CN218617159U

CN218617159U - Double-beam type wing main box section structure

Info

Publication number: CN218617159U
Application number: CN202223287561.3U
Authority: CN
Inventors: 李俊; 吴长锋; 王县委; 马婷婷; 王亦宁; 曹飞; 丛朋雨; 康瑞良; 张辰
Original assignee: Jiangsu Xinyang New Material Co ltd
Current assignee: Jiangsu Xinyang New Material Co ltd
Priority date: 2022-12-08
Filing date: 2022-12-08
Publication date: 2023-03-14
Anticipated expiration: 2032-12-08

Abstract

The utility model discloses a two beam type wing owner box section structures in the aircraft wing field comprises front-axle beam, back-axle beam, last covering, covering and rib down, and front-axle beam, back-axle beam, covering and rib are the integrated into one piece structure down, and the laminating of rib is at the front-axle beam, back-axle beam, the inboard of covering down, goes up the covering and installs on the integrated into one piece structure, the utility model discloses reduce the assembly work load, reduced the assembly degree of difficulty, the use of the standard parts such as bolt that have significantly reduced simultaneously has reduced later stage inspection and maintenance work load.

Description

Double-beam type wing main box section structure

Technical Field

The utility model relates to an aircraft wing technical field, in particular to wing owner box section structure.

Background

The traditional double-beam type wing main box section structure consists of a front beam, a rear beam, an upper skin, a lower skin and ribs. As shown in fig. 4, the original main wing box is formed by mechanically connecting an upper skin, a lower skin, a front beam, a rear beam and a wing rib, and during actual production and assembly, the positions of all components need to be positioned by using a fixture, and then the components are connected and fixed by using a self-plugging rivet or a high-locking bolt. The structural form has the advantages of multiple parts, complex assembly process, higher requirement on the precision of the tool fixture frame, lower overall structural strength, looseness of bolts caused by aerodynamic load in long-term flight due to the use of a large number of connecting pieces such as the bolts and the like, and large later-stage inspection and maintenance amount.

SUMMERY OF THE UTILITY MODEL

To exist not enough among the prior art, the utility model provides a two beam type wing owner box section structures has reduced the assembly work load, has reduced the assembly degree of difficulty, the use of the standard component such as bolt that has significantly reduced simultaneously, has reduced later stage inspection maintenance work load.

The purpose of the utility model is realized like this: a main box section structure of a double-beam type wing comprises a front beam, a rear beam, an upper skin, a lower skin and a wing rib, wherein the front beam, the rear beam, the lower skin and the wing rib are of an integrally formed structure, the wing rib is attached to the inner sides of the front beam, the rear beam and the lower skin, and the upper skin is installed on the integrally formed structure.

As a further limitation of the present invention, the top of the wing rib is processed with a notch, and the inner surface of the upper skin is provided with a rib which is clamped into the notch.

As a further limitation of the utility model, the ribs are of a sandwich structure, and the foam core is arranged inside the ribs and the composite material skin is arranged outside the ribs.

As a further limitation of the present invention, the upper skin is fixed to the integral molding structure by a fastener.

As a further limitation of the present invention, the front beam, the rear beam, the upper skin, the lower skin, and the wing rib are made of composite materials.

Compared with the prior art, the beneficial effects of the utility model reside in that:

the utility model has the advantages that the front middle beam, the rear beam, the lower skin and the wing ribs are of an integral forming structure, so that the assembly workload is reduced, the assembly difficulty is reduced, the tooling frame is simplified, the use of standard parts such as bolts is greatly reduced, and the later inspection and maintenance are convenient; the design has the characteristics of simple structural assembly, less assembly quantity, high safety, high overall strength and good sealing property.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.

Fig. 1 is a schematic view of the three-dimensional structure of the present invention.

Fig. 2 is a schematic view of the overall forming structure of the present invention.

Fig. 3 is a schematic view of the structure of the upper skin of the present invention.

Fig. 4 is a schematic structural diagram of a main box section of a dual-beam wing in the prior art.

Wherein, 100 front beams, 200 rear beams, 300 upper skins, 301 ribs, 400 lower skins, 500 ribs and 501 notches.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Examples

The main box section structure of the double-beam wing shown in fig. 1-3 comprises a front beam 100, a rear beam 200, an upper skin 300, a lower skin 400 and a rib 500, wherein the front beam 100, the rear beam 200, the lower skin 400 and the rib 500 are integrally formed, the rib 500 is attached to the inner sides of the front beam 100, the rear beam 200 and the lower skin 400, and the upper skin 300 is installed on the integrally formed structure.

