Riveting device for assembling aviation thin-walled parts

Abstract

The invention discloses a riveting device, particularly discloses a riveting device for assembling aviation thin-walled parts, and belongs to the technical field of design and manufacturing of aviation thin-walled part assembling process equipment. The riveting device for assembling the aviation thin-walled parts can effectively guarantee the riveting quality of two or more connected thin-walled parts. The riveting device comprises a rack, a riveting system and a part fixing mechanism. The riveting system is movably arranged on the rack. In the assembling process of the aviation thin-walled parts, two or more aviation thin-walled parts needing to be riveted are fixed through the part fixing mechanism and are riveted into a whole under the cooperation of the riveting system.

Description

Technical Field

[0001] The invention relates to a riveting device, in particular to a riveting device used for assembling aviation thin-wall parts, and belongs to the technical field of design and manufacturing of aviation thin-wall part assembly process equipment. Background Art

[0002] No matter what type of aircraft, there will be a large number of thin-walled parts, which are generally used to fix cables, harnesses, oil pipes, air pipes or other non-metallic parts. Thin-walled parts are more widely used in civil aircraft than in military aircraft. Since the structural assembly of the aircraft is basically a one-time assembly, the structure will not be disassembled later, so most of them are riveted. However, due to the low strength of thin-walled parts, which may even be lower than the strength of rivets, the problem of part deformation often occurs during the riveting process. There will be problems such as part warping and arching in the middle, which will cause the thin-walled parts to not fit with other parts, resulting in the problem of excessive matching clearance. The only way to solve the problem of parts not fitting and excessive clearance is to remove the rivets. Since rivets are one-time fasteners, the rivets can only be removed by drilling them out with a drill bit, which requires extremely high drilling skills of the operator, because once deflection occurs, the hole diameter will be excessive, resulting in the scrapping of the parts. In order to solve the problem of poor fit and excessive clearance in riveting of thin-walled parts, the technicians summarized the causes of deformation and feasible solutions, which are summarized as follows:

[0003] 1. Causes of deformation

[0004] Excessive riveting force: Excessive pressure applied during the riveting process may cause thin parts to deform or tear.

[0005] Thermal effects: The heat generated during the riveting process may cause thermal expansion of thin materials, resulting in deformation.

[0006] Difference in material hardness: Differences in hardness of different materials may lead to local stress concentration during riveting, which in turn causes deformation.

[0007] Improper rivet selection: Selecting the wrong rivet type or size may cause excessive local stress on thin parts.

[0008] Assembly accuracy issues: Insufficient alignment or assembly accuracy of parts before riveting may cause deformation of parts during the riveting process.

[0009] 2. Existing technologies and solutions

[0010] Control the riveting force: Use precise riveting equipment and techniques to ensure that the force applied is within the appropriate range to reduce the impact on thin parts.

[0011] Optimize heat treatment process: Use appropriate heat treatment process to control the heat generated during riveting and avoid deformation caused by thermal expansion.

[0012] Choose the right material and rivet: Choose the right rivet and material according to the thickness and material properties of the parts to reduce stress concentration.

[0013] Improve assembly accuracy: Through precise assembly processes and equipment, ensure the alignment accuracy of parts before riveting and reduce the risk of deformation.

[0014] Use shims or supports: Use shims or supports to stabilize thin parts during the riveting process to prevent deformation.

[0015] Pretreatment and post-treatment: Pretreatment and post-treatment processes are performed on thin parts, such as surface treatment, reinforcement, etc., to enhance their deformation resistance.

[0016] Cold riveting technology: Use cold riveting technology (such as cold pressure riveting) to reduce the impact of thermal effects on thin parts.

[0017] The above measures can effectively reduce the risk of deformation of thin parts during the riveting process, thereby improving the accuracy and quality of the aircraft manufacturing process. Of course, the above existing technologies cannot be applied to aircraft assembly, because the rivet materials, specifications, and heat treatment processes for aircraft assembly are determined by the design department and controlled by the process department, and cannot be changed at will during the assembly stage. Therefore, in order to solve this technical problem, the best way is to improve the riveting device and process.

