aircraft skin repairing, in particular to an aircraft skin repairing structure based on a self-piercing riveting technology, which comprises a base, an adjusting assembly is arranged on the base, a riveting assembly is arranged at the top of the adjusting assembly, a supporting assembly is arranged on one side of the riveting assembly, and a moving assembly is arranged at the bottom of the base. The adjusting assembly comprises a cavity formed in the base, a sliding plate is slidably connected into the cavity, and sliding rods are fixedly installed on the two sides of the top of the sliding plate. According to the aircraft skin repairing device, the adjusting assembly and the riveting assembly are arranged and matched with the stamping die and the female die, in the using process, the position of the aircraft skin repairing device can be conveniently adjusted and riveted according to the repairing requirement, and therefore the aircraft skin can be conveniently repaired, and the using convenience of the structure is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft skin repair, in particular to an aircraft skin repair structure and a rapid repair method based on a self-piercing riveting technology. Background Art

[0002] Aircraft skin is a layer of aluminum alloy or advanced lightweight material that gives it excellent aerodynamic properties. The function of aircraft skin is to maintain the shape of the aircraft and give it excellent aerodynamic properties. After the skin is subjected to aerodynamic forces, it transmits the force to the connected fuselage and wing frames. The force is complex, and the skin is in direct contact with the outside world. Therefore, the skin material is not only required to have high strength and good plasticity, but also to have a smooth surface and high corrosion resistance. After civil aircraft are put into operation, skin damage is a form of damage that aircraft often encounter on the route. If there is no corresponding rapid repair plan, the aircraft will be grounded for too long, and the cost caused by the aircraft being parked may be unacceptable to airlines and other operators.

[0003] At present, in the structural repair manuals of various aircraft models, the repair method for skin damage is mainly for damage with a smaller size, that is, fasteners are used to seal the damage removal holes. When the damage size is large, various structural repair manuals do not provide a quick temporary repair plan for removing large-sized damage. The existing patent, with the announcement number CN115924109A, discloses an aircraft skin repair structure and repair method. The structure requires opening holes in gaskets and reinforcement sheets, and the operation is cumbersome and time-consuming. In addition, although the repair method expands the range of repairable skin damage, the damaged area is still limited to a diameter of 25.4 mm. The screw caps on the outer surface of the skin after repair will also affect the aerodynamic characteristics of the aircraft. In actual application, it is not possible to quickly, conveniently and effectively handle skin damage of a wide range of sizes.

[0004] In view of this, the present invention proposes an aircraft skin repair structure and a rapid repair method based on self-piercing riveting technology to solve the above problems. Summary of the invention

[0005] In view of the shortcomings of the prior art, the purpose of the present invention is to propose an aircraft skin repair structure and a rapid repair method based on self-piercing riveting technology, which has the advantages of being able to quickly, conveniently and effectively handle skin damage in a wide range of sizes, and solves the problems raised in the above-mentioned background technology.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] The aircraft skin repair structure based on the self-piercing riveting technology comprises a base, an adjusting component is arranged on the base, a riveting component is arranged on the top of the adjusting component, a supporting component is arranged on one side of the riveting component, and a moving component is arranged at the bottom of the base.

[0008] The adjustment component includes a cavity opened inside the base, a skateboard is slidably connected inside the cavity, sliding rods are fixedly installed on both sides of the top of the skateboard, the top of the sliding rod passes through the base and extends to the outside of the base, a motor is fixedly installed at one end inside the cavity, a screw rod is fixedly installed on the output shaft of the motor, one end of the screw rod passes through the skateboard and extends to the outside of the skateboard, a moving plate is fixedly installed on the top of the sliding rod, an electric push rod is fixedly installed on the top of the moving plate, a shell is installed on the top of the electric push rod, and a telescopic rod is fixedly installed on one side of the inner wall of the shell.

[0009] The riveting assembly comprises a riveting machine fixedly mounted on one end of the telescopic rod, a positioning hole is opened on one side of the riveting machine, a push rod is inserted into the positioning hole, a punching die is fixedly mounted on one end of the push rod, and a concave die is arranged on one side of the punching die.

[0010] A reinforcement component is arranged between the stamping die and the concave die, and the reinforcement component comprises an aircraft skin, a gasket, a first reinforcement member, a second reinforcement member and a self-piercing rivet.

