CN213109761U

CN213109761U - Composite material fuselage skin and skeleton connecting structure

Info

Publication number: CN213109761U
Application number: CN202021079628.2U
Authority: CN
Inventors: 陈宜参; 王瑞; 马胜波
Original assignee: ZHEJIANG TSINGHUA YANGTZE RIVER DELTA RESEARCH INSTITUTE
Current assignee: ZHEJIANG TSINGHUA YANGTZE RIVER DELTA RESEARCH INSTITUTE; Yangtze Delta Region Institute of Tsinghua University Zhejiang
Priority date: 2020-06-12
Filing date: 2020-06-12
Publication date: 2021-05-04
Anticipated expiration: 2030-06-12

Abstract

The utility model discloses a composite material fuselage skin and skeleton connecting structure, which comprises a composite material fuselage skin and a stringer; the stringer is provided with a 1-shaped end, the 1-shaped end is contacted with the composite material fuselage skin, fiber cloth is arranged at the 1-shaped end, and the fiber cloth is cemented with the stringer and the composite material fuselage skin; the other end of the stringer is fixedly connected with the fuselage skeleton. The utility model relates to a combined material fuselage covering and skeleton connection structure adopts the stringer that has "1" font end to contact with the covering perpendicularly, has changed the cross sectional shape of stringer, has given up redundant turn-ups, has alleviateed weight, directly has spread in the both sides of stringer and fuselage combined material fuselage covering and pastes fibre cloth, and construction process becomes more simple and convenient, and intensity does not reduce. The fiber cloth is laid on the side surface of the end part of the stringer, so that different parts can be connected and stress can be transmitted.

Description

Composite material fuselage skin and skeleton connecting structure

Technical Field

The utility model belongs to the technical field of the technique of being connected of fuselage covering and fuselage skeleton and specifically relates to a combined material fuselage covering and skeleton connection structure.

Background

In the prior art, the aircraft is made of metal materials, so that when the fuselage skeleton and the stringers 2 are assembled with the skin, the fuselage skeleton and the stringers 2 are riveted together by rivets, and a flange 22 is arranged on the assembling surface of the fuselage skeleton, which is close to the stringers 2 and the skin, so that the fuselage skeleton and the skin can be riveted together by rivets.

The existing airframe adopts full composite materials, and mainly adopts a cementing mode to connect the airframe framework, the stringers and the skin. If the flange 22 is still retained, the weight of the flange 22 is wasted. Moreover, because the fiber cloth 3 is paved for cementation, the part of the flanging which is directly contacted with the skin is not directly cemented, but the strength is reduced.

SUMMERY OF THE UTILITY MODEL

When resulting in gluing with combined material fuselage covering to current combined material fuselage skeleton, stringer shape, intensity and weight receive the problem of influence, the utility model aims at providing a combined material fuselage covering and skeleton connection structure, the weight of lightening stringer and fuselage skeleton improves the structural strength after gluing with combined material fuselage covering.

In order to solve the technical problem, the purpose of the utility model is to realize like this:

the utility model relates to a composite material fuselage skin and skeleton connecting structure, which comprises a composite material fuselage skin and a stringer; the stringer is provided with a 1-shaped end, the 1-shaped end is contacted with the composite material fuselage skin, fiber cloth is arranged at the 1-shaped end, and the fiber cloth is cemented with the stringer and the composite material fuselage skin; the other end of the stringer is fixedly connected with the fuselage skeleton.

On the basis of the above scheme and as a preferable scheme of the scheme: the stringer is in a 1 shape as a whole.

On the basis of the above scheme and as a preferable scheme of the scheme: the whole stringer is L-shaped.

On the basis of the above scheme and as a preferable scheme of the scheme: the end of the 1 shape is in vertical contact with the composite fuselage skin 1.

On the basis of the above scheme and as a preferable scheme of the scheme: the fiber cloth is glass fiber cloth.

The utility model has the advantages that: the utility model relates to a combined material fuselage covering and skeleton connection structure adopts the stringer that has "1" font end to contact with the covering perpendicularly, has changed the cross sectional shape of stringer, has given up redundant turn-ups, has alleviateed weight, directly has spread in the both sides of stringer and fuselage combined material fuselage covering and pastes fibre cloth, and construction process becomes more simple and convenient, and intensity does not reduce. The fiber cloth is laid on the side surface of the end part of the stringer, so that different parts can be connected and stress can be transmitted.

Drawings

FIG. 1 is a schematic view of an improved composite fuselage skin to skeleton joint configuration according to an embodiment;

FIG. 1-A is a cross-sectional view of a composite fuselage skin and frame attachment arrangement according to one embodiment;

FIG. 1-B is a schematic view of a composite fuselage skin and skeleton connection after modification according to one embodiment;

FIG. 2 is a schematic view showing a modified structure of a composite fuselage skin-to-skeleton joint according to a second embodiment;

FIG. 2-A is a connecting structure of a fuselage skin and a framework of a composite material before modification according to the second embodiment;

FIG. 2-B is the connecting structure of the skin and the framework of the improved composite fuselage according to the second embodiment;

fig. 3 is a schematic view of a modified structure of the connection between the skin and the skeleton of the composite fuselage according to the third embodiment.

FIG. 3-A is a connecting structure of a fuselage skin and a framework of a composite material before modification in the third embodiment;

fig. 3-B is the connecting structure of the skin and the framework of the improved composite fuselage in the third embodiment.