[0018] 3. Disadvantages of the Existing Technology

[0019] The existing riveting of thin-walled parts is carried out one by one in sequence. However, after the first rivet is completed, the thin-walled part will bend upward around the riveted point, producing a certain curvature, causing a misfit between the thin-walled part and the other riveted part. During subsequent riveting, there may be stress assembly problems, or the riveting cannot be completed effectively due to excessive gaps. As a result, the riveting of thin-walled parts has become a problem that is often encountered in aircraft parts assembly and has not been effectively solved. It usually relies on technicians with high riveting skills to complete it. Summary of the invention

[0020] The technical problem to be solved by the present invention is to provide a riveting device for assembling aviation thin-walled parts, which can effectively ensure the riveting quality of two or more connected thin-walled parts.

[0021] The technical solution adopted to solve the above technical problems is as follows: A riveting device for assembling thin-walled aircraft parts, the riveting device includes a frame, a riveting system and a part fixing mechanism, and the riveting system is movably arranged on the frame; during the assembly process of thin-walled aircraft parts, two or more thin-walled aircraft parts to be riveted are fixed by the part fixing mechanism and riveted into a whole under the cooperation of the riveting system.

[0022] Further, the frame is a U-shaped truss, and the riveting system is movably fixed on the U-shaped truss through the two horizontal edges above and below the U-shaped truss. Two or more thin-walled aircraft parts fixed under the control of the part fixing mechanism are riveted into a whole through the cooperation of the riveting system and the U-shaped truss.

[0023] The preferred mode of the above solution is that the part fixing mechanism includes a part support platform and a pressing and fixing component. A part arrangement groove is provided on the part support platform, and the pressing and fixing component is movably arranged on the part support platform outside the part arrangement groove. Top pressing structures adapted to the riveting pressure output end of the riveting system are respectively provided on the part support platform and the pressing and fixing component; two or more thin-walled aircraft parts to be riveted are detachably fixed in the part arrangement groove through the pressing and fixing component, and each thin-walled aircraft part to be riveted is riveted into a whole under the cooperation of the top pressing structure and the power output of the riveting pressure output end of the riveting system.

[0024] Further, the part support platform is composed of a high-strength steel plate, the part arrangement groove is arranged on the top surface of the high-strength steel plate, the pressing and fixing component includes a pressing plate and a quick-release connection structure, the top pressing structure includes a riveting tightening blind hole arranged on the bottom surface of the high-strength steel plate and a riveting punching avoidance hole arranged on the pressing plate, and each thin-walled aircraft part to be riveted is detachably pressed and fixed in the part arrangement groove through the pressing plate under the cooperation of the quick-release connection structure; the riveting pressure output end of the riveting system inputs punching power to the rivets inserted into the riveting holes of each thin-walled aircraft part under the cooperation of the riveting tightening blind hole and the riveting punching avoidance hole.

[0025] The preferred mode of the above solution is that the pressing plate includes a pressing plate body and a pressing block, the pressing block is arranged overlapping on the pressing surface of the pressing plate body, the quick-release connection structure includes a hinged support and a quick-release connection support, the hinged support and the quick-release connection support are respectively arranged on the high-strength steel plates on both sides of the part arrangement groove in a position-adapted manner, the fixed end of the pressing plate body is hingedly connected to the hinged support, and the movable end of the pressing plate body is detachably movably connected to the quick-release connection support; at least a riveting punching avoidance hole is provided on the pressing plate body.

[0026] Furthermore, the quick-release connecting support includes two support bodies, two regulators, and two locking beads. Locking bead locking grooves are respectively arranged at corresponding positions on both sides of the pressing plate body. The two locking beads are respectively arranged at corresponding positions of the two support bodies in an axially telescopic manner through the two regulators. Each support body is arranged on the high-strength steel plate on one side of the part arrangement groove in a mutually adapted manner; during the pressing process of the aviation thin-walled part, the pressing plate body is locked on the two support bodies through the cooperation of the locking beads and the locking bead locking grooves with the support bodies and the regulators.

