High-flatness aircraft skin connecting piece

Abstract

The invention discloses a high-flatness aircraft skin connecting piece, and relates to the technical field of aircraft skins. The device comprises a machine body framework, a plurality of connecting piece assembling grooves are formed in the machine body framework, threaded suspension shafts are fixedly installed on the two sides of the interior of each connecting piece assembling groove, the two threaded suspension shafts are coaxially arranged, and a butt joint threaded groove is formed in one end of one threaded suspension shaft. By arranging the skin connecting structure, the aircraft skin connecting piece can be adjusted and replaced, the radian of the skin connecting plate is more adaptive to the curved surface fitting degree required by the current skin, and the angle between the two sub-pieces on the skin connecting structure can be adjusted and controlled in the design stage; the overall pitching angle of the skin connecting structure and the included angle between the components are adjusted, so that the more flexible and controllable curved surface fitting degree is obtained, transition between the skin and the connecting piece and transition between the skin and the framework are smoother, and the outer surface of the skin is smoother.

Description

Technical Field

[0001] This invention relates to the field of aircraft skin technology, and more specifically to a high-flatness aircraft skin connector. Background Technology

[0002] The massive fuselage of an aircraft is not a single piece; it requires millions of rivets to connect the fuselage structure. The skin, which is 2 to 5 millimeters thick, is like the "outer garment" of the aircraft. It has poor weldability and is easily deformed by heat, so it can only be physically fixed. At the same time, the turbulence generated by the airflow during flight will subject the skin to multi-directional tensile and bending forces. Therefore, the connectors must be fastened to each component to effectively distribute stress from all directions, and must also have characteristics such as fatigue resistance, crack resistance, and resistance to repeated vibration. In addition, during the upgrade and maintenance of the aircraft, the skin needs to be disassembled quickly. Welding is a permanent connection and is inconvenient to disassemble, while riveting technology can achieve easy disassembly and assembly, significantly improving maintenance efficiency. Therefore, riveting technology is often used to tightly splice together the skin and frame of different sizes.

[0003] Existing aircraft skins are assembled with the frame using rivets and connectors. However, the transition between the current connectors and the skin is not smooth enough, resulting in insufficient surface fit between the assembled skin and the connectors, which affects the aircraft's flight safety and aerodynamic performance. Therefore, a high-flatness aircraft skin connector is proposed. Summary of the Invention

[0004] The purpose of this invention is to solve the problem that the transition between the connector and the skin is not smooth enough, resulting in insufficient surface fit between the assembled skin and the connector, which affects the flight safety and aerodynamic performance of the aircraft. This invention provides a high-flatness aircraft skin connector.

[0005] To achieve the above objectives, the present invention specifically adopts the following technical solution: A high-flatness aircraft skin connector includes an airframe with multiple connector assembly slots. Threaded suspension shafts are fixedly installed on both sides of each connector assembly slot. Two threaded suspension shafts are coaxially arranged. One end of one threaded suspension shaft has a mating thread groove, and one end of the other threaded suspension shaft is fixedly installed with a mating screw adapted to the mating thread groove. A skin connection structure is provided on the ends of the two threaded suspension shafts that are close to each other. The skin connection structure includes two assembly rings respectively fitted onto one end of the two threaded suspension shafts. Two symmetrically arranged semi-shell sliding sleeves are fixedly installed on the side wall of each assembly ring. A pressure-bearing slide rod is slidably inserted into the two semi-shell sliding sleeves located at the same location. Slide rod riveting holes are opened on the side walls of the semi-shell sliding sleeves and the pressure-bearing slide rods. Slide rod rivets are inserted into the three slide rod riveting holes located at the same location. An assembly plate is fixedly installed at one end of each pressure-bearing slide rod. A skin connecting plate is fixedly installed on one side of each assembly plate. Multiple evenly distributed skin riveting holes are opened on the side of the skin connecting plate away from the body frame.

[0006] Furthermore, two single-drum rivets are fixedly inserted into the inner walls on both sides of the connecting component assembly groove. The four single-drum rivets are arranged coaxially and symmetrically in pairs, and the heads of the four single-drum rivets are respectively located on one side of the four half-shell sliding sleeves.

