A wing longitudinal and transverse frame connecting structure

Abstract

The utility model relates to the technical field of aircraft structure design, concretely is a kind of connecting structure of wing longitudinal framework and transverse framework.The connecting structure includes longitudinal framework and transverse framework, and it is crossed and is connected by connecting joint, and the longitudinal framework and transverse framework are I-shaped, can effectively improve the bending and shear capacity of framework, and the connecting joint is the trihedral connecting piece consisting of joint edge strip, joint web and joint edge strip boss, by increasing the connecting surface between longitudinal and transverse framework, effectively strengthen the connection strength of longitudinal and transverse framework, can guarantee the stable transmission of wing aerodynamic load when aircraft flies.

Description

Technical Field

[0001] This utility model relates to the field of aircraft structural design technology, specifically a connection structure between the longitudinal and transverse frames of a wing. Background Technology

[0002] During high-speed flight, the wings of an aircraft bear enormous aerodynamic loads, requiring the wing structure to possess excellent strength and rigidity. The basic load-bearing components of an aircraft wing include the longitudinal frame, transverse frame, and skin. The longitudinal frame is composed of spars, longitudinal walls, and stringers arranged along the wingspan, bearing all or most of the bending moment and shear force. The transverse frame is mainly composed of ribs, arranged perpendicular to the wingspan, whose function is to maintain the wing shape and transfer loads to the longitudinal frame. The rib webs are attached to the spars webs via tabs, braces, or direct riveting. Stringers pass through pre-designed notches in the ribs, and the edges of these notches are fixed to the ribs via tabs or rivets. The longitudinal struts are riveted to the upper and lower skins, while the ribs are connected to the longitudinal struts via rivets, together forming a torsional closed structure. The skin is a shaped component surrounding the wing frame, fixed to the frame with adhesives or fasteners to form the wing's aerodynamic shape.

[0003] The longitudinal and transverse frames of an aircraft are the main load-bearing structural components of the wing. Therefore, the connection between the longitudinal and transverse frames is particularly important. A good connection structure can ensure the transmission of aerodynamic loads and plays a crucial role in improving the overall structural strength and stiffness of the wing. Existing structures, in order to enhance the wing's resistance to bending and torsional loads, typically use L-beam or T-beam structures. However, due to the sharp angles in the design, coupled with stress concentration caused by abrupt changes in cross-section at rib slots and stringer notches, these structures are prone to fatigue cracking under cyclic loading. In addition, if there are manufacturing errors during frame assembly (such as excessive clearance), shims must be added or forced tightening is required, resulting in localized residual tensile stress. If the gap at the joint is too large, thicker shims are needed, which may increase the bending stress of the bolts. If the gap is too small, parts need to be ground, weakening the effective cross-section. Summary of the Invention

[0004] The purpose of this utility model is to overcome the defects of the prior art and provide a connection structure between the longitudinal and transverse frames of an airfoil, so as to solve the problem that the frame is prone to fatigue cracks due to structural design defects and the assembly interference caused by manufacturing errors.

[0005] The objective of this utility model is achieved through the following technical solution: This utility model provides a connection structure for a longitudinal and transverse wing frame. The connection structure includes a longitudinal frame and a transverse frame, both of which are I-shaped and are cross-connected by a connecting joint.

[0006] Furthermore, the longitudinal skeleton includes a longitudinal skeleton web, and the upper and lower ends of the longitudinal skeleton web are respectively connected to longitudinal skeleton flanges.

[0007] Furthermore, the transverse skeleton includes a transverse skeleton web, and the upper and lower ends of the transverse skeleton web are respectively connected to transverse skeleton flanges, with a certain assembly gap provided on the connecting side of the transverse skeleton flanges.

[0008] Furthermore, the longitudinal skeleton web and the transverse skeleton web are respectively provided with longitudinal skeleton weight reduction holes and transverse skeleton weight reduction holes.

[0009] Furthermore, the connecting joint is a three-sided connector, which includes a connector web. A first connecting plate and a second connecting plate are respectively connected to two adjacent sides of the connector web, and the adjacent ends of the first connecting plate and the second connecting plate are connected.

[0010] Furthermore, a boss is provided on the upper surface of the first connecting plate, and the boss is located in the assembly gap between the longitudinal skeleton edge strip and the transverse skeleton edge strip.

[0011] Furthermore, the connecting joint is connected to both the longitudinal and transverse skeletons via fasteners.

[0012] Compared with the prior art, the technical solution provided by the present invention has the following beneficial effects: (1) In this utility model, an I-shaped longitudinal and transverse frame is designed, the web provides shear strength, and the flange width enhances the buckling resistance, which can effectively improve the shear and bending resistance of the frame. A three-sided connector is designed to connect the longitudinal and transverse frames. By increasing the connection surface between the longitudinal and transverse frames, the connection strength of the longitudinal and transverse frames is strengthened, which can ensure the smooth transmission of wing aerodynamic loads during aircraft flight.

[0013] (2) In this utility model, a certain assembly gap is provided at the transverse frame edge strip, which can avoid assembly interference caused by processing errors. At the same time, a boss is provided at the connecting joint to compensate for the frame assembly gap, which can support the skin and enhance the stability of the wing skin.

[0014] (3) In this utility model, weight reduction holes are provided on the longitudinal skeleton web and the transverse skeleton web respectively, which greatly reduces the amount of material used and effectively reduces the weight of the web. Attached Figure Description

[0015] The accompanying drawings are incorporated in and form part of this specification, and together with the description serve to explain the principles of the invention.