[0027] The preferred embodiment of the above solution is that the riveting system includes a lower top support riveting assembly and an upper stamping riveting assembly. The lower top support riveting assembly is movably arranged on the lower horizontal side of the C-shaped truss, and the upper stamping riveting assembly is movably arranged on the upper horizontal side of the C-shaped truss; each aviation thin-walled part fixed on the part fixing mechanism is riveted into a whole through the top iron rod of the lower top support riveting assembly and the stamping rod of the upper stamping riveting assembly under the cooperation of the input power of the lower top support riveting assembly and the upper stamping riveting assembly.

[0028] Furthermore, the lower top support riveting assembly further includes a second telescopic driver, a second driving rod, an anti-tilting mechanism, and a lower riveting head. The second telescopic driver is fixedly installed on the lower horizontal side of the C-shaped truss through the second driving rod. The top iron rod is fixedly installed on the anti-tilting mechanism through the lower riveting head, and the anti-tilting mechanism is movably arranged on the second driving rod.

[0029] The preferred embodiment of the above solution is that the upper stamping riveting assembly further includes a first telescopic driver, a first driving rod, and an upper riveting head. The first telescopic driver is fixedly installed on the upper horizontal side of the C-shaped truss through the first driving rod. The stamping rod is movably fixedly installed on the first driving rod through the upper riveting head.

[0030] Furthermore, the anti-tilting mechanism includes an anti-tilting frame and a telescopic rod. The lower riveting head is fixedly installed on the anti-tilting frame, and the anti-tilting frame is fixedly installed on the second driving rod. At least one telescopic rod is respectively arranged between the anti-tilting frame on both sides of the second driving rod and the lower horizontal side; the upper stamping riveting assembly further includes an L-shaped support and stabilizer frame. One end of the first driving rod connected to the upper riveting head is fixedly connected to the upper middle part of the vertical side of the C-shaped truss through the L-shaped support and stabilizer frame; at least four groups of connecting and mounting holes are further arranged on the vertical side of the C-shaped truss; and reinforcing rib plates are respectively arranged between the vertical side and the lower horizontal side of the C-shaped truss and inside the L-shaped support and stabilizer frame.

[0031] The beneficial effects of the present invention are as follows: the technical solution provided by the present application is to set up a riveting device including a frame, a riveting system and a part fixing mechanism, and then movably arrange the riveting system on the frame; and in the assembly process of aviation thin-walled parts, two or more aviation thin-walled parts that need to be riveted are fixed by the part fixing mechanism, and are riveted into a whole with the cooperation of the riveting system. In this way, since the present application first fixes the two or more thin-walled parts that need to be assembled by riveting them through the part fixing mechanism, and then rivets them, it can effectively ensure that the two or more connected thin-walled parts are always in a fitted state from the beginning of riveting the first rivet to the completion of riveting, avoiding the occurrence of loose fitting, thereby achieving the purpose of effectively ensuring the riveting quality of the two or more connected thin-walled parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic diagram of the three-dimensional structure of the front side of the riveting device used for assembling aviation thin-walled parts of the present invention;

[0033] Figure 2 It is a front view of the riveting device used for assembling aviation thin-wall parts of the present invention;

[0034] Figure 3 for Figure 2 Side view of

[0035] Figure 4 for Figure 3 AA section view;

[0036] Figure 5 It is a three-dimensional structural schematic diagram of the rear side of the riveting device used for assembling aviation thin-walled parts of the present invention;

[0037] Figure 6 It is a three-dimensional structural schematic diagram of a part fixing mechanism involved in the riveting device for assembling aviation thin-walled parts of the present invention;

[0038] Figure 7 A top view of a part fixing mechanism involved in a riveting device for assembling aviation thin-walled parts according to the present invention;

[0039] Figure 8 for Figure 7 Side view of

[0040] Fig. 9 It is a schematic diagram of the three-dimensional structure in another direction of the part fixing mechanism involved in the riveting device for assembling aviation thin-walled parts of the present invention.

