Composite wing eVTOL wing body butt joint structure with interchangeability and automatic centering

Abstract

The utility model relates to the technical field of electric aircrafts, in particular to a composite wing eVTOL wing body butt joint structure with interchangeability and automatic centering, which comprises a fuselage first front transverse frame, and two sides of the fuselage first front transverse frame are fixedly connected with fuselage front edge ribs through bolts. The airframe front frame has the advantages of being simple in structure, easy to manufacture, low in assembly difficulty and capable of achieving wing body butt joint, in the actual use process, the first front transverse frame, the airframe front edge rib, the second front transverse frame and the airframe front longitudinal frame on the front portion of the airframe are used in cooperation, a bolt connection mode is adopted, splicing of the airframe front frame can be easily completed, and the assembly efficiency is improved. The rear portion of the fuselage is matched with the rear longitudinal frame of the fuselage through a first rear transverse frame, a rear edge rib of the fuselage and a second rear transverse frame, bolt connection is still adopted, a rear frame of the fuselage can be smoothly spliced, the front frame of the fuselage is connected with the rear frame of the fuselage through a connector automatic centering device, and installation precision and stability are guaranteed. And a solid foundation is provided for subsequent assembly work.

Description

Technical Field

[0001] This utility model relates to the field of electric aircraft technology, specifically to a composite wing eVTOL wing-body docking structure with interchangeability and automatic alignment. Background Technology

[0002] The wing-body joint is the most important part of aircraft structural design. All the loads of the wing are transferred to the fuselage through the wing-body joint, which is a high-stress area of ​​the aircraft and directly affects the safety of the aircraft. At the same time, the accuracy of the wing-body joint directly affects the wing attitude. The structural design of the wing-body joint requires a comprehensive consideration of structural strength, safety and assembly process.

[0003] Traditional large and medium-sized high-wing aircraft have several drawbacks due to the lack of a dedicated docking structure for the center wing to connect with the fuselage. First, because the docking point is an intersection line on the center wing structure, an additional transition structure is needed at the wing ribs, making the center wing structure complex and increasing its weight. Second, it occupies a significant amount of internal fuselage space, which is not conducive to the layout of internal systems and other specialized pipelines. Third, even without a center wing, the "back-to-back" design of the wing and fuselage makes controlling the structural positioning and assembly accuracy during wing-fuselage docking a huge workload, and may even cause misalignment of the wing-fuselage docking holes, resulting in forced assembly. Utility Model Content

[0004] The purpose of this invention is to provide a composite wing eVTOL wing-body docking structure that is interchangeable and automatically aligned. It has the advantages of simple structure, simple manufacturing, and low assembly difficulty in wing-body docking. It solves the problem that controlling the positioning and assembly accuracy of the structure during wing-body docking can bring a huge workload and even affect the misalignment of the wing-body docking holes, resulting in forced assembly.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a compound wing eVTOL wing-body docking structure with interchangeability and automatic alignment, comprising a first forward transverse frame of the fuselage, both sides of which are bolted to fuselage leading edge ribs, and a second forward transverse frame of the fuselage bolted to the opposite side of the two fuselage leading edge ribs, a forward longitudinal frame of the fuselage bolted between the first and second forward transverse frames, a first aft transverse frame of the fuselage on one side of the forward longitudinal frame, both sides of which are bolted to fuselage rear edge ribs, a second aft transverse frame of the fuselage bolted to the opposite side of the two fuselage rear edge ribs, a rear longitudinal frame of the fuselage bolted between the rear edge ribs and the second aft transverse frame of the fuselage, and the second forward transverse frame of the fuselage and the fuselage... The surfaces of the first rear transverse frame opposite each other are fixedly connected to automatic centering devices by bolts. A wing frame is installed on the side of the second front transverse frame opposite to the first rear transverse frame. Wing joints are installed on both sides of the inner cavity of the wing frame. A hexagonal nut is fixedly connected to the inner cavity of the wing joint. A hexagonal anti-loosening washer is fixedly connected to the surface of the hexagonal nut. An anti-loosening pin is fixedly connected to one end of the inner cavity of the hexagonal nut. A wing-body positioning joint is fixedly connected to one side of the wing joint, and the wing-body positioning joint is located on the outer side of the wing frame. A wing-body mating bolt is installed on one side of the wing-body positioning joint. An anti-loosening washer is fitted onto the surface of the wing-body mating bolt. A bushing is installed on one side of the anti-loosening washer, and the bushing is fitted onto the surface of the wing-body mating bolt. The wing-body positioning joint is fixedly connected to the other end of the inner cavity of the hexagonal nut.

