CN216443774U - An aircraft wing-fuselage connection structure - Google Patents

Abstract

The present application belongs to the technical field of connection design between aircraft wing and fuselage, and in particular relates to an aircraft wing and fuselage connection structure, comprising: a connecting strip, which is divided into two sections, wherein one section is a fuselage connecting section, and the section is abutted on the fuselage. On the fuselage, it is connected to the fuselage, and the other end is the wing connecting section, which is attached to the upper edge of the aircraft wing longitudinal beam; the ribs are connected to the connecting section of the fuselage, and are located at the connecting end of the fuselage facing away from the aircraft. One side of the body; the connecting edge, which is connected to the wing connecting section, is located on the side of the wing connecting section facing the aircraft wing stringer, and is connected to the web of the aircraft wing stringer.

Description

An aircraft wing-fuselage connection structure

technical field

The present application belongs to the technical field of connection design between aircraft wing and fuselage, and in particular relates to an aircraft wing and fuselage connection structure.

Background technique

The load borne by the aircraft wing is transmitted to the fuselage through the connection structure. The root of the aircraft wing is a plane, and the surface of the fuselage is a curved surface. The existing connection structure between the root of the aircraft wing and the fuselage is difficult to efficiently and reliably realize the The transfer of loads on an aircraft wing to the fuselage.

The present application is made in view of the existence of the above-mentioned technical defects.

It should be noted that the disclosure of the above background technology content is only used to assist the understanding of the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of the present patent application. If the filing date has been disclosed, the above background art should not be used to evaluate the novelty and inventive step of the present application.

SUMMARY OF THE INVENTION

The purpose of the present application is to provide an aircraft wing-fuselage connection structure to overcome or alleviate at least one of the known technical deficiencies.

The technical solution of this application is:

An aircraft wing-fuselage connecting structure, comprising:

The connecting strip is divided into two sections, one of which is the fuselage connecting section, which is attached to the fuselage and connected to the fuselage, and the other end is the wing connecting section, which is attached to the aircraft wing longitudinal beam. upper edge;

Ribs are connected to the connecting section of the fuselage and are located on the side of the connecting end of the fuselage facing away from the fuselage;

The connecting edge is connected to the wing connecting section, is located on the side of the wing connecting section facing the aircraft wing stringer, and is connected with the web of the aircraft wing stringer.

According to at least one embodiment of the present application, in the above-mentioned aircraft wing-fuselage connection structure, the fuselage connection section is connected to the fuselage skin through bolts.

According to at least one embodiment of the present application, in the above-mentioned aircraft wing-fuselage connection structure, the connecting edge is connected to the web of the aircraft wing stringer through bolts.

According to at least one embodiment of the present application, in the above-mentioned aircraft wing-fuselage connecting structure, the rib portion extends to the side of the wing connecting section facing away from the aircraft wing stringer.

According to at least one embodiment of the present application, in the above-mentioned aircraft wing-fuselage connection structure, the end of the fuselage connection section is beveled.

According to at least one embodiment of the present application, in the above-mentioned aircraft wing-fuselage connection structure, the thickness of the part of the wing connecting section abutting against the upper edge of the aircraft wing stringer is relatively thick, and the thickness of the part away from the upper edge of the aircraft wing stringer gradually becomes thinner .

According to at least one embodiment of the present application, in the above-mentioned aircraft wing-fuselage connection structure, the connecting strip, the rib, and the connecting edge are integrally machined.

According to at least one embodiment of the present application, in the above-mentioned aircraft wing-fuselage connection structure, the connecting bars, the ribs, and the connecting edges are made of aluminum alloy materials.

According to at least one embodiment of the present application, in the above-mentioned aircraft wing-fuselage connection structure, there are a plurality of connecting strips and their corresponding ribs and connecting edges, wherein each wing connecting section abuts against different aircraft wing longitudinal beams The upper edge of the connecting edge is connected to the web of the corresponding aircraft wing stringer.