[0041] The markings in the figure are: horizontal edge 1, part support platform 2, part layout groove 3, riveting tightening blind hole 4, riveting stamping avoidance hole 5, pressure plate body 6, pressure block 7, hinged support 8, support body 9, regulator 10, locking bead 11, bead locking groove 12, top iron rod 13, stamping rod 14, second telescopic driver 15, second driving rod 16, lower riveting head 17, first telescopic driver 18, first driving rod 19, upper riveting head 20, anti-tilting frame 21, telescopic rod 22, ∟-shaped support and stabilizer 24, vertical edge 25. Detailed implementation mode

[0042] As Figures 1 to 9 Shown in the figure is a riveting device for assembling aviation thin-walled parts provided by the present invention, which can effectively ensure the riveting quality of two or more connected thin-walled parts. The riveting device includes a frame, a riveting system and a part fixing mechanism. The riveting system is movably arranged on the frame. During the assembly process of aviation thin-walled parts, two or more aviation thin-walled parts to be riveted are fixed by the part fixing mechanism and riveted into a whole under the cooperation of the riveting system. The technical solution provided in this application is to set up a riveting device including a frame, a riveting system and a part fixing mechanism, and then movably arrange the riveting system on the frame. And during the assembly process of aviation thin-walled parts, two or more aviation thin-walled parts to be riveted are fixed by the part fixing mechanism and riveted into a whole under the cooperation of the riveting system. In this way, since the two or more thin-walled parts to be assembled in this application are fixed by the part fixing mechanism first and then riveted, it can effectively ensure that the two or more connected thin-walled parts are always in a fitting state from the first rivet being riveted to all the rivets being riveted, avoiding the occurrence of the image of not being firmly fitted, and thus achieving the purpose of effectively ensuring the riveting quality of two or more connected thin-walled parts.

[0043] Combined with the actual situation of the production site, in order to simplify the structure of the riveting device of this application as much as possible, facilitate the layout in production, and the riveting work, the frame of this application is a U-shaped truss. The riveting system is movably fixed on the U-shaped truss through the two horizontal edges 1 above and below the U-shaped truss. Two or more aviation thin-walled parts fixed under the control of the part fixing mechanism are riveted into a whole under the cooperation of the U-shaped truss by the riveting system.