[0007] Furthermore, energy-absorbing hollow blocks are fixedly installed on the top and bottom inner walls of the connector assembly groove, and the heads of the two single-drum rivets located at the same location are engaged inside the energy-absorbing hollow blocks.

[0008] Furthermore, welding rings are fixedly installed on the sides of the two assembly rings that are close to each other, and multiple energy-absorbing hollow teeth are fixedly installed on the sides of the two welding rings that are close to each other, which are evenly distributed along the axis of the assembly rings. The multiple energy-absorbing hollow teeth distributed on both sides are staggered.

[0009] Furthermore, active corrugated plates are fixedly installed on both sides of one end of the pressure-bearing slide rod located inside the semi-shell slide sleeve, and energy-absorbing corrugated plates that match the active corrugated plates are fixedly installed on the inner wall of the semi-shell slide sleeve.

[0010] Furthermore, multiple evenly distributed reinforcing arc-shaped rods are fixedly installed on the side of the skin connecting plate facing the body frame, and one end of each of the multiple skin riveting holes penetrates the multiple reinforcing arc-shaped rods respectively.

[0011] Furthermore, each of the skin connecting plates has multiple reinforcing through holes at one end, and the same double-ended threaded rod passes through the interior of the multiple reinforcing through holes located at the same location. Both ends of the multiple double-ended threaded rods are screwed with fastening nuts.

[0012] Furthermore, a plurality of evenly distributed transition arc plates are provided between the two skin connecting plates. The plurality of transition arc plates are respectively located between the plurality of reinforcing arc rods. Two reinforcing arc strips are fixedly installed on the side of each transition arc plate facing the body frame. The two ends of the two reinforcing arc strips located at the same location are respectively in contact with one end of the two reinforcing arc rods. The plurality of double-ended threaded rods are respectively passed through the two ends of the reinforcing arc strips.

[0013] The beneficial effects of this invention are as follows: 1. This invention, by setting a skin connection structure, allows the aircraft skin connectors to be adjusted and replaced, making the curvature of the skin connection plate more suitable for the required surface fit of the current skin. The angle between the two components on the skin connection structure can be adjusted during the design stage, and the pitch angle of the overall skin connection structure and the included angle between the components can be adjusted to obtain a more flexible and controllable surface fit, making the transition between the skin, connectors and frame smoother, and making the outer surface of the skin flatter. 2. By setting a transition arc plate, the present invention positions the transition arc plate between two skin connecting plates. It can not only abut against the middle of the two skin connecting plates to maintain the stability of the included angle between the two skin connecting plates, but also fill the gap between the two skin connecting plates, making the transition between the skin connecting plates smoother. At the same time, the individual structure of the transition arc plate and the reinforcing arc strip can continue to be set in different skin connection structures, which greatly improves the flatness of the skin after riveting on the skin connecting plates. 3. By setting up energy-absorbing hollow teeth, the energy-absorbing hollow teeth on both sides interlock and lock the included angle of the two components and the included angle of the skin connecting plate, thereby improving the stability of the skin connecting structure after it is shaped. At the same time, when the fuselage is impacted, the two components of the skin connecting structure are subjected to impact forces from different directions. The energy-absorbing hollow teeth will squeeze each other and undergo plastic deformation, thereby converting the impact load into heat energy and other forms of energy through the deformation of the energy-absorbing hollow teeth, playing the role of energy absorption and buffering. 4. By setting a single-drum rivet and an energy-absorbing hollow block, the single-drum rivet can limit the two parts of the skin connection structure during assembly and daily operation. When the fuselage is impacted, similar to the energy-absorbing hollow tooth, the energy-absorbing hollow block will continue to deform and absorb energy after the single-drum rivet breaks, thereby buffering and avoiding abnormal damage to the skin connection structure caused by abnormal force during impact. 5. By setting up active corrugated plates and energy-absorbing corrugated plates, this invention ensures that when the fuselage is impacted, if the pressure-bearing slide bar and the half-shell sliding sleeve bear axial impact load, the impact kinetic energy will first destroy the slide bar rivets, and then be transmitted through the pressure-bearing slide bar and active corrugated plates to the energy-absorbing corrugated plates on both sides. This will crush the energy-absorbing corrugated plates with lower stiffness, causing the energy-absorbing corrugated plates to produce orderly, continuous, and stable plastic buckling deformation, thereby rapidly converting and absorbing the axial impact kinetic energy, completing efficient, stable, and irreversible kinetic energy consumption, and playing a protective role for the fuselage frame. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural schematic diagram of the present invention; Figure 2 This is a three-dimensional structural diagram of the suspension shaft and assembly ring of the present invention; Figure 3 This is a three-dimensional structural diagram of the threaded suspension shaft of the present invention; Figure 4 This is a second-view perspective three-dimensional structural diagram of the skin connector of the present invention; Figure 5 This is a second-view perspective three-dimensional structural diagram of the skin connector of the present invention; Figure 6 This is a three-dimensional structural diagram of the assembly ring and the skin connecting plate of the present invention. Figure 7 This is a schematic diagram of the three-dimensional structure of the assembly ring of the present invention; Figure 8 This is a schematic diagram of the three-dimensional structure of the pressure-bearing slide bar of the present invention; Figure 9 This is a schematic diagram of the three-dimensional structure of the semi-shell sliding sleeve of the present invention; Reference numerals: 1. Body frame; 101. Connecting component assembly slot; 2. Threaded suspension shaft; 201. Butt threaded groove; 202. Butt screw; 3. Assembly ring; 4. Half-shell sliding sleeve; 5. Pressure-bearing sliding rod; 501. Sliding rod riveting hole; 6. Sliding rod rivet; 7. Assembly plate; 8. Skin connecting plate; 801. Skin riveting hole; 9. Single-drum rivet; 10. Energy-absorbing hollow block; 11. Welding ring; 12. Energy-absorbing hollow tooth; 13. Active corrugated plate; 14. Energy-absorbing corrugated plate; 15. Reinforcing arc rod; 1501. Reinforcing through hole; 16. Double-ended threaded rod; 17. Fastening nut; 18. Reinforcing arc strip; 19. Transition arc plate. Detailed Implementation