The designations in the figures illustrate the following: 1-composite fuselage skin; 2-stringer; 21- "1" shaped end; 22-flanging; 3-fiber cloth.

Detailed Description

The present invention will be further described with reference to the accompanying drawings and specific embodiments.

The utility model relates to a combined material fuselage covering and skeleton connection structure, including combined material fuselage covering 1 and stringer 2. The stringer 2 has a 1-shaped end 21, the 1-shaped end 21 is vertically contacted with the composite material fuselage skin 1, the 1-shaped end 21 is provided with a fiber cloth 3, the fiber cloth 3 is cemented with the stringer 2 and the composite material fuselage skin 1, namely, one part of the fiber cloth 3 is cemented with the stringer 2, and the other end is cemented with the composite material fuselage skin. The fiber cloth laid on the side surface of the 1-shaped end part 21 can connect different parts and transmit stress. And the other end of the stringer 2 is fixedly connected with the fuselage skeleton. The flanging 22 arranged in the original stringer 2 is reduced, so that the weight of the stringer 2 can be reduced, and the weight of the whole fuselage is reduced. When the original stringer 2 is glued to the composite fuselage skin 1 using the fiber cloth 3, the part of the flange 22 that is in contact with the composite fuselage skin 1 is not glued directly, but rather the strength is reduced.

Further, the fiber cloth 3 used is a glass fiber cloth.

Example one

This embodiment will be described in detail with reference to FIGS. 1, 1-A, and 1-B. The composite fuselage skin and skeleton connection structure according to the embodiment comprises a composite fuselage skin 1 and stringers 2. The stringer 2 is provided with a 1-shaped end 21, the 1-shaped end 21 is in contact with the composite material fuselage skin 1, the 1-shaped end 21 is provided with a fiber cloth 3, and the fiber cloth 3 is glued with the stringer 2 and the composite material fuselage skin 1; the other end of the stringer 2 is fixedly connected with the fuselage skeleton.

Specifically, the stringer 2 according to the present embodiment has a "1" shape as a whole, that is, a rectangular shape in cross section. The original stringer 2 is L-shaped, the flanging 22 of the original stringer 2 is arranged in parallel with the composite material fuselage skin 2, when the stringer 2 is connected with the composite material fuselage skin 1 by using the fiber cloth 3, one part of the fiber cloth is cemented with the flanging 22, so that the part of the flanging 22, which is in contact with the composite material fuselage skin 1, is not directly cemented, and the strength is reduced on the contrary.

Example two

This embodiment will be described in detail with reference to FIGS. 2, 2-A, and 2-B. As shown in fig. 2-a, in the composite fuselage skin and skeleton connection structure before modification, the stringer 2 used is T-shaped, and the flanges 22 are provided on both sides, and when the stringer 2 is bonded to the composite fuselage skin 1 by using the fiber cloth 3, a part of the fiber cloth 3 on both sides is bonded to the flanges 22, so that the part of the flanges 22 contacting the composite fuselage skin 1 is not directly bonded, but the strength is reduced.

In the modified composite fuselage skin to skeleton connection shown in fig. 2-B, in the present embodiment, the T-shaped stringer 2 is modified into an overall "1" shaped stringer 2. The fiber cloth laid on the side surface of the 1-shaped end part 21 can connect different parts and transmit stress.

EXAMPLE III

This embodiment will be described in detail with reference to FIGS. 3, 3-A, and 3-B. As shown in fig. 3-a, in the composite fuselage skin and skeleton connection structure before modification, the stringer 2 used is in a "[" shape, and like the connection structure before modification in the first and second embodiments, when the stringer 2 is glued to the composite fuselage skin 1 by the fiber cloth 3, the fiber cloth 3 on one side is glued to the flange 22, so that the part of the flange 22 contacting the composite fuselage skin 1 is not glued directly, but the strength is reduced.

As shown in fig. 3-B, the modified composite fuselage skin and skeleton connection structure, in this embodiment, is modified by "L" -shaped stringers 2 into overall L-shaped stringers 2. The fiber cloth laid on the side surface of the 1-shaped end part 21 can connect different parts and transfer stress.

The foregoing has described in detail preferred embodiments of the present invention. It should be understood that numerous modifications and variations can be devised by those skilled in the art in light of the present teachings without departing from the inventive concepts. Therefore, the technical solutions that can be obtained by a person skilled in the art through logic analysis, reasoning or limited experiments based on the prior art according to the concepts of the present invention should be within the scope of protection defined by the claims.

Claims

1. A composite material fuselage skin and skeleton connecting structure is characterized by comprising a composite material fuselage skin (1) and stringers (2); the stringer (2) is provided with a 1-shaped end (21), the 1-shaped end (21) is in contact with the composite material fuselage skin (1), fiber cloth (3) is arranged at the 1-shaped end (21), and the fiber cloth (3) is cemented with the stringer (2) and the composite material fuselage skin (1); the other end of the stringer (2) is fixedly connected with the fuselage framework.

2. The composite fuselage skin and skeleton connection according to claim 1, characterized in that the stringers (2) are overall in the shape of a "1".

3. A composite fuselage skin and skeleton connection according to claim 1, characterised in that the stringers (2) are overall "L" -shaped.

4. A composite fuselage skin to skeleton connection according to claim 1, characterised in that the "1" -shaped end (21) is in vertical contact with the composite fuselage skin (1).

5. The composite fuselage skin and skeleton connection according to claim 1, characterized in that the fiber cloth (3) is a glass fiber cloth.