[0011] As an optimal technical solution, a thread hole is opened on the slide plate for the screw rod to pass through, the thread hole is threadedly connected to the screw rod, one end of the screw rod is sleeved with a sleeve rotatably connected to the screw rod, and one end of the sleeve is fixedly connected to one side of the inner wall of the cavity.

[0012] As a preferred technical solution, rod grooves for the sliding rod to pass through are provided on both sides of the upper surface of the base, and the inner walls of the rod grooves are slidably connected to the surface of the sliding rod.

[0013] As a preferred technical solution, sliding bars are fixedly installed on both sides of the bottom wall of the base cavity, and sliding grooves for the sliding bars to pass through are opened on both sides of the bottom of the slide plate. The inner wall of the sliding groove is slidably connected to the surface of the sliding bar.

[0014] As a preferred technical solution, the moving component includes positioning plates fixedly installed on both sides of the bottom of the base, support tubes are fixedly installed on both sides of the bottom of the positioning plates, a hydraulic rod is fixedly installed on the inner bottom wall of the support tube, a bracket is fixedly installed on the bottom of the hydraulic rod, and the interior of the bracket is rotatably connected to a roller through a rotating shaft.

[0015] As a preferred technical solution, a mounting ring is fixedly installed at the bottom of the support tube, a mounting hole is provided on the mounting ring, the mounting hole is an arc-shaped oblong hole, and anti-slip grooves are provided on the lower surface of the mounting ring.

[0016] As a preferred technical solution, a screw is inserted into the surface of the riveting machine, one end of which passes through the riveting machine and extends to the inside of the riveting machine to be threadedly connected to the surface of the push rod.

[0017] As a preferred technical solution, the supporting assembly includes an inclined rod fixedly installed at the bottom of the shell, a sliding plate fixedly installed at the bottom of the inclined rod, plug-in rods are inserted on both sides of the upper surface of the sliding plate, the bottom of the plug-in rod is plugged into the upper surface of the base, the top of the plug-in rod is fixedly connected through a pull plate, a spring sheet is fixedly installed at the bottom of the pull plate, and the bottom of the spring sheet is fixedly connected to the top of the sliding plate.

[0018] A rapid repair method for an aircraft skin repair structure based on self-piercing riveting technology comprises the following steps:

[0019] S1. Remove the damaged part in the aircraft skin;

[0020] S2. Provide a gasket of the same size as the damaged part to be removed, the gasket is used to replace the damaged part of the aircraft skin;

[0021] S3. Place the gasket between the stamping die and the die;

[0022] S4. Surface treatment of damaged parts of gaskets, stamping dies, dies and aircraft skins, including removal of oil stains and foreign particles;

[0023] S5. Riveting is performed by using a self-piercing riveting device, that is, the punch contacts the rivet cap of the self-piercing rivet and provides pressure, and the self-piercing rivet moves downward under the action of the punch, piercing the second reinforcement and the skin in turn, and piercing the first reinforcement, and finally, under the action of the die and the punch, the rivet legs expand to the surroundings to form a strong mechanical internal locking structure, thereby fixing the gasket, the first reinforcement and the second reinforcement to the damaged part of the aircraft skin with the help of the self-piercing rivet, wherein, after the riveting is completed, the rivet cap of the self-piercing rivet is approximately at the same height as the outer surface of the second reinforcement;

[0024] S6. Considering the actual situation, if the damaged area is large, an appropriate number of self-piercing rivets can be set in the gasket area for riveting. That is, the self-piercing rivets pierce the second reinforcement, the gasket, and the first reinforcement in turn. Finally, under the action of the die and the punch, the rivet legs expand to the surroundings to form a firm mechanical internal locking structure.

[0025] As a preferred technical solution, the method further comprises the following steps: before assembling the gasket, the first reinforcement and the second reinforcement to the damaged part of the aircraft skin, applying sealing glue to all overlapping mating surfaces.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] 1. The present invention provides an adjustment component and a riveting component, cooperates with a stamping die and a concave die, and during use, it is convenient to adjust the position and perform riveting operations according to the repair requirements, thereby facilitating the repair operation of the aircraft skin and improving the ease of use of the structure.