[0015] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0016] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0017] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0018] In the description of the embodiments of the present invention, it should be noted that the terms "inner", "outer", "upper", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the present invention.

[0019] like Figures 1 to 9 As shown, a high-flatness aircraft skin connector includes an airframe 1, such as... Figure 1 , Figure 2 . Figure 3 As shown, the frame 1 has multiple connector assembly slots 101. Threaded suspension shafts 2 are fixedly installed on both sides of the inner side of each connector assembly slot 101. Two threaded suspension shafts 2 are coaxially arranged. One end of one threaded suspension shaft 2 has a mating thread groove 201, and one end of the other threaded suspension shaft 2 is fixedly fitted with a mating screw 202 that matches the mating thread groove 201. A skin connection structure is provided on the ends of the two threaded suspension shafts 2 that are close to each other, such as... Figure 4 , Figure 6 , Figure 8 As shown, the skin connection structure includes two assembly rings 3 respectively fitted onto one end of two threaded suspension shafts 2. Two symmetrically arranged half-shell sliding sleeves 4 are fixedly installed on the side wall of each assembly ring 3. A pressure-bearing slide rod 5 is slidably inserted into the two half-shell sliding sleeves 4 located at the same location. Slide rod riveting holes 501 are opened on the side wall of each half-shell sliding sleeve 4 and the pressure-bearing slide rod 5. Slide rod rivets 6 are inserted into the three slide rod riveting holes 501 located at the same location. An assembly plate 7 is fixedly installed on one end of each pressure-bearing slide rod 5. A skin connecting plate 8 is fixedly installed on one side of each assembly plate 7. Multiple evenly distributed skin riveting holes 801 are opened on the side of the skin connecting plate 8 away from the body frame 1.

[0020] More specifically, by setting up a skin connection structure, the aircraft skin connectors can be adjusted and replaced according to the location and specifications of the skin. This makes the curvature of the skin connection plate 8 more suitable for the required surface fit of the current skin. The angle between the two components on the skin connection structure can be adjusted during the design stage. The pitch angle of the overall skin connection structure and the included angle between the components can be adjusted to obtain a more flexible and controllable surface fit, making the transition between the skin, connectors, and frame smoother and the outer surface of the skin flatter.