Description of drawings

1 is a schematic diagram of an angle of an aircraft wing-fuselage connection structure provided by an embodiment of the present application;

2 is a schematic diagram of another angle of an aircraft wing-fuselage connection structure provided by an embodiment of the present application;

3 is a schematic diagram of the connection between the aircraft wing-fuselage connection structure provided by the embodiment of the present application;

in:

1-connecting strip; 2-rib; 3-connecting edge.

In order to better illustrate this embodiment, some parts in the drawings are omitted, enlarged or reduced, which do not represent the size of the actual product; in addition, the drawings are used for exemplary description, and their positional relationship is only for exemplary description and cannot be understood to limit this patent.

Detailed ways

In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further described in detail and completely with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only part of the present application. The examples are only used to explain the present application, but not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts may refer to the general design. If there is no conflict, the embodiments in the present application and the techniques in the embodiments Features can be combined with each other to obtain new embodiments.

Also, unless otherwise defined, technical or scientific terms used in the description of this application shall have the ordinary meaning as understood by those of ordinary skill in the art to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application to indicate orientation are only used To indicate the relative direction or positional relationship, rather than implying that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the described object changes, its relative positional relationship may also change accordingly. , so it cannot be construed as a limitation on this application. The terms "first", "second", "third" and similar terms used in the description of this application are only used for the purpose of description, to distinguish different components, and cannot be construed as indicating or implying relative importance. Words like "a," "an," or "the" and the like used in the description of this application should not be construed as an absolute limitation on the quantity, but should be construed as the presence of at least one. As used in the description of this application, "comprises" or "comprises" and similar words mean that the elements or things appearing before the word encompass the elements or things listed after the word and their equivalents, but do not exclude other elements or things.

In addition, it should be noted that, unless otherwise expressly specified and limited, the words "installed", "connected", "connected" and the like used in the description of this application should be understood in a broad sense, for example, the connection may be a fixed The connection can also be a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be an internal connection between two components. A skilled person can understand its specific meaning in this application according to specific circumstances.

The present application will be further described in detail below with reference to FIGS. 1 to 3 .

An aircraft wing-fuselage connecting structure, comprising:

The connecting strip 1 is divided into two sections, one of which is the fuselage connecting section, which is attached to the fuselage and connected to the fuselage, and the other end is the wing connecting section, which is attached to the aircraft wing stringer. the upper edge of;

Rib 2, connected to the connecting section of the fuselage, is located on the side of the connecting end of the fuselage facing away from the fuselage;

The connecting edge 3 is connected to the wing connecting section, is located on the side of the wing connecting section facing the aircraft wing stringer, and is connected to the web of the aircraft wing stringer.

For the aircraft wing-fuselage connection structure disclosed in the above embodiments, those skilled in the art can understand that it is designed so that the fuselage connecting section of the connecting bar 1 abuts on the fuselage and is connected with the fuselage, so that the connecting bar 1 The wing connecting section is attached to the upper edge of the aircraft wing stringer, and is connected to the web of the aircraft wing stringer with the connecting edge 3 connected to the side of the wing connecting section facing the aircraft wing stringer, so as to This realizes a reliable connection between the wings of the aircraft fuselage, and can efficiently transmit loads between the wings of the aircraft fuselage.

In some optional embodiments, in the above-mentioned aircraft wing-fuselage connection structure, the fuselage connection section is connected to the fuselage skin by bolts, and the specific number and position distribution of the bolts can be determined by the relevant technical personnel in the When applying the technical solutions disclosed in this application, it is determined according to the actual situation.

In some optional embodiments, in the above-mentioned aircraft wing-fuselage connection structure, the connecting edge is connected to the web of the aircraft wing longitudinal beam by bolts, and the specific number and position distribution of the bolts can be determined by the related art. When applying the technical solutions disclosed in the present application, the personnel should make determinations according to the actual situation.