[0044] Correspondingly, as a key component improved in the present application, in order to maximize the riveting quality, the part fixing mechanism of the present application includes a part support platform 2 and a clamping and fixing assembly, a part arrangement groove 3 is provided on the part support platform 2, the clamping and fixing assembly is movably arranged on the part support platform 2 outside the part arrangement groove 3, and a top pressing structure adapted to the riveting power output end of the riveting system is respectively provided on the part support platform 2 and the clamping and fixing assembly; two or more aviation thin-walled parts that need to be riveted are detachably fixed in the part arrangement groove 3 by the clamping and fixing assembly, and each aviation thin-walled part that needs to be riveted is riveted as a whole by the top pressing structure with the cooperation of the power output from the riveting power output end of the riveting system. At this time, the part support platform 2 is preferably composed of a high-strength steel plate, the part arrangement groove 3 is arranged on the top surface of the high-strength steel plate, the clamping and fixing assembly includes a pressure plate and a quick-release connection structure, and the top pressure structure includes a riveted top tightening blind hole 4 arranged on the bottom surface of the high-strength steel plate and a riveted stamping avoidance hole 5 arranged on the pressure plate. Each piece of aviation thin-walled parts that need to be riveted is detachably pressed and fixed in the part arrangement groove 3 through the pressure plate with the cooperation of the quick-release connection structure; the riveting power output end of the riveting system inputs stamping power to the rivets inserted in the riveting holes of each piece of aviation thin-walled parts with the cooperation of the riveted top tightening blind hole 4 and the riveted stamping avoidance hole 5. More specifically, the pressure plate includes a pressure plate body 6 and a pressure block 7, and the pressure block 7 is overlapped and arranged on the pressing surface of the pressure plate body 6. The quick-release connection structure includes a hinged support 8 and a quick-release connection support. The hinged support 8 and the quick-release connection support are respectively arranged on the high-strength steel plates on both sides of the part arrangement groove 3 in a mutually adaptive manner. The fixed end of the pressure plate body 6 is hingedly connected to the hinged support 8, and the movable end of the pressure plate body 6 is detachably connected to the quick-release connection support; at least a riveted stamping avoidance hole 5 is provided on the pressure plate body 6. Furthermore, in order to facilitate the assembly and disassembly of aviation thin-walled parts, the quick-release connecting support described in the present application includes two support bodies 9, two adjusters 10 and two locking beads 11. Bead locking grooves 12 are respectively provided at corresponding positions on both sides of the pressure plate body 6. The two locking beads 11 are respectively arranged axially telescopically at corresponding positions of the two support bodies 9 through two adjusters 10, and the positions of each support body 9 are arranged on the high-strength steel plate on one side of the part arrangement groove 3 in a mutually adaptive manner; during the pressing and consolidation process of aviation thin-walled parts, the pressure plate body 6 is locked on the two support bodies 9 through the locking beads 11 and the bead locking grooves 12 with the cooperation of the support body 9 and the adjuster 10.

[0045] As another important component of the improvement of this application, as described above, in order to simplify its structure as much as possible on the premise of facilitating operation, the riveting system of this application includes a lower top-support riveting component and an upper stamping riveting component. The lower top-support riveting component is movably arranged on the lower horizontal side of the C-shaped truss, and the upper stamping riveting component is movably arranged on the upper horizontal side of the C-shaped truss; each aviation thin-walled part fixed on the part fixing mechanism is riveted into a whole by the top iron rod 13 of the lower top-support riveting component and the stamping rod 14 of the upper stamping riveting component under the cooperation of the power input of the lower top-support riveting component and the upper stamping riveting component. At this time, the lower top-support riveting component further includes a second telescopic driver 15, a second driving rod 16, an anti-tilting mechanism and a lower riveting head 17. The second telescopic driver 15 is fixedly installed on the lower horizontal side of the C-shaped truss through the second driving rod 16. The top iron rod 13 is fixedly installed on the anti-tilting mechanism through the lower riveting head 17. The anti-tilting mechanism is movably arranged on the second driving rod 16. The upper stamping riveting component further includes a first telescopic driver 18, a first driving rod 19 and an upper riveting head 20. The first telescopic driver 18 is fixedly installed on the upper horizontal side of the C-shaped truss through the first driving rod 19. The stamping rod 14 is movably fixedly installed on the first driving rod 19 through the upper riveting head 20.

[0046] More specifically, the anti-tilting mechanism includes an anti-tilting frame 21 and a telescopic rod 22. The lower riveting head 17 is fixedly installed on the anti-tilting frame 21. The anti-tilting frame 21 is fixedly installed on the second driving rod 16. At least one telescopic rod 22 is respectively arranged between the anti-tilting frame 21 on both sides of the second driving rod 16 and the lower horizontal side; the upper stamping riveting component further includes an L-shaped support and stabilizer frame 24. One end of the first driving rod 19 connected to the upper riveting head 20 is fixedly connected to the upper middle part of the vertical side of the C-shaped truss through the L-shaped support and stabilizer frame 24; at least four groups of connecting and mounting holes are further provided on the vertical side 25 of the C-shaped truss; reinforcing rib plates are respectively provided between the vertical side and the lower horizontal side of the C-shaped truss and inside the L-shaped support and stabilizer frame 24.