[0021] like Figure 4 , Figure 6As shown, specifically, multiple evenly distributed reinforcing arc rods 15 are fixedly installed on the side of the skin connecting plate 8 facing the body frame 1. One end of multiple skin riveting holes 801 passes through multiple reinforcing arc rods 15 respectively. Multiple reinforcing through holes 1501 are opened on one end of the skin connecting plate 8. The same double-ended threaded rod 16 passes through the inside of the multiple reinforcing through holes 1501 located at the same location. Both ends of the multiple double-ended threaded rods 16 are screwed with fastening nuts 17. Two reinforcing arc strips 18 are fixedly installed on the side of the transition arc plate 19 facing the body frame 1. The two ends of the two reinforcing arc strips 18 located at the same location are in contact with one end of the two reinforcing arc rods 15 respectively. Multiple double-ended threaded rods 16 are respectively passed through the two ends of the reinforcing arc strips 18.

[0022] In this embodiment, the number of transition arc plates 19 can be adjusted. For example, the number of transition arc plates 19 can be set to half the number of reinforcing arc rods 15, and the number of reinforcing arc strips 18 is the same as the number of reinforcing arc rods 15. Each transition arc plate 19 has a reinforcing arc rod 15 at both ends, and the two reinforcing arc rods 15 are connected by two reinforcing arc strips 18.

[0023] More specifically, by setting up reinforcing arc rods 15 and reinforcing arc strips 18, the reinforcing arc rods 15 are positioned on the inner side of the skin connecting plate 8, reinforcing the skin connecting plate 8 and the skin riveting holes 801 used for riveting the skin. At the same time, each reinforcing arc strip 18 is screwed between each reinforcing arc rod 15 through a double-threaded rod 16 and a fastening nut 17, so that the reinforcing arc strips 18, double-threaded rods 16 and reinforcing arc rods 15 form a small skeleton, which not only greatly enhances the structural strength of each skin connecting plate 8, but also enhances the connection strength between skin connecting plates 8.

[0024] like Figure 4 , Figure 6 As shown, specifically, multiple evenly distributed transition arc plates 19 are provided between the two skin connecting plates 8, and the multiple transition arc plates 19 are respectively located between multiple reinforcing arc rods 15.

[0025] More specifically, by setting a transition arc plate 19, the transition arc plate 19 is positioned between the two skin connecting plates 8. It can both abut against the middle of the two skin connecting plates 8 to maintain the stability of the included angle between the two skin connecting plates 8, and fill the gap between the two skin connecting plates 8, making the transition between the skin connecting plates 8 smoother. At the same time, the individual structures of the transition arc plate 19 and the reinforcing arc strip 18 can continue to be set in different skin connection structures, which greatly improves the flatness of the skin after it is riveted on the skin connecting plate 8.

[0026] like Figure 6 , Figure 7As shown, specifically, welding rings 11 are fixedly installed on the side of the two assembly rings 3 that are close to each other, and multiple energy-absorbing hollow teeth 12 are fixedly installed on the side of the two welding rings 11 that are close to each other, which are evenly distributed along the axis of the assembly rings 3. The multiple energy-absorbing hollow teeth 12 distributed on both sides are staggered.

[0027] More specifically, by setting energy-absorbing hollow teeth 12, the energy-absorbing hollow teeth 12 on both sides interlock and lock the included angle of the two components and the included angle of the skin connecting plate 8, thereby improving the stability of the skin connecting structure after it is shaped. At the same time, when the fuselage is impacted, the two components of the skin connecting structure are subjected to impact forces from different directions. The energy-absorbing hollow teeth 12 will squeeze each other and undergo plastic deformation, thereby converting the impact load into heat energy and other forms of energy through the deformation of the energy-absorbing hollow teeth 12, playing the role of energy absorption and buffering.

[0028] like Figure 2 As shown, specifically, two single-drum rivets 9 are fixedly inserted into the inner walls on both sides of the connector assembly groove 101. The four single-drum rivets 9 are arranged coaxially and symmetrically in pairs. The heads of the four single-drum rivets 9 are located on one side of the four half-shell sliding sleeves 4 respectively. Energy-absorbing hollow blocks 10 are fixedly installed on the inner walls of the top and bottom of the connector assembly groove 101. The heads of the two single-drum rivets 9 located at the same place are engaged inside the energy-absorbing hollow block 10.

