A plug-in leading edge of a strake wing

Abstract

This invention belongs to the field of aircraft structural design, specifically relating to a plug-in leading edge of a strake wing. It includes a leading edge of the strake wing, an inner sidewall, an outer sidewall, and a frame. The inner sidewall is attached to the outer surface of the frame. The leading edge of the strake wing is integrally formed, including an upper wing surface, a lower wing surface, a flyedge, a cavity, and a wing slat. The area on the inner sidewall that mates with the flyedge has a recess. The upper wing surface is fused with the edge of the flyedge, which is locally widened. The area on the inner sidewall that mates with the upper wing surface has a groove for mates with the widened area on the flyedge. The leading edge of the strake wing is positioned between the inner and outer sidewalls. The outer sidewall is riveted to the frame. This structural form has good rigidity and is easy to connect to the fuselage sidewalls. It is not easily deformed under aerodynamic loads, thus better maintaining the aerodynamic shape of the leading edge of the strake wing.

Description

Technical Field

[0001] This invention belongs to the field of aircraft structural design, specifically relating to a plug-in leading edge of a strake wing. Background Technology

[0002] The leading edges of strakes are mounted on both sides of the fuselage to increase lift. Designing the leading edge structure of strakes is one of the challenges in aircraft structural design. On one hand, the small size of the leading edge makes the design of its rigidity and connections difficult. On the other hand, the shape of the leading edge is sensitive to airflow variations, thus requiring a high degree of aerodynamic control. Currently, a common structural form involves a slender edge strip along the outer edge of the strake, with the leading edge itself machined as part of this strip. This edge strip connects to the upper and lower wing skins and the bulkhead. The leading edge, due to its small size, cannot be designed with connection points. The leading edge is designed to fit snugly to the fuselage, resulting in a cantilever structure that relies solely on its own rigidity to maintain its shape. This structure is prone to warping or deformation under aerodynamic loads, making it difficult to meet the aerodynamic requirements of the leading edge. Summary of the Invention

[0003] Purpose of the invention

[0004] To address the problems existing in cantilever strake leading edge structures, a plug-in strake leading edge structure is proposed. This structure can effectively improve structural stiffness and facilitate connection.

[0005] Technical solution

[0006] A plug-in leading edge of a strake wing includes a leading edge of the strake wing, an inner sidewall panel, an outer sidewall panel, and a frame. The inner sidewall panel is attached to the outer surface of the frame. The leading edge of the strake wing is integrally formed and includes an upper wing surface, a lower wing surface, a fly edge, a cavity, and a flange. The area on the inner sidewall panel that mates with the fly edge has a recess. The upper wing surface is fused with the edge of the fly edge, and the fly edge is locally widened. The area on the inner sidewall panel that mates with the upper wing surface has a groove for mates with the widened area on the fly edge. The leading edge of the strake wing is disposed between the inner sidewall panel and the outer sidewall panel. The outer sidewall panel is fixed to the frame by riveting.

[0007] Furthermore, the leading edge of the wing, the inner sidewall, the outer sidewall, and the frame are made of aluminum alloy.

[0008] Furthermore, the length of the wingtip should ensure that the tip of the leading edge of the strake is flush with the edge;

[0009] Furthermore, the thickness of the burr should be as thin as possible while ensuring machinability;

[0010] Furthermore, the cavity is specifically the area enclosed by the upper wing surface and the lower wing surface;

[0011] Furthermore, the cavity should be as large as possible while meeting structural strength requirements, in order to further reduce structural weight.

[0012] Furthermore, the edge strip includes an upper edge strip and a lower edge strip;

[0013] Furthermore, the upper edge strip overlaps with the rear upper wing surface and is fixed by riveting;

[0014] Furthermore, the lower edge strip overlaps with the rear lower wing surface and is fixed by riveting;

[0015] The beneficial effects of this application are as follows:

[0016] Conventional leading-edge extension designs, where the leading edge is integrally machined as part of the edge strip, suffer from limited design flexibility due to structural space and assembly constraints. This invention presents a plug-in leading-edge extension structure where the leading edge and edge strip are designed separately. The lower part of the leading edge features a winglet with an L-shaped structure formed by the winglet and the lower wing surface. Compared to the conventional cantilever structure, this design offers better structural rigidity and facilitates connection to the fuselage sidewalls. It is also less prone to deformation under aerodynamic loads, better preserving the aerodynamic shape of the leading edge. Upper and lower edge strips at the rear of the leading edge facilitate connection to the rear upper and lower wing surface structures. A hollow structure within the leading edge effectively reduces structural weight. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the leading edge assembly of the strake wing.

[0018] Figure 2 This is a schematic diagram of the outer edge of the leading edge of the strake.

[0019] Figure 3 This is a schematic diagram of the inner side of the leading edge of the strake wing.

[0020] Figure 4 This is a schematic diagram of the inner wall panel.

[0021] Figure 5 This is a exploded view of the leading edge of the strake wing.

[0022] Among them: leading edge of the wing 1, inner sidewall 2, outer sidewall 3, and frame 4. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below. In the examples, the same or similar reference numerals denote the same or similar components or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of this invention. The embodiments described below with reference to reference are exemplary and intended to explain this invention, and should not be construed as limiting the invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention. The embodiments of this invention will be described in detail below.

[0024] The components of the plug-in leading edge structure of the strut wing are: leading edge wing 1, inner sidewall 2, outer sidewall 3, and frame 4, as shown. Figure 1 As shown.