[0047] To sum up, compared with the existing impact riveting, the riveting device provided by this application has been improved mainly in two aspects to solve the problem that the thin-walled parts are prone to warping. After riveting the parts, they still remain flat without the problems of middle bulging and edge warping.

[0048] 1. This application uses a part fixing mechanism to tightly press and fix the parts. During the riveting process, the thin-walled parts have no space for deformation, and the internal stress generated by riveting can be evenly dispersed, avoiding part deformation caused by stress concentration.

[0049] 2. This application adopts the method of press riveting, avoiding the problem of stress concentration that is prone to occur in impact riveting.

[0050] The technical solution of this application will be further described below through specific embodiments:

[0051] Example 1

[0052] Next, in conjunction with the accompanying drawings, the technical solutions in the embodiments of the present application will be clearly and completely described. Obviously, the described embodiments are only a 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 of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0053] A deformation-preventing riveting device for an aviation thin-wall bracket provided by this solution aims to solve problems such as part flanging and non-fitting that are prone to occur during the riveting of thin-wall parts in aircraft assembly.

[0054] First, a description of the problems of the existing riveting technology:

[0055] Aircraft riveting assembly uses rivets as fasteners or connectors to rivet and fix two or more parts together to form an integrated structure. In most cases, two parts are riveted together. In special cases, there may be more than two parts, but this is an exceptional case. Aircraft part riveting has specification requirements. Among them, the requirements for parts include that the gap between two parts after riveting should be less than the gap specified in the standard. Generally, a feeler gauge or a thickness gauge is used for seam inspection. If the feeler gauge can be inserted, it means it is unqualified and the rivet needs to be removed and re-riveted. Generally, the number of rivets for a thin-wall part is not less than 2. After the first rivet is riveted, the part will bend and deform radially with the riveting point as the center. That is to say, at the riveting point of the rivet, due to the extrusion of the part, the stress received by different positions of the part is uneven, resulting in deformation and phenomena such as flanging and arching. However, since the weight of the aircraft is an important indicator of aircraft performance, that is, the method of increasing the part thickness is not allowed by the specifications, thus this technical problem has arisen.

[0056] Secondly, the inventor introduces the core structure and working principle of the present application as follows:

[0057] As Figure 1-9 shown, the riveting structure of the present application includes an outer frame, a stressed skeleton. The skeleton is a structure used to install and fix various functional components. First telescopic drivers and second telescopic drivers are respectively installed at both ends of the skeleton, that is, the upper and lower horizontal sides of the above-mentioned U-shaped truss. The first telescopic driver has a first driving rod capable of outputting an axial force. The end of the first driving rod is detachably and fixedly connected with an upper riveting head. Multiple (at least 2) riveting clamps (a structure for abutting against the rivet, and the end face shape thereof is consistent with the rivet head) are fixedly or detachably and fixedly installed on the upper riveting head;

[0058] The part fixing mechanism is a structure used to place parts and is also a key structure to solve the riveting deformation of thin-walled parts. Figure 6-Figure 9 As shown, the part fixing mechanism includes an integrally formed part support platform for placing and fixing parts. The part support platform has a part slot for placing parts. Generally speaking, a part support platform is usually only suitable for parts of a smaller size, or even can only hold one type of part (special support platform). The function of the part slot is to place the two parts to be riveted in the part slot, and then press the two installed parts in place through the pressing plate, see Figure 6 As shown, part A01 is at the bottom and thin-walled part B02 is at the top. Except for the position where rivets need to be installed, the surface of thin-walled part B02 is tightly compacted, so that during the riveting process, there will be no space and possibility for thin-walled part B02 to deform.