[0028] 2. The repair method adopted by the present invention can quickly, conveniently and effectively handle skin damage of a wide range of sizes, and can quickly respond to skin damage repairs including damage removal of larger sizes, reduce the downtime of aircraft in civil aviation and other fields, improve the maneuverability of aircraft, and thus reduce the economic impact caused by aircraft downtime. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0030] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0031] Figure 2 It is a schematic diagram of the three-dimensional cross-sectional structure of the present invention from a first viewing angle;

[0032] Figure 3 It is a schematic diagram of a three-dimensional cross-sectional structure of the present invention from a second viewing angle;

[0033] Figure 4 It is a schematic diagram of the three-dimensional cross-sectional structure of the present invention from a third viewing angle;

[0034] Figure 5 For the present invention Figure 1 A magnified schematic diagram of the structure at B in the middle;

[0035] Figure 6 This is an enlarged schematic diagram of the structure at A in the present invention 3;

[0036] Figure 7 It is a three-dimensional structural schematic diagram of the concave mold of the present invention;

[0037] Figure 8 It is a three-dimensional structural schematic diagram of the repair method in the first embodiment of the present invention;

[0038] Fig. 9 It is a schematic top view of the structure of the repair method in the first embodiment of the present invention;

[0039] Fig.10 It is a three-dimensional structural schematic diagram of the repair method in the second embodiment of the present invention.

[0040] In the figure: 1, base; 2, adjustment assembly; 200, slide plate; 201, slide bar; 202, motor; 203, screw rod; 204, shift plate; 205, electric push rod; 206, housing; 207, telescopic rod; 3, riveting assembly; 300, riveting machine; 301, push rod; 302, stamping die; 303, die; 304, screw rod; 305, raised rod; 4, moving assembly; 400, fixed Position plate; 401, support tube; 402, hydraulic rod; 403, bracket; 404, roller; 405, mounting ring; 5, support assembly; 500, diagonal rod; 501, sliding plate; 502, plug-in rod; 503, pull plate; 504, spring sheet; 6, reinforcement assembly; 600, aircraft skin; 601, gasket; 602, first reinforcement; 603, second reinforcement; 604, self-piercing rivet. DETAILED DESCRIPTION

[0041] In order to better understand the above technical solution, the above technical solution will be described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0042] Embodiment 1

[0043] According to the attached Figure 1-6 and Figure 8-9 As shown, an embodiment of the present invention provides an aircraft skin repair structure based on self-piercing riveting technology, including a base 1, an adjusting component 2 is arranged on the base 1, a riveting component 3 is arranged on the top of the adjusting component 2, a supporting component 5 is arranged on one side of the riveting component 3, and a moving component 4 is arranged at the bottom of the base 1.

[0044] The adjustment component 2 includes a cavity opened inside the base 1, and a slide plate 200 is slidably connected inside the cavity. Slide rods 201 are fixedly installed on both sides of the top of the slide plate 200. The top of the slide rod 201 passes through the base 1 and extends to the outside of the base 1. A motor 202 is fixedly installed at one end inside the cavity, and a screw rod 203 is fixedly installed on the output shaft of the motor 202. One end of the screw rod 203 passes through the slide plate 200 and extends to the outside of the slide plate 200. A moving plate 204 is fixedly installed on the top of the slide rod 201, and an electric push rod 205 is fixedly installed on the top of the moving plate 204. A shell 206 is installed on the top of the electric push rod 205, and a telescopic rod 207 is fixedly installed on one side of the inner wall of the shell 206.

[0045] The riveting assembly 3 includes a riveting machine 300 fixedly mounted on one end of the telescopic rod 207 . A positioning hole is provided on one side of the riveting machine 300 . A push rod 301 is inserted into the positioning hole. A stamping die 302 is fixedly mounted on one end of the push rod 301 . A concave die 303 is provided on one side of the stamping die 302 .

[0046] A reinforcement assembly 6 is arranged between the stamping die 302 and the concave die 303 . The reinforcement assembly 6 includes an aircraft skin 600 , a gasket 601 , a first reinforcement member 602 , a second reinforcement member 603 and a self-piercing rivet 604 .

[0047] By setting the adjustment component 2 and the riveting component 3, in cooperation with the stamping die 302 and the concave die 303, during use, it is convenient to adjust their positions and perform riveting operations according to the repair requirements, thereby facilitating the repair operation of the aircraft skin and improving the ease of use of the structure.