[0025] The plug-in leading edge structure of the strake wing includes an upper wing surface 11, a lower wing surface 12, a flange 13, a cavity 14, and a flange 15. The flange 13 is used for connection, and it forms an L-shaped structure with the lower wing surface 12, which can effectively improve the structural rigidity of the leading edge wing 1. To reduce weight, an internal cavity 14 is provided. A flange 15 is provided to facilitate the connection between the leading edge wing 1 and the rear structure. Figure 2 and Figure 3 As shown. The inner wall panel 2 has a recess 21, as... Figure 3 As shown. The inner side panel 2 is the internal connecting frame, providing support for the connection of the leading edge 1 of the strake wing. The outer side panel 3 is the aircraft skin, used to maintain the fuselage shape, and the frame 4 is used to fix the inner side panel 2 and the outer side panel 3.

[0026] First, attach and position the inner side panel 2 to the frame 4. Then, attach and position the leading edge 1 fly 13 of the strake wing 1 to the recessed area 21 of the inner side panel 2, aligning the upper surface 22 of the inner side panel with the upper wing surface 11 of the leading edge wing to ensure the aircraft's shape. Next, attach and position the outer side panel 3 to the outer side of the fly 13, i.e., insert the leading edge 1 fly 13 of the strake wing 1 between the inner side panel 2 and the outer side panel 3. To meet waterproof sealing requirements, apply sealant to the surfaces where the fly 13 is attached to the inner side panel and the outer side panel 3. Finally, use fasteners to secure the parts at each attachment point. At least one fastener must be used at each of the four attachment points (the overlapping areas of the leading edge wing 1, inner side panel 2, outer side panel 3, and frame 4) to facilitate the transfer of aerodynamic loads from the leading edge wing 1 to the frame.

[0027] The insert-type leading edge of the wing includes a leading edge 1, an inner sidewall panel 2, an outer sidewall panel 3, and a frame 4, wherein the inner sidewall panel 2 is attached to the outer surface of the frame 4.

[0028] The leading edge 1 of the wing is integrally formed and includes an upper wing surface 11, a lower wing surface 12, a fly edge 13, a cavity 14, and a wing strip 15. The area on the inner wall panel 2 that mates with the fly edge 13 is recessed. The upper wing surface 11 and the fly edge 13 are fused together at their edges. The fly edge 13 is partially widened. The area on the inner wall panel 2 that mates with the upper wing surface 11 is provided with a groove. The groove is used to mate with the widened area on the fly edge 13. The leading edge 1 of the wing is located between the inner wall panel 2 and the outer wall panel 3. The outer wall panel 3 is fixed to the frame 4 by riveting.

[0029] In one embodiment of the present invention, the leading edge 1 of the wing, the inner sidewall 2, the outer sidewall 3, and the frame 4 are made of aluminum alloy.

[0030] In one embodiment of the present invention, the length of the wing edge 13 should ensure that the tip of the leading edge 1 of the strake wing is flush with the edge.

[0031] In one embodiment of the present invention, the thickness of the flash 13 should be thinner while ensuring machinability;

[0032] In one embodiment of the present invention, the cavity 14 is specifically the area enclosed by the upper wing surface 11 and the lower wing surface 12;

[0033] In one embodiment of the present invention, the cavity 14 should be as large as possible while meeting the structural strength requirements, in order to reduce the structural weight in one embodiment of the present invention.

[0034] In one embodiment of the present invention, the rim strip 15 includes an upper rim strip and a lower rim strip;

[0035] In one embodiment of the present invention, the upper edge strip overlaps with the rear upper wing surface and is fixed by riveting;

[0036] In one embodiment of the present invention, the lower edge strip overlaps with the rear lower wing surface and is fixed by riveting;

[0037] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein. The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Within the spirit and principles of the present invention, any person skilled in the art may use the disclosed technical content to make changes or modifications to create equivalent embodiments applicable to other fields. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention, any modifications, equivalent substitutions, improvements, etc., should be included within the protection scope of the present invention.

Claims

1. A plug-in leading edge of a strake wing, characterized in that, The system includes a leading edge of a strake, an inner sidewall, an outer sidewall, and a frame. The inner sidewall is attached to the outer surface of the frame. The leading edge of the strake is integrally formed and includes an upper wing surface, a lower wing surface, a fly edge, a cavity, and a flange. The area on the inner sidewall that mates with the fly edge has a recess. The upper wing surface merges with the edge of the fly edge, which is locally widened. The area on the inner sidewall that mates with the upper wing surface has a groove for mates with the widened area on the fly edge. The leading edge of the strake is positioned between the inner and outer sidewalls. The outer sidewall is riveted to the frame. The length of the fly edge... The leading edge of the strake should be flush with the tip; the thickness of the wingtip should be sufficient for machining performance while being as thin as possible; the wingtip is used for connection, and the wingtip and the lower wing surface form an L-shaped structure, with the wingtip of the leading edge inserted between the inner and outer side panels; the cavity is specifically the area enclosed by the upper and lower wing surfaces; the cavity should be as large as possible while meeting structural strength requirements; the strake includes an upper strake and a lower strake; the upper strake overlaps with the rear upper wing surface and is fixed by riveting; the lower strake overlaps with the rear lower wing surface and is fixed by riveting.

2. The leading edge of the plug-in strut wing as described in claim 1, characterized in that, The leading edge, inner sidewall, outer sidewall, and frame of the wing are made of aluminum alloy.

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