[0059] The fixing principle of parts: one end of the pressure plate is hinged on a pair of supports A, i.e. the above-mentioned hinged supports, and can be flipped freely. When the pressed parts need to be fixed, the other end of the pressure plate will be pressed down to the support B, i.e. the above-mentioned quick-release connection support, and then the retaining bead will be pushed into the spherical groove on the pressure plate by tightening the adjuster to achieve fixation. The rivet head is fixed against the rivet card on the upper rivet joint, and then the second telescopic drive drives the top iron rod to slowly apply stress to the lower end of the rivet until the rivet deformation meets the standard requirements and then returns to the lower rivet joint (the top iron rod is installed on the lower rivet joint and can be replaced according to different types of rivets). After riveting is completed, the second telescopic drive and the first telescopic drive are successively returned, and the adjuster on the support B is released so that the pressure plate can be freely loosened to remove the riveted parts. It should be noted that the pressure block is a structure that is in direct contact with the parts. Its shape varies according to the parts and can be set to a variety of shapes and structures, but the general principle will not change, that is, it must avoid the location where the rivets are installed and cannot affect the installation and riveting of the rivets. Compared with the existing impact riveting, the present application adopts slow pressure riveting. Compared with impact riveting, the parts are more evenly stressed and it is not easy to produce instantaneous stress concentration to cause deformation of the parts. Depending on the riveting form, such as positive riveting or reverse riveting, the rivet loading method and the order of pressure riveting are also different. It can be up first and then down or down first and then up. The part support platform is provided with pressure rivet holes. On the one hand, it is convenient for the top iron rod to move up and down. On the other hand, it can also avoid the problem of too large rivet heads formed after pressure riveting.

Claims

1. A riveting device for assembling thin-walled aviation parts, characterized in that: The riveting device includes a frame, a riveting system and a part fixing mechanism, and the riveting system is movably arranged on the frame; during the assembly process of aviation thin-walled parts, two or more aviation thin-walled parts that need to be riveted are fixed by the part fixing mechanism and riveted into a whole with the cooperation of the riveting system.

2. The riveting device for assembling aviation thin-walled parts according to claim 1 is characterized in that: The frame is a ⌚-shaped truss, and the riveting system is movably fixed on the ⌚-shaped truss through two horizontal edges (1) above and below the ⌚-shaped truss. Two or more aviation thin-walled parts fixed under the control of the part fixing mechanism are riveted into a whole through the riveting system with the cooperation of the ⌚-shaped truss.

3. The riveting device for assembling aviation thin-walled parts according to claim 1 or 2, characterized in that: The part fixing mechanism comprises a part support platform (2) and a clamping and fixing assembly, wherein a part arrangement groove (3) is arranged on the part support platform (2), the clamping and fixing assembly is movably arranged on the part support platform (2) outside the part arrangement groove (3), and a top pressing structure adapted to a riveting power output end of a riveting system is respectively arranged on the part support platform (2) and the clamping and fixing assembly; two or more aviation thin-walled parts to be riveted are detachably fixed in the part arrangement groove (3) by the clamping and fixing assembly, and each aviation thin-walled part to be riveted is riveted into a whole by the top pressing structure in cooperation with the output power of the riveting power output end of the riveting system.

4. The riveting device for assembling aviation thin-walled parts according to claim 3 is characterized in that: The part support platform (2) is composed of a high-strength steel plate, the part arrangement groove (3) is arranged on the top surface of the high-strength steel plate, the pressing and fixing assembly includes a pressing plate and a quick-release connection structure, the pressing structure includes a riveted top-tightening blind hole (4) arranged on the bottom surface of the high-strength steel plate and a riveted punching avoidance hole (5) arranged on the pressing plate, and each aviation thin-walled part to be riveted is detachably pressed and fixed in the part arrangement groove (3) through the pressing plate in cooperation with the quick-release connection structure; the riveting power output end of the riveting system inputs punching power to the rivets inserted in the riveting holes of each aviation thin-walled part in cooperation with the riveted top-tightening blind hole (4) and the riveted punching avoidance hole (5).