[0029] More specifically, by setting up a single-drum rivet 9 and an energy-absorbing hollow block 10, the single-drum rivet 9 can limit the two parts of the skin connection structure during assembly and daily operation. When the fuselage is impacted, similar to the energy-absorbing hollow tooth 12, the energy-absorbing hollow block 10 will continue to deform and absorb energy after the single-drum rivet 9 breaks, thereby buffering and avoiding abnormal damage to the skin connection structure caused by abnormal force during impact.

[0030] like Figure 8 , Figure 9 As shown, specifically, active corrugated plates 13 are fixedly installed on both sides of one end of the pressure-bearing slide rod 5 inside the semi-shell slide sleeve 4, and energy-absorbing corrugated plates 14 that match the active corrugated plates 13 are fixedly installed on the inner wall of the semi-shell slide sleeve 4.

[0031] More specifically, by setting up active corrugated plates 13 and energy-absorbing corrugated plates 14, when the fuselage is impacted, if the pressure-bearing slide bar 5 and the half-shell slide sleeve 4 bear axial impact loads, the impact kinetic energy will first destroy the slide bar rivets 6, and then be transmitted to the energy-absorbing corrugated plates 14 on both sides through the pressure-bearing slide bar 5 and the active corrugated plates 13. This will crush the energy-absorbing corrugated plates 14 with lower stiffness, causing the energy-absorbing corrugated plates 14 to produce orderly, continuous, and stable plastic buckling deformation, thereby quickly converting and absorbing the axial impact kinetic energy, completing efficient, stable, and irreversible kinetic energy consumption, and playing a protective role for the fuselage frame 1.

[0032] In summary: Assembly of components: According to the specified position, the pressure-bearing slide rod 5 is inserted into the interior of one of the half-shell slide sleeves 4, so that the active corrugated plate 13 engages with the energy-absorbing corrugated plate 14 inside the half-shell slide sleeve 4. Then, one half-shell slide sleeve 4 is welded to fix the pressure-bearing slide rod 5. Then, the skin connecting plate 8 with multiple reinforcing arc rods 15 is riveted to the assembly plate 7 at the top of the pressure-bearing slide rod 5. After that, the complete half-shell slide sleeve 4 is welded to the assembly ring 3 with the half-shell slide sleeve 4 and the energy-absorbing hollow tooth 12, thus completing the assembly of the first group of components. Assembly of components: Assemble another set of components according to the same process. Finally, at the specified angle, make the energy-absorbing hollow teeth 12 on the two assembly rings 3 mesh with each other, and then interlock the two components. Then, screw a set of threaded suspension shafts 2 into the two assembly rings 3 to assemble the components into a complete skin connection structure. Assembly of the reinforced structure: Select reinforcing arc strips 18 in the same number as the reinforcing arc rods 15, group them in pairs, first select one group and place it between the two skin connecting plates 8, so that the two ends of the two reinforcing arc strips 18 contact the two sides of one end of the first group of reinforcing arc rods 15 respectively, and pass each double-ended threaded rod 16 through the reinforcing arc strips 18 and the reinforcing arc rods 15 for a certain distance, temporarily suspend and fix the first group of reinforcing arc strips 18, repeat the operation until each group of reinforcing arc rods 15 is equipped with two reinforcing arc strips 18, at which point each double-ended threaded rod 16 fixes all the reinforcing arc strips 18, and then screws fastening nuts 17 at both ends of each double-ended threaded rod 16 to fasten the reinforcing arc strips 18 to the reinforcing arc rods 15; Assembly of transition arc plates: According to the ratio of two reinforcing arc strips 18 to one transition arc plate 19, the transition arc plates 19 are welded onto the reinforcing arc strips 18 in sequence, or a whole transition arc plate 19 is directly welded, so that the transition arc plate 19 is stuck between the two skin connecting plates 8. Assembly of the skin connection structure: Holes are drilled in the connector assembly groove 101 and the threaded suspension shaft 2. The threaded suspension shaft 2, together with the skin connection structure, is riveted into the connector assembly groove 101. Holes are drilled on the upper and lower inner walls of the connector assembly groove 101 and single-drum rivets 9 are riveted to secure the two components. Two energy-absorbing hollow blocks 10 are inserted into the connector assembly groove 101 and secured to the four single-drum rivets 9 from the upper and lower sides. The two energy-absorbing hollow blocks 10 are then riveted to complete the assembly of the first skin connection structure with the body frame 1. After all the skin connection structures are assembled, the skin can be riveted and fixed using rivets and the skin riveting holes 801 on the skin connection plate 8.

