Airplane and wing-fuselage connection structure

Abstract

The application relates to the field of aircraft technology and discloses an aircraft and a wing-body connecting structure thereof. The wing-body connecting structure comprises a wing body, the wing body comprising a first surface, a plurality of plug-in parts being arranged on the first surface; a body, the body comprising a second surface, a plurality of plug-in holes corresponding to the plug-in parts one by one being arranged on the second surface, and a corresponding plug-in channel being formed in the body by the plug-in holes; and a plurality of fixing assemblies, the fixing assemblies being configured to prevent the plug-in parts from moving in the corresponding plug-in channels after the plug-in parts are inserted into the plug-in channels through the corresponding plug-in holes, and the first surface and the second surface being attached to each other. The wing-body connecting structure can realize quick disassembly and assembly of the wing body and the body, saves time and effort, and reduces transportation cost and maintenance cost.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft, in particular to an aircraft and a wing-body connecting structure thereof. BACKGROUND

[0002] At present, the wing and the fuselage of an aircraft are usually assembled as a whole. For a large aircraft, it is very inconvenient to transport the aircraft, and the transportation cost is high. In addition, some designs are made in a detachable manner, but the assembly process is complicated and time-consuming. CONTENT OF THE UTILITY MODEL

[0003] The present application aims to provide an aircraft and a wing-body connecting structure thereof. The wing-body connecting structure can realize quick disassembly and assembly of the wing and the fuselage, save time and effort, and reduce transportation and maintenance costs.

[0004] To solve the above technical problems, the present application provides a wing-body connecting structure, comprising: a wing body, the wing body comprising a first surface, the first surface being provided with a plurality of plug-in parts; a fuselage body, the fuselage body comprising a second surface, the second surface being provided with a plurality of plug-in holes corresponding to the plug-in parts one by one, and a plug-in channel corresponding to the plug-in hole being formed in the fuselage body; and a plurality of fixing components, the fixing components being configured to prevent the plug-in parts from moving in the plug-in channel corresponding to the plug-in parts after the plug-in parts are inserted into the plug-in channel corresponding to the plug-in hole, and to make the first surface and the second surface adhere to each other.

[0005] The present application provides an aircraft, comprising the wing-body connecting structure described above.

[0006] Optionally, the first surface is further provided with at least one pair of positioning columns, the second surface is provided with positioning holes corresponding to the at least one pair of positioning columns one by one, and the positioning columns are configured to pass through the corresponding positioning holes on the second surface when the plug-in parts are inserted into the plug-in holes corresponding to the plug-in parts.

[0007] Optionally, the fixing components are further configured to release the plug-in parts 3 after the plug-in parts are inserted into the plug-in channel corresponding to the plug-in hole, so that the plug-in parts are separated from the plug-in channel and the first surface and the second surface are separated from each other.

[0008] Optionally, the fixing components comprise a plug pin and a stopper, the plug pin is configured to pass through and connect the wing body and the fuselage body, and the stopper is arranged on the fuselage body and can be telescopically connected to the plug pin to limit the relative movement between the plug pin and the fuselage body, thereby connecting the wing body and the fuselage body.

[0009] Optionally, the stopper is arranged on the outer sidewall of the insertion channel of the fuselage body, the stopper comprises a telescopic part, and the insertion pin comprises an insertion pin socket, the telescopic part is configured to be inserted into the insertion pin socket to lock the insertion pin.

[0010] Optionally, a reinforcing plate is further arranged on the outer sidewall of the insertion channel, and the insertion pin sequentially passes through the reinforcing plate, the fuselage body and the wing body to connect the wing body and the fuselage body.

[0011] Optionally, the reinforcing plate is made of glass fiber.

[0012] Optionally, the insertion part comprises a main insertion part and a sub insertion part, the main insertion part comprises a pair of main serial holes, and the sub insertion part comprises a sub serial hole.

[0013] Optionally, the main insertion part is connected by a pair of insertion pins inserted into the main serial holes after entering the corresponding insertion channel, and the sub insertion part is connected by an insertion pin inserted into the sub serial hole.

[0014] The wing-fuselage connecting structure of the present application can realize quick disassembly and assembly of the wing-fuselage, save time and effort, and reduce transportation and maintenance costs. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 A structure schematic diagram of the wing-fuselage connecting structure of the present application is shown;

[0016] Figure 2 A structure schematic diagram of the wing-fuselage connecting structure of the present application before connection is shown;

[0017] Figure 3 A structure schematic diagram of the fixing assembly of the fastening connecting piece of the present application is shown. DETAILED DESCRIPTION

[0018] The following embodiments further illustrate the technical solutions of the present application. It can be understood that the specific embodiments described herein are only used to explain the present application. In addition, it should be noted that, for the convenience of description, only parts related to the present application are shown in the drawings, not all.