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the connection structure between the longitudinal and transverse frames of the wing. Figure 2 This is a schematic diagram of the I-shaped longitudinal frame structure of the wing; Figure 3 This is a schematic diagram of the I-shaped transverse frame structure of the wing; Figure 4 A schematic diagram of the connection joint structure between the longitudinal and transverse frames of the wing; Figure 5 This is an enlarged schematic diagram of the connection structure between the longitudinal and transverse frames of the wing. In the figure: 1-Longitudinal skeleton; 2-Transverse skeleton; 3-Trihedral connector; 4-Longitudinal skeleton flange; 5-Longitudinal skeleton web; 6-Longitudinal skeleton weight reduction hole; 7-Transverse skeleton flange; 8-Transverse skeleton web; 9-Transverse skeleton weight reduction hole; 10-First connecting plate; 11-Joint web; 12-Boss; 13-Second connecting plate. Detailed Implementation

[0018] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatuses consistent with some aspects of the invention as detailed in the appended claims.

[0019] To enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Example

[0020] refer to Figure 1 This example proposes a connection structure for the longitudinal and transverse frames of an airfoil. The connection structure includes a longitudinal frame 1 and a transverse frame 2, which are cross-connected by a connecting joint.

[0021] In the above embodiments, to avoid the possibility of cracks appearing under cyclic loads due to sharp edges in the design of the skeleton structure, the longitudinal skeleton 1 and the transverse skeleton 2 are preferably I-shaped, so that the web provides shear strength and the flange width enhances the buckling resistance, which can effectively improve the shear and bending resistance of the skeleton.

[0022] refer to Figure 2 In the above embodiments, the longitudinal frame 1 includes a longitudinal frame web 5, and the upper and lower ends of the longitudinal frame web 5 are respectively connected to longitudinal frame flanges 4. Considering the problem of excessive wing load, longitudinal frame weight reduction holes 6 are provided on the longitudinal frame web 5 to effectively reduce the weight of the web.

[0023] refer to Figure 3 In the above embodiments, the transverse skeleton 2 includes a transverse skeleton web plate 8, and the upper and lower ends of the transverse skeleton web plate 8 are respectively connected to transverse skeleton flanges 7. A transverse skeleton weight reduction hole 9 is provided on the transverse skeleton web plate 8, and a certain assembly gap is provided on the connecting side of the transverse skeleton flanges 7.

[0024] refer to Figure 4 In the above embodiments, the connecting joint is a trihedral connector 3, which includes a connector web 11. The two adjacent sides of the connector web 11 are respectively connected to a first connecting plate 10 and a second connecting plate 13. The adjacent ends of the first connecting plate 10 and the second connecting plate 13 are connected. A boss 12 is provided on the upper surface of the first connecting plate 10.

[0025] refer to Figure 5 In the above embodiments, the joint web 11 is connected to the transverse skeleton web 8 by fasteners, the second connecting plate 13 is connected to the longitudinal skeleton web 6 by fasteners, and the first connecting plate 10 is connected to the longitudinal skeleton flange 4 and the transverse skeleton flange 7 by fasteners. The three-sided connector increases the connection surfaces between the longitudinal skeleton web, the transverse skeleton web, and the longitudinal and transverse skeleton flanges, effectively strengthening the connection strength of the longitudinal and transverse skeletons and ensuring the smooth transmission of wing aerodynamic loads during aircraft flight.

[0026] In the above embodiments, the boss 12 is located in the assembly gap between the longitudinal frame flange 4 and the transverse frame flange 7, which compensates for the frame assembly gap, avoids assembly interference problems caused by manufacturing errors, and can also support the skin and enhance the stability of the wing skin.

[0027] The above description is merely a specific embodiment of the present invention, enabling those skilled in the art to understand or implement the present invention. Various modifications to the above embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention.

[0028] It should be understood that the present invention is not limited to the content already described above, and various modifications and changes can be made without departing from its scope. The scope of the present invention is limited only by the appended claims.

Claims

1. A connection structure for a wing's longitudinal and transverse skeletons, characterized in that, The connection structure includes a longitudinal skeleton (1) and a transverse skeleton (2), both of which are I-shaped and are cross-connected by a connecting joint.

2. The connection structure between the longitudinal and transverse wing frames according to claim 1, characterized in that, The longitudinal skeleton (1) includes a longitudinal skeleton web (5), and the upper and lower ends of the longitudinal skeleton web (5) are respectively connected to longitudinal skeleton flanges (4).

3. The connection structure between the longitudinal and transverse wing frames according to claim 1, characterized in that, The transverse skeleton (2) includes a transverse skeleton web (8), and the upper and lower ends of the transverse skeleton web (8) are respectively connected to transverse skeleton flanges (7). A certain assembly gap is provided on the connecting side of the transverse skeleton flanges (7).

4. The connection structure between the longitudinal and transverse frames of a wing according to claim 2, characterized in that, The longitudinal skeleton web (5) is provided with longitudinal skeleton weight reduction holes (6).

5. The connection structure between the longitudinal and transverse wing frames according to claim 3, characterized in that, The transverse skeleton web plate (8) is provided with transverse skeleton weight reduction holes (9).

6. The connection structure between the longitudinal and transverse frames of a wing according to claim 1, characterized in that, The connecting joint is a trihedral connector (3), which includes a connector web (11). The two adjacent sides of the connector web (11) are respectively connected to a first connecting plate (10) and a second connecting plate (13), and the adjacent ends of the first connecting plate (10) and the second connecting plate (13) are connected.

7. The connection structure between the longitudinal and transverse wing frames according to claim 6, characterized in that, The upper surface of the first connecting plate (10) is provided with a boss (12), which is located in the assembly gap between the longitudinal skeleton edge strip (4) and the transverse skeleton edge strip (7).

8. The connection structure between the longitudinal and transverse frames of a wing according to claim 6, characterized in that, The trihedral connector (3) is connected to the longitudinal skeleton (1) and the transverse skeleton (2) by fasteners.

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