[0006] Furthermore, as a preferred embodiment of this utility model, the automatic centering device for the connector includes a docking plate, and two sets of docking plates are provided. The docking plates are respectively fixedly connected to the side opposite to the second front cross frame and the first rear cross frame of the machine body. The docking plates are provided with positioning grooves on their surfaces.

[0007] Furthermore, as a preferred embodiment of this utility model, two first docking holes are provided on the surfaces of the second front cross frame and the first rear cross frame of the fuselage. The first docking holes and the second docking holes have the same diameter. The positioning rail groove is configured as a raised arc-shaped structure, and the wing-body positioning joint is adapted to the positioning rail groove.

[0008] Furthermore, as a preferred embodiment of this utility model, the wing frame includes a wing front sparsity, one side of which is fixedly connected to four wing ribs by bolts, and the other side of the four wing ribs is jointly fixedly connected to a wing rear sparsity by bolts.

[0009] Furthermore, as a preferred embodiment of this utility model, two large beam holes are provided on the surfaces of both the front and rear wing spars, and the large beam holes are adapted to the first and second mating holes.

[0010] Beneficial effects: The technical solution of this application has the following technical effects: This utility model has the advantages of simple structure, simple manufacturing, low assembly difficulty, and wing-fuselage docking. In actual use, through the cooperation of the first forward transverse frame, the leading edge rib, the second forward transverse frame, and the forward longitudinal frame of the fuselage, the front frame of the fuselage can be easily assembled by bolt connection. Similarly, the rear frame of the fuselage can be smoothly assembled by bolt connection through the cooperation of the first rear transverse frame, the rear edge rib, the second rear transverse frame, and the rear longitudinal frame of the fuselage. The front frame and the rear frame of the fuselage are connected by a joint. The automatic centering device ensures the accuracy and stability of the installation, providing a solid foundation for subsequent assembly work. The wing-body docking adopts an automatic centering structure, which has low manufacturing cost and significantly improves positioning accuracy while reducing assembly difficulty. During the splicing process of the wing frame, the splicing of the wing frame and wing joint is successfully completed through the coordinated use of the wing frame, wing joint, hexagonal nut, hexagonal anti-loosening washer, anti-loosening washer, and bushing. This simplifies the overall assembly process of the aircraft, effectively reduces the complexity of the wing structure, and improves the convenience of the overall aircraft assembly.

[0011] It should be understood that all combinations of the foregoing concepts and the additional concepts described in more detail below can be considered as part of the utility model subject matter of this disclosure, provided that such concepts do not contradict each other. Attached Figure Description

[0012] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0013] Figure 1 This is a schematic diagram of the front horizontal frame structure of this utility model;

[0014] Figure 2 This is a rear view of the front horizontal frame structure of this utility model;

[0015] Figure 3 This is a schematic diagram of the rear horizontal frame structure of this utility model;

[0016] Figure 4 This is a schematic diagram of the wing frame structure of this utility model;

[0017] Figure 5 This is an enlarged cross-sectional view of the wing joint structure of this utility model.