[0019] In the description of the present application, it should be noted that, unless otherwise explicitly specified and limited, the terms "mounting", "connection" and "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection; it can be mechanical connection, or electrical connection; it can be direct connection, or indirect connection through intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0020] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0021] Embodiments of this application are described below with reference to the accompanying drawings, such as Figure 1 and Figure 2 As shown, the wing-fuselage connection structure of this application embodiment includes: a wing body 1, a fuselage body 2, and a plurality of fixing components 4. The wing body 1 includes a first surface 10, on which a pair of insertion portions 3 are provided. The fuselage body 2 includes a second surface 20, on which a pair of insertion holes (not shown in the figure) corresponding one-to-one with the insertion portions 3 are provided, extending from the pair of insertion holes into the fuselage body 2 to form corresponding insertion channels 21T and 22T respectively. After the pair of insertion portions 3 are inserted into the insertion channels 21T and 22T respectively through the corresponding insertion holes, the fixing components 4 can prevent the pair of insertion portions 3 from moving within the corresponding insertion channels 21T and 22T, and make the first surface 10 and the second surface 20 fit together.

[0022] Specifically, the wing body 1 includes a main wing spars 11 and secondary wing spars 12, which are parallel to each other to avoid interference and simplify installation. The main wing spars 11 and secondary wing spars 12 extend from the interior of the wing body 1 to form corresponding main insertion portions 31 and secondary insertion portions 32. The main insertion portion 31 includes a pair of main connecting holes 310, and the secondary insertion portion 32 includes a secondary connecting hole 320. The fuselage body 2 includes a fuselage main spars 21 and a fuselage secondary spars 22. The internal beam boxes of the main fuselage main spars 21 and the fuselage secondary spars 22 respectively form a pair of insertion channels 21T and 22T, which communicate with the outside through insertion holes on the second surface 20. The fixing assembly 4 includes a pin 41 and a stop 42. After the main connector 31 and the auxiliary connector 32 are inserted into the corresponding connector channels 21T and 22T through the corresponding connector holes, each pin 41 can pass through the outer side wall 23 of the main fuselage beam 21 and the side wall of the auxiliary fuselage beam 22, and pass through the main connection hole 310 and the auxiliary connection hole 320, respectively, and finally exit from the other side of the main fuselage beam 21 and the auxiliary fuselage beam 22, thereby connecting the wing body 1 and the fuselage body 2. The cooperation between the pin 41 and the stop 42 can reduce the shear force, vibration force and tension between the wing and the fuselage. Each stop 42 is respectively disposed on the outer wall of the insertion channels 21T and 22T of the fuselage body 2. The stop 42 is provided with a telescopic portion, and the pin 41 includes a pin slot. The telescopic portion of the stop 42 can telescopically engage with the pin slot to restrict relative movement between the pin 41 and the fuselage body 2, thereby connecting the wing body 1 and the fuselage body 2. Alternatively, the telescopic portion can telescopically disengage from the pin slot, thereby releasing the pin 41, allowing each insertion portion 3 to disengage from the insertion channels 21T or 22T, and separating the first surface 10 and the second surface 20. The wing-fuselage connection structure of this application enables rapid assembly and disassembly of the wing and fuselage, saving time and effort, and reducing transportation and maintenance costs. It should be noted that, based on the principle that three points determine a plane, in this embodiment, the plane defined by a pair of main connecting holes 310 of the main connector 31 and a secondary connecting hole 320 of the secondary connector 32 is used to lock the wing body 1 and the fuselage body 2. However, the actual connection is not limited to the above three-point position. The plane defined by the fixing components corresponding to the three points can achieve stable and smooth installation. The main connector 31 is connected to the wing main sparsity 11 to bear a larger portion of the shear force between the wing and fuselage. The secondary connector 32 is connected to the wing secondary sparsity 12 to bear the remaining portion of the shear force. The secondary connector 32 is shorter and smaller than the main connector 31, mainly to prevent torsion between the wing and fuselage.

[0023] Furthermore, the first surface 10 is provided with at least a pair of positioning posts 5, and the second surface 20 is provided with at least a pair of positioning holes (not shown in the figure) corresponding one-to-one with the positioning posts 5. When the insertion part 3 is inserted into the corresponding insertion hole, the positioning post 5 can pass through the corresponding positioning hole on the second surface 20. After the positioning post 5 is inserted into the corresponding positioning hole, the main serial connection hole 310 and the secondary serial connection hole 320 are aligned with the opening of the outer wall 23 of the main beam 21 and the opening of the side wall of the secondary beam 22 of the fuselage, respectively. This defines the position of the pair of insertion parts 3 in the length and width directions of the insertion channel 21T or 22T, thereby reducing the installation difficulty and saving time and effort. At the same time, the positioning post 5 transmits the sway of the wing during flight to the fuselage, reducing the strain deformation of the wing under vibration.