[0048] As a preferred technical solution, the slide plate 200 is provided with a threaded hole for the screw rod 203 to pass through, the threaded hole is threadedly connected to the screw rod 203, one end of the screw rod 203 is sleeved with a sleeve rotatably connected to the screw rod 203, and one end of the sleeve is fixedly connected to one side of the inner wall of the cavity.

[0049] As a preferred technical solution, rod grooves for the sliding rod 201 to pass through are provided on both sides of the upper surface of the base 1 , and the inner walls of the rod grooves are slidably connected to the surface of the sliding rod 201 .

[0050] As a preferred technical solution, sliding bars are fixedly installed on both sides of the bottom wall of the base 1 cavity, and sliding grooves for the sliding bars to pass through are opened on both sides of the bottom of the slide plate 200, and the inner wall of the sliding groove is slidably connected to the surface of the sliding bar.

[0051] As a preferred technical solution, the moving component 4 includes a positioning plate 400 fixedly installed on both sides of the bottom of the base 1, and support tubes 401 are fixedly installed on both sides of the bottom of the positioning plate 400. A hydraulic rod 402 is fixedly installed on the inner bottom wall of the support tube 401, and a bracket 403 is fixedly installed on the bottom of the hydraulic rod 402. The interior of the bracket 403 is rotatably connected to a roller 404 through a rotating shaft.

[0052] As a preferred technical solution, a mounting ring 405 is fixedly installed at the bottom of the support tube 401 , and a mounting hole is provided on the mounting ring 405 . The mounting hole is an arc-shaped oblong hole, and the lower surface of the mounting ring 405 is provided with anti-slip grooves.

[0053] As a preferred technical solution, a screw rod 304 is inserted into the surface of the riveting machine 300 , and one end of the screw rod 304 passes through the riveting machine 300 and extends to the inside of the riveting machine 300 to be threadedly connected to the surface of the push rod 301 .

[0054] As a preferred technical solution, the support assembly 5 includes an inclined rod 500 fixedly installed at the bottom of the shell 206, a sliding plate 501 is fixedly installed at the bottom of the inclined rod 500, plug-in rods 502 are inserted on both sides of the upper surface of the sliding plate 501, the bottom of the plug-in rod 502 is plugged into the upper surface of the base 1, the top of the plug-in rod 502 is fixedly connected through a pull plate 503, a spring sheet 504 is fixedly installed at the bottom of the pull plate 503, and the bottom of the spring sheet 504 is fixedly connected to the top of the sliding plate 501.

[0055] As a preferred technical solution, a protruding rod 305 is fixedly installed on one side of the die 303 .

[0056] A rapid repair method for an aircraft skin repair structure based on self-piercing riveting technology comprises the following steps:

[0057] S1. Remove the damaged part in the aircraft skin;

[0058] S2. Provide a gasket of the same size as the damaged part to be removed, the gasket is used to replace the damaged part of the aircraft skin;

[0059] S3. The gasket is placed between the stamping die 302 and the die 303;

[0060] S4. Surface treatment of the gasket, stamping die 302, die 303 and damaged parts of the aircraft skin, including removal of oil stains and impurity particles;

[0061] S5. The self-piercing riveting equipment is used for riveting, that is, the punch contacts the nail cap of the self-piercing rivet 604 and provides pressure. The self-piercing rivet 604 moves downward under the action of the punch, pierces the second reinforcement 603 and the skin 600 in turn, and pierces the first reinforcement 602. Finally, under the action of the die 303 and the punch, the rivet legs expand to the surroundings to form a strong mechanical internal locking structure, thereby fixing the gasket 601, the first reinforcement 602 and the second reinforcement 603 to the damaged part of the aircraft skin with the help of the self-piercing rivet 604. After the riveting is completed, the nail cap of the self-piercing rivet 604 is approximately at the same height as the outer surface of the second reinforcement 603;

[0062] S6. Considering the actual situation, if the damaged area is large, an appropriate number of self-piercing rivets can be set in the gasket area for riveting. That is, the self-piercing rivets 604 pierce the second reinforcement 603 and the gasket 601 in turn, and then penetrate into the first reinforcement 602. Finally, under the action of the die 303 and the punch, the rivet legs expand to the surroundings to form a firm mechanical internal locking structure.

[0063] As a preferred technical solution, the method further includes the following steps: before assembling the gasket 601 , the first reinforcement 602 and the second reinforcement 603 to the damaged part of the aircraft skin 600 , applying sealing glue to all overlapping mating surfaces.