[0018] In the figure, the meanings of the various reference numerals are as follows: 1. First forward transverse frame of fuselage; 2. Leading edge rib of fuselage; 3. Second forward transverse frame of fuselage; 4. Forward longitudinal frame of fuselage; 5. First aft transverse frame of fuselage; 6. Rear edge rib of fuselage; 7. Second aft transverse frame of fuselage; 8. Rear longitudinal frame of fuselage; 9. Automatic centering device for the joint; 901. Docking plate; 902. Second docking hole; 903. Positioning rail groove; 10. Wing frame; 101. Wing front spars; 102. Wing rib; 103. Wing rear spars; 11. Wing joint; 12. Hexagonal nut; 13. Hexagonal anti-loosening washer; 14. Anti-loosening pin; 15. Wing-body positioning joint; 16. Wing-body docking bolt; 17. Anti-loosening washer; 18. Bushing; 19. First docking hole. Detailed Implementation

[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. To better understand the technical content of the present utility model, specific embodiments are provided and described in conjunction with the accompanying drawings. Various aspects of the present utility model are described in this disclosure with reference to the accompanying drawings, which show many illustrative embodiments. It should be understood that the various concepts and embodiments described above, as well as those described in more detail below, can be implemented in any of many ways. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0020] As attached Figure 1 To be continued Figure 5As shown: This embodiment provides a composite wing eVTOL wing-body docking structure with interchangeability and automatic alignment, including a first forward transverse frame 1 of the fuselage. Both sides of the first forward transverse frame 1 are bolted to fuselage leading edge ribs 2. The opposite sides of the two fuselage leading edge ribs 2 are bolted to a second forward transverse frame 3 of the fuselage. A forward longitudinal frame 4 of the fuselage is bolted between the first forward transverse frame 1 and the second forward transverse frame 3. A first aft transverse frame 5 of the fuselage is provided on one side of the forward longitudinal frame 4. Both sides of the first aft transverse frame 5 are bolted to aft edge ribs 6. The opposite sides of the two aft edge ribs 6 are bolted to a second aft transverse frame 7 of the fuselage. A aft longitudinal frame 8 is bolted between the aft edge ribs 6 and the second aft transverse frame 7 of the fuselage. The surfaces of the second forward transverse frame 3 and the first aft transverse frame 5 are bolted to each other. An automatic centering device 9 is fixedly connected to the joint. A wing frame 10 is provided on the side opposite to the second front cross frame 3 and the first rear cross frame 5 of the fuselage. Wing joints 11 are provided on both sides of the inner cavity of the wing frame 10. A hexagonal nut 12 is fixedly connected to the inner cavity of the wing joint 11. A hexagonal anti-loosening washer 13 is fixedly connected to the surface of the hexagonal nut 12. An anti-loosening pin 14 is fixedly connected to one end of the inner cavity of the hexagonal nut 12. A wing-body positioning joint 15 is fixedly connected to one side of the wing joint 11 and is located on the outside of the wing frame 10. A wing-body mating bolt 16 is provided on one side of the wing-body mating bolt 16. An anti-loosening washer 17 is sleeved on the surface of the anti-loosening washer 17. A bushing 18 is provided on one side of the anti-loosening washer 17 and is sleeved on the surface of the wing-body mating bolt 16. The wing-body positioning joint 15 is fixedly connected to the other end of the inner cavity of the hexagonal nut 12.

[0021] Specifically, the automatic centering device 9 for the connector includes a docking plate 901. Two sets of docking plates 901 are provided, and the docking plates 901 are respectively fixedly connected to the side opposite to the second front cross frame 3 and the first rear cross frame 5 of the machine body. The docking plate 901 has a 902 opening, and the surface of the docking plate 901 has a positioning groove 903.

[0022] In this embodiment, the automatic centering device 9 of the joint is mainly used to enhance the strength and rigidity of the structure itself, and also to provide positioning for the installation of the wing.

[0023] Specifically, the surfaces of the second front cross frame 3 and the first rear cross frame 5 of the fuselage are each provided with two first docking holes 19. The diameters of the first docking holes 19 and the second docking holes 902 are the same. The positioning rail groove 903 is set as a raised arc-shaped structure, and the wing-body positioning joint 15 is adapted to the positioning rail groove 903.