5. The riveting device for assembling aviation thin-walled parts according to claim 4, characterized in that: The pressure plate comprises a pressure plate body (6) and a pressure block (7), the pressure block (7) is overlapped and arranged on the pressing surface of the pressure plate body (6), the quick-release connection structure comprises a hinge support (8) and a quick-release connection support, the hinge support (8) and the quick-release connection support are respectively arranged on the high-strength steel plates on both sides of the part arrangement groove (3) in a mutually adaptive manner, the fixed end of the pressure plate body (6) is hingedly connected to the hinge support (8), and the movable end of the pressure plate body (6) is detachably connected to the quick-release connection support; at least a riveted stamping avoidance hole (5) is provided on the pressure plate body (6).

6. The riveting device for assembling aviation thin-walled parts according to claim 5, characterized in that: The quick-release connecting support includes two support bodies (9), two regulators (10) and two locking balls (11). At corresponding positions on both sides of the pressing plate body (6), there are respectively provided ball locking grooves (12). The two locking balls (11) are respectively arranged at corresponding positions of the two support bodies (9) in an axially telescopic manner through the two regulators (10). Each support body (9) is arranged on the high-strength steel plate on one side of the part arrangement groove (3) in a mutually adapted manner. During the pressing process of the aviation thin-walled part, the pressing plate body (6) is locked on the two support bodies (9) through the cooperation of the locking balls (11) and the ball locking grooves (12) with the support bodies (9) and the regulators (10).

7. The riveting device for assembling aviation thin-walled parts according to claim 6, characterized in that: The riveting system includes a lower supporting riveting assembly and an upper stamping riveting assembly. The lower supporting riveting assembly is movably arranged on the lower horizontal side of the C-shaped truss, and the upper stamping riveting assembly is movably arranged on the upper horizontal side of the C-shaped truss. Each aviation thin-walled part fixed on the part fixing mechanism is riveted into a whole through the cooperation of the top iron rod (13) of the lower supporting riveting assembly and the stamping rod (14) of the upper stamping riveting assembly under the input power of the lower supporting riveting assembly and the upper stamping riveting assembly.

8. The riveting device for assembling aviation thin-walled parts according to claim 7, characterized in that: The lower supporting riveting assembly further includes a second telescopic driver (15), a second driving rod (16), an anti-tilting mechanism and a lower riveting head (17). The second telescopic driver (15) is fixedly installed on the lower horizontal side of the C-shaped truss through the second driving rod (16). The top iron rod (13) is fixedly installed on the anti-tilting mechanism through the lower riveting head (17), and the anti-tilting mechanism is movably arranged on the second driving rod (16).

9. The riveting device for assembling aviation thin-walled parts according to claim 8, characterized in that: The upper stamping riveting assembly further includes a first telescopic driver (18), a first driving rod (19) and an upper riveting head (20). The first telescopic driver (18) is fixedly installed on the upper horizontal side of the C-shaped truss through the first driving rod (19). The stamping rod (14) is movably fixedly installed on the first driving rod (19) through the upper riveting head (20).

10. The riveting device for assembling aviation thin-walled parts according to claim 9, characterized in that: The anti-tilting mechanism includes an anti-tilting frame (21) and a telescopic rod (22). The lower riveting head (17) is fixedly installed on the anti-tilting frame (21), and the anti-tilting frame (21) is fixedly installed on the second driving rod (16). At least one telescopic rod (22) is respectively arranged between the anti-tilting frame (21) on both sides of the second driving rod (16) and the lower horizontal side. The upper stamping riveting assembly further includes an L-shaped support and stabilizer frame (24). One end of the first driving rod (19) connected to the upper riveting head (20) is fixedly connected to the upper middle part of the vertical side of the C-shaped truss through the L-shaped support and stabilizer frame (24). At least four groups of connecting and mounting holes are further provided on the vertical side (25) of the C-shaped truss. Reinforcing rib plates are respectively provided between the vertical side and the lower horizontal side of the C-shaped truss and inside the L-shaped support and stabilizer frame (24).

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