[0064] It is worth noting that the use of this repair method can quickly, conveniently and effectively handle skin damage of a wide range of sizes, and can quickly respond to skin damage repairs including damage removal of larger sizes, reduce the downtime of aircraft in civil aviation and other fields, improve the maneuverability of aircraft, and thereby reduce the economic impact caused by aircraft downtime.

[0065] Embodiment 2

[0066] According to the attached Figure 7 and Fig.10 As shown, an embodiment of the present invention provides an aircraft skin repair structure based on self-piercing riveting technology, and the riveting assembly 3 includes a riveting machine 300 fixedly mounted on one end of the telescopic rod 207, a positioning hole is provided on one side of the riveting machine 300, a push rod 301 is inserted into the positioning hole, a stamping die 302 is fixedly mounted on one end of the push rod 301, a die 303 is provided on one side of the stamping die 302, and a protruding rod 305 is fixedly mounted on one side of the die 303.

[0067] The reinforcement assembly 6 disposed between the stamping die 302 and the concave die 303 includes an aircraft skin 600 , a gasket 601 , a first reinforcement member 602 and a self-piercing rivet 604 .

[0068] It is worth noting that another repair method may include the following steps: under the action of the die 303 and the protruding rod 305, the rivet legs expand to the surroundings to form a strong mechanical inner locking structure. That is, the self-piercing rivet 604 moves downward under the action of the punch, pierces the gasket, and penetrates the first reinforcement 602, and finally, under the action of the die 303, the protruding rod 305 and the punch, the rivet legs expand to the surroundings to form a strong mechanical inner locking structure; at the same time, the self-piercing rivet 604 moves downward under the action of the punch, pierces the skin, and penetrates the first reinforcement 602, and finally, under the action of the die 303 and the punch, the rivet legs expand to the surroundings to form a strong mechanical inner locking structure. In this way, the gasket 601 and the first reinforcement 602 are fixed to the damaged part of the aircraft skin 600 with the help of the self-piercing rivet 604, wherein, after the riveting is completed, the nail head of the self-piercing rivet 604 is approximately at the same height as the outer surface of the aircraft skin 600 and the outer surface of the gasket 601.

[0069] Before assembling the gasket 601 and the first reinforcement 602 to the damaged part of the aircraft skin 600, sealing glue is applied to all overlapping mating surfaces to ensure the stability of the contact between the gasket 601 and the corresponding surfaces of the reinforcement and the skin surface, increase the connection strength and obtain the desired sealing effect, and prevent the occurrence of damage such as corrosion.

[0070] The aircraft skin repair structure according to the present invention may include but is not limited to the following beneficial technical effects:

[0071] The aircraft skin repair structure can be used for temporary or semi-permanent repair of skin damage in a wide range of sizes and in areas where the skin thickness does not exceed 3 mm. The entire repair process is simple to operate and easy to implement.

[0072] The aircraft skin repair structure does not require pre-punching of gaskets and reinforcements, and the operation process is simple and no waste is generated.

[0073] In the aircraft skin repair structure, the self-piercing rivets pierce from the outside of the skin to the inside, and the rivet heads are flush with the outer surface of the first layer of plate, which maximizes the aerodynamic shape of the skin after repair.

[0074] The aircraft skin repair structure of the present invention is urgent both from a technical perspective and from an operating cost perspective.

[0075] The aircraft skin repair structure overcomes the shortcomings of the existing technology and is easy to operate. It can effectively reduce aircraft downtime, improve aircraft maneuverability, and minimize the operating costs of airlines and other related units.

[0076] The layering order of gaskets and reinforcements, the number of reinforcements, the insertion direction of self-piercing rivets, the arrangement path and number of rivets in the repair structure proposed by the present invention are only illustrative and cannot be used as a limitation to the present invention.