[0024] In this embodiment: the cooperation of the first docking hole 19 and the second docking hole 902, with the same hole diameter, ensures that the automatic centering device 9 of the connector can pass smoothly through, thereby completing the precise installation and providing a reliable docking foundation for the subsequent installation of the structure, ensuring the stability and high precision of the overall assembly. The positioning groove 903 provides precise positioning support for the installation of the wing, improving the stability of the structure.

[0025] Specifically, the wing frame 10 includes a wing front spars 101, one side of which is fixedly connected to four wing ribs 102 by bolts, and the other side of the four wing ribs 102 is fixedly connected to a wing rear spars 103 by bolts.

[0026] In this embodiment, the wing frame 10 is designed to combine with the upper and lower skins to form a robust wing body, which effectively improves the overall strength and stability of the wing, while ensuring the aerodynamic performance and structural integrity of the wing, thus providing a reliable guarantee for the flight performance of the aircraft.

[0027] Specifically, the surfaces of the front spar 101 and the rear spar 103 of the wing are each provided with two large spar holes, and the large spar holes are adapted to the first docking hole 19 and the second docking hole 902.

[0028] In this embodiment: by setting the main beam hole, the main beam hole has the same diameter as the first docking hole 19 and the second docking hole 902, which can ensure that the structure is accurately inserted into it, thereby achieving a stable docking between the fuselage and the wing, improving the connection accuracy, enhancing the stability of the overall structure, ensuring a close fit between the fuselage and the wing, and further improving the overall strength and safety of the aircraft.

[0029] The working principle and usage process of this utility model are as follows: First, the user installs the front edge rib 2 of the fuselage on both sides of the first front horizontal frame 1 of the fuselage using bolts. Then, the user installs the second front horizontal frame 3 of the fuselage on the opposite side of the front edge rib 2 of the fuselage using bolts, thus completing the splicing of the front frame of the fuselage. After the assembled front frame of the fuselage is placed aside, the user then installs the rear edge rib 6 of the fuselage on both sides of the first rear horizontal frame 5 of the fuselage using bolts. Subsequently, the user installs the second rear horizontal frame 7 of the fuselage on the opposite side of the rear edge rib 6 of the fuselage using bolts, thus completing the splicing of the rear frame of the fuselage. At this time, the surfaces of the second front horizontal frame 3 and the first rear horizontal frame 5 of the fuselage are respectively provided with first mating holes 19, and the surface of the automatic centering device 9 of the connector is provided with second mating holes 902. Next, the user installs the automatic centering device 9 of the connector on the opposite side of the surfaces of the second front horizontal frame 3 and the first rear horizontal frame 5 of the fuselage, ensuring that the first mating holes 19 and the second mating holes 902 are aligned. Then, the user installs the automatic centering device 9 using bolts... The four wing ribs 102 are bolted to one side of the wing front spars 101, and the wing rear spars 103 is bolted to the other end of the four wing ribs 102. Next, wing joints 11 are installed in the corresponding inner cavities of the wing front spars 101 and the wing rear spars 103, so that the wing joints 11 align with the spars holes. Then, the user installs the wing-body positioning joints 15 on the outer sides of the wing front spars 101 and the wing rear spars 103, ensuring that the wing-body positioning joints 15 are installed in the inner cavity of the hexagonal nut 12. Then, the wing-body docking bolts 16, anti-loosening washers 17, and bushings 18 are installed into the inner cavity of the wing-body positioning joints 15, and the anti-loosening pins 14 are installed into the inner cavity of the hexagonal nut 12 to prevent loosening during use. Finally, the user aligns the assembled fuselage front frame and fuselage rear frame through the wing-body positioning joints 15, so that the spars holes align with the first docking hole 19 and the second docking hole 902, thereby completing the assembly of the aircraft frame.

[0030] It should be noted that in this paper, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

[0031] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Those skilled in the art to which this invention pertains can make various modifications and refinements without departing from the spirit and scope of the present invention. Therefore, the scope of protection of this invention shall be determined by the claims.