In some optional embodiments, in the above-mentioned aircraft wing-fuselage connection structure, the rib 2 partially extends to the side of the wing connecting section facing away from the aircraft wing stringer, so as to strengthen the fuselage connected to the fuselage The load transfer effect between the connecting end and the connecting section of the wing connected to the web of the aircraft wing stringer through the connecting edge 3.

In some optional embodiments, in the above-mentioned aircraft wing-fuselage connection structure, the ends of the fuselage connection sections are beveled.

In some optional embodiments, in the above-mentioned aircraft wing-fuselage connection structure, the thickness of the part of the wing connecting section abutting against the upper edge of the aircraft wing stringer is thicker, and the thickness of the part away from the upper edge of the aircraft wing stringer gradually becomes thinner , in order to reduce the non-uniformity of bolt load distribution and reduce stress concentration.

In some optional embodiments, in the above-mentioned aircraft wing-fuselage connection structure, the connecting strip 1 , the rib 2 , and the connecting edge 3 are integrally formed.

In some optional embodiments, in the above-mentioned aircraft wing-fuselage connection structure, the connecting bars 1 , the ribs 2 , and the connecting edges 3 are made of aluminum alloy materials.

In some optional embodiments, in the above-mentioned aircraft wing-fuselage connection structure, there are multiple connecting bars 1 and their corresponding ribs 2 and connecting edges 3, wherein each wing connecting section is abutted against different aircraft. The upper edge of the wing stringer, the connecting edge 3 is connected with the web of the corresponding aircraft wing stringer.

The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the various embodiments can be referred to each other.

So far, the technical solutions of the present application have been described with reference to the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, without departing from the principles of the present application. Under the premise that those skilled in the art can make equivalent changes or replacements to the relevant technical features, the technical solutions after these changes or replacements will fall within the protection scope of the present application.

Claims (9)

1. An aircraft wing-fuselage connection structure, comprising:

the connecting strip (1) is divided into two sections, wherein one section is a fuselage connecting section which is attached to the fuselage and connected with the fuselage, and the other end is a wing connecting section which is attached to the upper edge of a wing longitudinal beam of the airplane;

the rib (2) is connected to the machine body connecting section and is positioned on one side of the machine body connecting end back to the machine body;

and the connecting edge (3) is connected to the wing connecting section, is positioned on one side of the wing connecting section, which faces to the airplane wing longitudinal beam, and is connected with the web of the airplane wing longitudinal beam.

2. The aircraft wing-to-body connection of claim 1,

the fuselage connection section is connected to the fuselage skin through a bolt.

3. The aircraft wing-to-body connection of claim 1,

the connecting edges are connected to the web plate of the airplane wing longitudinal beam through bolts.

4. The aircraft wing-to-body connection of claim 1,

the rib (2) partially extends to one side of the wing connecting section, which faces away from a longitudinal beam of the airplane wing.

5. The aircraft wing-to-body connection of claim 1,

and the end part of the machine body connecting section is chamfered.

6. The aircraft wing-to-body connection of claim 1,

the thickness of the part of the wing connecting section, which is attached to the upper edge of the airplane wing longitudinal beam, is thicker, and the thickness of the part, which is far away from the upper edge of the airplane wing longitudinal beam, is gradually thinner.

7. The aircraft wing-to-body connection of claim 1,

the connecting strip (1), the ribs (2) and the connecting edges (3) are integrally formed.

8. The aircraft wing-to-body connection of claim 1,

the connecting strip (1), the ribs (2) and the connecting edges (3) are made of aluminum alloy materials.

9. The aircraft wing-to-body connection of claim 1,

the connecting strips (1) and the corresponding ribs (2) and connecting edges (3) are multiple, wherein each wing connecting section is attached to the upper edges of different airplane wing stringers, and the connecting edges (3) are connected with webs of the corresponding airplane wing stringers.

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