[0077] When the aircraft skin repair structure and rapid repair method based on the self-piercing riveting technology of the present invention are used, the motor 202 is controlled to work, and then the motor 202 drives the screw rod 203 to rotate, and the screw rod 203 at this time drives the slide bar 201 on the slide plate 200 to move, so as to adjust the position of the electric push rod 205 on the shift plate 204, so as to facilitate the position adjustment of the riveting assembly 3, so as to facilitate the adjustment of the distance between the reinforcement and the gasket, and at the same time control the electric push rod 205 and the telescopic rod 207 to work, so as to facilitate the adjustment operation, and then the damaged part in the aircraft skin is cut off, and a gasket with the same size as the removed damaged part is provided, and the gasket is used to replace the damaged part of the aircraft skin, and the gasket is placed between the stamping die 302 and the concave die 303, and the gasket, the stamping die 302, the concave die 303 and the damaged part of the aircraft skin are surface treated, including the removal of oil stains and impurity particles, and riveted by using self-piercing riveting equipment, that is, the punch contacts the nail cap of the self-piercing rivet and provides pressure, and the self-piercing rivet is formed at the punch. , and penetrates the second reinforcement 603 and the skin in turn, and penetrates the first reinforcement 602. Finally, under the action of the die 303 and the punch, the rivet legs expand to the surroundings to form a strong mechanical inner locking structure, so that the gasket and the reinforcement are fixed to the damaged part of the aircraft skin with the help of self-piercing rivets. After the riveting is completed, the nail cap of the self-piercing rivet is approximately at the same height as the outer surface of the reinforcement. Considering the actual situation, if the damaged area is large, an appropriate number of self-piercing rivets can be arranged in the gasket area for riveting forming, that is, the self-piercing rivets penetrate the reinforcement and the gasket in turn, and penetrate into the reinforcement. Finally, under the action of the die 303 and the punch, the rivet legs expand to the surroundings to form a strong mechanical inner locking structure. The layering order of the gasket and the reinforcement, the number of reinforcements, the penetration direction of the self-piercing rivets, the arrangement path and number of the rivets in the repair structure proposed by the present invention are only schematic, and cannot be used as a limitation to the present invention. Both the flat bottom die and the convex bottom die can be used for 3-layer and 2-layer skin repair structures.

[0078] The basic principles, main features and advantages of the present invention are described above in conjunction with specific embodiments. Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and descriptions are only preferred examples of the present invention and are not intended to limit the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. An aircraft skin repair structure based on self-piercing riveting technology, comprising a base (1), characterized in that: The base (1) is provided with an adjustment component (2), a riveting component (3) is provided on the top of the adjustment component (2), a supporting component (5) is provided on one side of the riveting component (3), and a moving component (4) is provided at the bottom of the base (1); The adjustment component (2) comprises a cavity opened inside the base (1), a slide plate (200) is slidably connected inside the cavity, slide bars (201) are fixedly installed on both sides of the top of the slide plate (200), the top of the slide bar (201) passes through the base (1) and extends to the outside of the base (1), a motor (202) is fixedly installed on one end of the cavity, a screw rod (203) is fixedly installed on the output shaft of the motor (202), one end of the screw rod (203) passes through the slide plate (200) and extends to the outside of the slide plate (200), a moving plate (204) is fixedly installed on the top of the slide bar (201), an electric push rod (205) is fixedly installed on the top of the moving plate (204), a shell (206) is installed on the top of the electric push rod (205), and a telescopic rod (207) is fixedly installed on one side of the inner wall of the shell (206); The riveting assembly (3) comprises a riveting machine (300) fixedly mounted on one end of the telescopic rod (207); a positioning hole is provided on one side of the riveting machine (300); a push rod (301) is inserted into the positioning hole; a punching die (302) is fixedly mounted on one end of the push rod (301); and a concave die (303) is provided on one side of the punching die (302); A reinforcement assembly (6) is arranged between the stamping die (302) and the concave die (303), and the reinforcement assembly (6) comprises an aircraft skin (600), a gasket (601), a first reinforcement member (602), a second reinforcement member (603) and a self-piercing rivet (604).

2. The aircraft skin repair structure based on self-piercing riveting technology according to claim 1 is characterized in that: The slide plate (200) is provided with a threaded hole for the screw rod (203) to pass through, the threaded hole is threadedly connected to the screw rod (203), one end of the screw rod (203) is sleeved with a sleeve rotatably connected to the screw rod (203), and one end of the sleeve is fixedly connected to one side of the inner wall of the cavity.

3. The aircraft skin repair structure based on self-piercing riveting technology according to claim 1 is characterized in that: Rod grooves for the sliding rod (201) to pass through are provided on both sides of the upper surface of the base (1), and the inner walls of the rod grooves are slidably connected to the surface of the sliding rod (201).