Claims

1. A composite wing eVTOL wing-body docking structure with interchangeability and automatic alignment, comprising a first forward transverse frame of the fuselage (1), characterized in that: Both sides of the first front transverse frame (1) of the fuselage are fixedly connected to the front edge ribs (2) of the fuselage by bolts. The opposite side of the two front edge ribs (2) of the fuselage is fixedly connected to the second front transverse frame (3) of the fuselage by bolts. The first front transverse frame (1) of the fuselage and the second front transverse frame (3) of the fuselage are fixedly connected to the front longitudinal frame (4) of the fuselage by bolts. The first rear transverse frame (5) of the fuselage is provided on one side. Both sides of the first rear transverse frame (5) of the fuselage are fixedly connected to the rear edge ribs (6) of the fuselage by bolts. The opposite side of the two rear edge ribs (6) of the fuselage is fixedly connected to the second rear transverse frame (7) of the fuselage by bolts. The rear edge ribs (6) of the fuselage and the second rear transverse frame (7) of the fuselage are fixedly connected to the rear longitudinal frame (8) of the fuselage by bolts. The surfaces of the second front transverse frame (3) and the first rear transverse frame (5) of the fuselage are fixedly connected to the joint automatic centering device (9) by bolts. The second front transverse frame (3) and the first rear transverse frame (5) of the fuselage are fixedly connected to the joint automatic centering device (9) of the fuselage by bolts. 5) An wing frame (10) is provided on one side of the opposite side. Wing connectors (11) are provided on both sides of the inner cavity of the wing frame (10). A hexagonal nut (12) is fixedly connected to the inner cavity of the wing connector (11). A hexagonal anti-loosening washer (13) is fixedly connected to the surface of the hexagonal nut (12). An anti-loosening pin (14) is fixedly connected to one end of the inner cavity of the hexagonal nut (12). A wing-body positioning connector (15) is fixedly connected to one side of the wing connector (11). The wing-body positioning joint (15) is located on the outside of the wing frame (10). A wing-body docking bolt (16) is provided on one side of the wing-body positioning joint (15). An anti-loosening washer (17) is fitted on the surface of the wing-body docking bolt (16). A bushing (18) is provided on one side of the anti-loosening washer (17), and the bushing (18) is fitted on the surface of the wing-body docking bolt (16). The wing-body positioning joint (15) is fixedly connected to the other end of the inner cavity of the hexagonal nut (12).

2. The composite wing eVTOL wing-body docking structure with interchangeability and automatic alignment according to claim 1, characterized in that: The automatic centering device (9) for the connector includes a docking plate (901). Two sets of docking plates (901) are provided, and the docking plates (901) are respectively fixedly connected to the side opposite to the second front cross frame (3) and the first rear cross frame (5) of the machine body. The docking plate (901) is provided with a second docking hole (902), and the surface of the docking plate (901) is provided with a positioning groove (903).

3. The composite wing eVTOL wing-body docking structure with interchangeability and automatic alignment according to claim 2, characterized in that: The second front cross frame (3) and the first rear cross frame (5) of the fuselage each have two first docking holes (19). The first docking holes (19) and the second docking holes (902) have the same diameter. The positioning rail groove (903) is set as a raised arc-shaped structure, and the wing-body positioning joint (15) is adapted to the positioning rail groove (903).

4. The composite wing eVTOL wing-body docking structure with interchangeability and automatic alignment according to claim 1, characterized in that: The wing frame (10) includes a wing front spars (101), one side of which is fixedly connected to four wing ribs (102) by bolts, and the other side of the four wing ribs (102) is fixedly connected to a wing rear spars (103) by bolts.

5. A composite wing eVTOL wing-body docking structure with interchangeability and automatic alignment according to claim 4, characterized in that: The surfaces of the front wing spall (101) and the rear wing spall (103) each have two large beam holes, and the large beam holes are adapted to the first docking hole (19) and the second docking hole (902).

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