[0033] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed invention. The scope of protection claimed by the appended claims and their equivalents is defined.

Claims

1. A high-flatness aircraft skin connector, characterized in that, The system includes a frame (1), on which a plurality of connector assembly slots (101) are provided. Threaded suspension shafts (2) are fixedly installed on both sides of the connector assembly slots (101). Two threaded suspension shafts (2) are coaxially arranged. One end of one threaded suspension shaft (2) is provided with a mating thread groove (201), and one end of the other threaded suspension shaft (2) is fixedly installed with a mating screw (202) that is compatible with the mating thread groove (201). A skin connection structure is provided on the ends of the two threaded suspension shafts (2) that are close to each other. The skin connection structure includes two assembly rings (3) respectively sleeved on one end of the two threaded suspension shafts (2). Two symmetrically arranged half-shell sliding sleeves (4) are fixedly installed on the side wall of each assembly ring (3). A pressure-bearing slide rod (5) is slidably inserted into the two half-shell sliding sleeves (4) located at the same location. A slide rod riveting hole (501) is opened on the side wall of each half-shell sliding sleeve (4) and the pressure-bearing slide rod (5). A slide rod rivet (6) is inserted into the three slide rod riveting holes (501) located at the same location. An assembly plate (7) is fixedly installed on one end of each pressure-bearing slide rod (5). A skin connecting plate (8) is fixedly installed on one side of each assembly plate (7). A plurality of evenly distributed skin riveting holes (801) are opened on the side of the skin connecting plate (8) away from the body frame (1).

2. The high-flatness aircraft skin connector according to claim 1, characterized in that, Two single-drum rivets (9) are fixedly inserted into the inner walls of both sides of the connector assembly groove (101). The four single-drum rivets (9) are arranged coaxially and symmetrically in pairs. The heads of the four single-drum rivets (9) are located on one side of the four half-shell sliding sleeves (4).

3. The high-flatness aircraft skin connector according to claim 2, characterized in that, Energy-absorbing hollow blocks (10) are fixedly installed on the top and bottom inner walls of the connector assembly groove (101), and the heads of the two single-drum rivets (9) located at the same location are engaged inside the energy-absorbing hollow blocks (10).

4. The high-flatness aircraft skin connector according to claim 1, characterized in that, Welding rings (11) are fixedly installed on the side of the two assembly rings (3) that are close to each other. Multiple energy-absorbing hollow teeth (12) are fixedly installed on the side of the two welding rings (11) that are close to each other. The multiple energy-absorbing hollow teeth (12) distributed on both sides are staggered.

5. The high-flatness aircraft skin connector according to claim 1, characterized in that, Both sides of the pressure-bearing slide bar (5) located inside the half-shell slide sleeve (4) are fixedly installed with active corrugated plates (13), and energy-absorbing corrugated plates (14) that match the active corrugated plates (13) are fixedly installed on the inner wall of the half-shell slide sleeve (4).

6. The high-flatness aircraft skin connector according to claim 1, characterized in that, Multiple evenly distributed reinforcing arc rods (15) are fixedly installed on the side of the skin connecting plate (8) facing the body frame (1), and one end of each of the multiple skin riveting holes (801) penetrates the multiple reinforcing arc rods (15).

7. A high-flatness aircraft skin connector according to claim 6, characterized in that, One end of each of the skin connecting plates (8) is provided with multiple reinforcing through holes (1501), and the same double-ended threaded rod (16) is inserted inside the multiple reinforcing through holes (1501) located at the same location. Both ends of the multiple double-ended threaded rods (16) are screwed with fastening nuts (17).

8. A high-flatness aircraft skin connector according to claim 7, characterized in that, Multiple uniformly distributed transition arc plates (19) are provided between the two skin connecting plates (8). The multiple transition arc plates (19) are respectively located between the multiple reinforcing arc rods (15). Two reinforcing arc strips (18) are fixedly installed on the side of the transition arc plate (19) facing the body frame (1). The two ends of the two reinforcing arc strips (18) located at the same place are respectively in contact with one end of the two reinforcing arc rods (15). Multiple double-headed threaded rods (16) are respectively passed through the two ends of the reinforcing arc strips (18).

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