4. The aircraft skin repair structure based on self-piercing riveting technology according to claim 1 is characterized in that: Sliding bars are fixedly mounted on both sides of the bottom wall of the base (1) cavity, and sliding grooves for the sliding bars to pass through are provided on both sides of the bottom of the slide plate (200), and the inner wall of the sliding groove is slidably connected to the surface of the sliding bar.

5. The aircraft skin repair structure based on self-piercing riveting technology according to claim 1 is characterized in that: The moving assembly (4) comprises a positioning plate (400) fixedly mounted on both sides of the bottom of the base (1); support tubes (401) are fixedly mounted on both sides of the bottom of the positioning plate (400); a hydraulic rod (402) is fixedly mounted on the inner bottom wall of the support tube (401); a bracket (403) is fixedly mounted on the bottom of the hydraulic rod (402); and a roller (404) is rotatably connected to the inside of the bracket (403) via a rotating shaft.

6. The aircraft skin repair structure based on self-piercing riveting technology according to claim 5 is characterized in that: A mounting ring (405) is fixedly mounted on the bottom of the support tube (401), a mounting hole is provided on the mounting ring (405), the mounting hole is an arc-shaped oblong hole, and anti-slip grooves are provided on the lower surface of the mounting ring (405).

7. The aircraft skin repair structure based on self-piercing riveting technology according to claim 1 is characterized in that: A screw rod (304) is inserted into the surface of the riveting machine (300), and one end of the screw rod (304) penetrates the riveting machine (300) and extends to the inside of the riveting machine (300) to be threadedly connected to the surface of the push rod (301).

8. The aircraft skin repair structure based on self-piercing riveting technology according to claim 1 is characterized in that: The support assembly (5) comprises an inclined rod (500) fixedly mounted on the bottom of the housing (206); a sliding plate (501) is fixedly mounted on the bottom of the inclined rod (500); plug-in rods (502) are inserted on both sides of the upper surface of the sliding plate (501); the bottom of the plug-in rod (502) is plugged into the upper surface of the base (1); the top of the plug-in rod (502) is fixedly connected via a pull plate (503); a spring sheet (504) is fixedly mounted on the bottom of the pull plate (503); and the bottom of the spring sheet (504) is fixedly connected to the top of the sliding plate (501).

9. The aircraft skin repair structure based on self-piercing riveting technology according to claim 1 is characterized in that: A protruding rod (305) is fixedly mounted on one side of the female mold (303).

10. The rapid repair method for aircraft skin repair structure based on self-piercing riveting technology according to any one of claims 1 to 9, comprising the following steps: S1. Remove the damaged part in the aircraft skin; S2. Provide a gasket of the same size as the damaged part to be removed, the gasket is used to replace the damaged part of the aircraft skin; S3. Placing the gasket between the stamping die (302) and the die (303); S4. Surface treatment of the gasket, the stamping die (302), the die (303) and the damaged parts of the aircraft skin, including removal of oil stains and foreign particles; S5. The self-piercing riveting equipment is used for riveting, that is, the punch contacts the nail cap of the self-piercing rivet (604) and provides pressure. The self-piercing rivet (604) moves downward under the action of the punch, pierces the second reinforcement (603) and the skin (600) in turn, and pierces the first reinforcement (602). Finally, under the action of the die (303) and the punch, the rivet legs expand to the surroundings to form a strong mechanical internal locking structure, thereby fixing the gasket (601), the first reinforcement (602) and the second reinforcement (603) to the damaged part of the aircraft skin with the help of the self-piercing rivet (604), wherein: After riveting is completed, the rivet head of the self-piercing rivet (604) is approximately at the same height as the outer surface of the second reinforcement member (603); S6. Considering the actual situation, if the damaged area is large, an appropriate number of self-piercing rivets can be arranged in the gasket area for riveting, that is, the self-piercing rivets (604) pierce the second reinforcement (603), the gasket (601) in sequence, and penetrate into the first reinforcement (602), and finally, under the action of the die (303) and the punch, the rivet legs expand to the surroundings to form a strong mechanical internal locking structure; The method further comprises the following steps: before assembling the gasket (601), the first reinforcement (602) and the second reinforcement (603) to the damaged part of the aircraft skin (600), applying sealing glue to all overlapping mating surfaces.

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