[0024] Furthermore, such as Figure 3 As shown, a reinforcing plate 24 is also provided on the outer wall 23 of the insertion channel 21T. The pin 41 passes sequentially through the reinforcing plate 24, the outer wall 23, the main connection hole 310 of the insertion part 3, and the other side wall opposite to the outer wall 23, so as to connect the wing body 1 and the fuselage body 2, thereby enhancing the connection strength. This reduces the vibration force transmitted from the wing to the fuselage and reduces the influence of the shear force between the wing and the fuselage. The reinforcing plate 24 is preferably made of glass fiber. This application uses local glass fiber reinforcement at the insertion pin location. Glass fiber has better toughness than carbon fiber and can reduce the vibration transmitted from the wing to the fuselage to a certain extent.

[0025] This application provides an aircraft including the aforementioned wing-fuselage connection structure. The wing-fuselage connection structure of this application enables rapid assembly and disassembly of the wing and fuselage, saving time and effort, and reducing transportation and maintenance costs.

[0026] The above embodiments are merely illustrative of the principles and effects of this application. Any person skilled in the art can modify or alter the above embodiments without departing from the purpose of this application. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the purpose disclosed in this application should still be covered by the claims of this application.

Claims

1. A wing-fuselage connection structure, characterized in that, include: The wing body (1) includes a first surface (10) on which a plurality of insertion parts (3) are provided; The fuselage body (2) includes a second surface (20), which is provided with a plurality of plug holes corresponding to the plug-in part (3) and extends from the plug holes into the fuselage body (2) to form corresponding plug-in channels (21T, 22T). Multiple fixing components (4) are configured to prevent the plug (3) from moving within the corresponding plug channel (21T, 22T) after the plug (3) is inserted through the corresponding plug hole, and to make the first surface (10) and the second surface (20) fit together.

2. The wing-fuselage connection structure according to claim 1, characterized in that, The first surface (10) is provided with at least one pair of positioning posts (5), and the second surface (20) is provided with positioning holes corresponding to the at least one pair of positioning posts (5). The positioning posts (5) are configured to pass through the corresponding positioning holes on the second surface (20) when the plug-in part (3) is inserted into the corresponding plug-in hole.

3. The wing-fuselage connection structure according to claim 1, characterized in that, The fixing component (4) is also configured to release the plug (3) after the plug (3) is inserted into the corresponding plug channel (21T, 22T), so that the plug (3) leaves the plug channel (21T, 22T) and the first surface (10) and the second surface (20) are separated from each other.

4. The wing-fuselage connection structure according to claim 1, characterized in that, The fixing component (4) includes a pin (41) and a stop (42). The pin (41) is configured to pass through and connect the wing body (1) and the fuselage body (2). The stop (42) is disposed on the fuselage body (2) and can extend and retract through and connect the pin (41) to restrict relative movement between the pin (41) and the fuselage body (2), thereby connecting the wing body (1) and the fuselage body (2).

5. The wing-fuselage connection structure according to claim 4, characterized in that, The stop (42) is disposed on the outer wall (23) of the insertion channel (21T, 22T) of the fuselage body (2). The stop (42) includes a telescopic part, and the pin (41) includes a pin slot. The telescopic part is configured to be able to be inserted into the pin slot to lock the pin (41).

6. The wing-fuselage connection structure according to claim 5, characterized in that, A reinforcing plate (24) is also provided on the outer wall (23) of the insertion channel (21T, 22T). The pin (41) passes through the reinforcing plate (24), the fuselage body (2) and the wing body (1) in sequence, so that the wing body (1) is connected to the fuselage body (2).

7. The wing-fuselage connection structure according to claim 6, characterized in that, The reinforcing plate (24) is made of glass fiber.

8. The wing-fuselage connection structure according to claim 7, characterized in that, The plug-in part (3) includes a main plug-in part (31) and a secondary plug-in part (32). The main plug-in part (31) includes a pair of main serial holes (310), and the secondary plug-in part (32) includes a secondary serial hole (320).

9. The wing-fuselage connection structure according to claim 8, characterized in that, After the main connector (31) enters the corresponding connector channel (21T, 22T), a pair of pins (41) are inserted into the main serial hole (310) to form a connection. The secondary connector is connected by inserting one pin (41) into the secondary serial hole (320).

10. An aircraft, characterized in that, Includes the wing-fuselage connection structure as described in any one of claims 1-9.

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