Specifically, ten ribs 500 are designed in the embodiment, but the design is not limited to this, and the adjustment can be performed according to actual needs, the lower skin 400, the front beam 100, the rear beam 200, and the ribs 500 are integral pieces, the thickness of the middle area is 10mm, the thickness gradually decreases to 6mm from both sides, only the upper skin 300 is assembled with the integral molding structure in the assembling process, and the upper skin 300 and the integral molding structure are fixedly connected by using connecting pieces such as bolts and pull nails.

It should be noted that, the front beam 100, the back beam 200, the lower skin 400 and the wing rib 500 are all made of composite materials, prepreg is adopted for paving and curing in the molding process, the paving process is the same as the conventional paving process, the front beam 100, the back beam 200 and the lower skin 400 are paved on a designed mould, after precuring, the wing rib 500 paving mould is placed on the inner side of the prepreg after precuring, the wing rib 500 prepreg is paved, after paving, the prepreg is sent into a hot pressing tank for curing, and an integral molding structure is obtained after demoulding, when assembling, the integral molding structure is fixedly connected with the upper skin 300 only by adopting a fastener, when an airplane flies, the upper and lower skins 400 of the wing bear pneumatic load and concentrated force load, and then force is transmitted to the wing rib 500 and the front and back beams 200 through connecting pieces such as bolts, nails and the like, and is used as a direct stressed piece, and the upper and lower skins 400 have enough strength; the utility model discloses to a great extent has reduced the assembly work volume, has reduced the assembly degree of difficulty. The strength and rigidity at the wing box section are improved.

Further, a notch 501 is processed at the top of the rib 500, and a rib 301 which is clamped into the notch 501 is arranged on the inner surface of the upper skin 300.

Specifically, the number of the processed notches 501 is the same as that of the ribs 301, the ribs 301 are of a sandwich structure, foam cores are arranged inside the ribs 301, composite skin is arranged outside the ribs, the upper skin 300 is independently paved and adhered and cured during molding, the foam cores are added at local positions in the paving and adhering process, curing is performed after paving and adhering, and the upper skin 300 is obtained after demolding.

In the utility model, the beam-rib-lower skin 400 integral forming structure is composed of a front beam 100, a back beam 200, a wing rib 500 and a lower skin 400, and then is connected with an upper skin 300 to form a certain type wing box section, when taking off, the whole wing can bear the taking-off weight of 20t, and the strength and the rigidity of the wing can meet the requirements; a structural oil tank is arranged in the wing box section, can bear 8-10t of heavy fuel oil, and simultaneously requires that the box section consisting of the front and rear beams 200, the lower skin 400 and the wing ribs 500 has good sealing performance; under covering 400 thickness be 10mm to 6 mm's gradual change thickness, structural strength and sealing performance homoenergetic meet the demands, the utility model discloses the assembly is simple, and the assembly volume is few, and the bulk strength is high, and sealing performance is good, can satisfy actual need.

The above description of the embodiments is only intended to help understand the method of the present invention and its core ideas. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, the present invention can be further modified and modified, and such modifications and modifications also fall within the protection scope of the appended claims.

Claims

1. A main box section structure of a double-beam type wing consists of a front beam (100), a rear beam (200), an upper skin (300), a lower skin (400) and a wing rib (500), and is characterized in that the front beam (100), the rear beam (200), the lower skin (400) and the wing rib (500) are of an integrally formed structure, the wing rib (500) is attached to the inner sides of the front beam (100), the rear beam (200) and the lower skin (400), and the upper skin (300) is installed on the integrally formed structure.

2. A twin beam wing main box section structure as defined in claim 1, characterised in that the top of the rib (500) is machined with a notch (501) and the inner surface of the upper skin (300) is provided with a rib (301) which snaps into the notch (501).

3. A twin beam wing box section structure as claimed in claim 2 in which the ribs (301) are of sandwich construction with a foam core inside and a composite skin outside.

4. A twin beam wing core box section structure as defined in any one of claims 1-3 in which the upper skin (300) is fixedly attached to the integrally formed structure using fasteners.

5. A twin beam wing main box section structure according to any of claims 1-3, characterised in that the front beam (100), rear beam (200), upper skin (300), lower skin (400) and ribs (500) are all of composite material.