CN219140474U

CN219140474U - Composite material stiffened plate with high out-of-plane compression performance

Info

Publication number: CN219140474U
Application number: CN202320033620.XU
Authority: CN
Inventors: 从庆; 隋显航; 张�林; 李光友; 杨佳成
Original assignee: Weihai Guangwei Composites Co Ltd
Current assignee: Weihai Guangwei Composites Co Ltd
Priority date: 2023-01-06
Filing date: 2023-01-06
Publication date: 2023-06-06
Anticipated expiration: 2033-01-06

Abstract

The utility model discloses a composite material reinforcing plate with high out-of-plane compression performance, which is characterized in that: the skin structure comprises a reinforcing rib component and skin structures respectively arranged at the upper end and the lower end of the reinforcing rib component; the reinforcing rib assembly comprises a plurality of reinforcing ribs, the cross section of each reinforcing rib is of a closed annular structure, each reinforcing rib comprises two transversely arranged skin connecting parts and two longitudinally arranged rib plate connecting parts, the skin connecting parts are used for being connected with the skin, the reinforcing ribs are connected with each other through the rib plate connecting parts, and the rib plate connecting parts are attached to each other. The composite material reinforcing plate with high out-of-plane compression performance provided by the utility model can be used for periodically designing the section of the reinforcing rib, so that the lower material use is ensured, the higher buckling characteristic value is realized, and the buckling stability is better.

Description

Composite material stiffened plate with high out-of-plane compression performance

Technical Field

The utility model relates to the field of composite materials, in particular to a composite material reinforcing plate with high out-of-plane compression performance.

Background

The composite material stiffened plate shell is widely applied to various fields of aerospace, wind power generation, rail transit and the like, and has the characteristics of light weight, high strength, excellent corrosion resistance, excellent environmental resistance and the like, and for example, an aircraft wing structure, a fuselage structure, a wind power blade and the like all adopt the material and the structural mode.

The composite material stiffened plate has various failure modes, wherein what is important is that the stiffener buckling failure caused by out-of-plane compression occurs, and the failure mode can lead to early buckling of the stiffener when the product does not reach the out-of-plane compression ultimate strength, and the bearing capacity of the stiffened plate is reduced until the product is damaged.

Disclosure of Invention

The utility model aims to overcome the problems and provide a composite material reinforcing plate with high out-of-plane compression performance.

In order to achieve the above purpose, the method adopted by the utility model is as follows: a composite stiffened panel having high out-of-plane compression properties, characterized by: the skin structure comprises a reinforcing rib component and skin structures respectively arranged at the upper end and the lower end of the reinforcing rib component; the reinforcing rib assembly comprises a plurality of reinforcing ribs, the cross section of each reinforcing rib is of a closed annular structure, each reinforcing rib comprises two transversely arranged skin connecting parts and two longitudinally arranged rib plate connecting parts, the skin connecting parts are used for being connected with the skin, the reinforcing ribs are connected with each other through the rib plate connecting parts, and the rib plate connecting parts are attached to each other.

Preferably, the skin connecting part of the reinforcing rib is in adhesive connection with the skin.

Preferably, the rib plate connecting parts of the reinforcing ribs are connected by gluing.

Preferably, the rib plate connecting parts are respectively connected with the transverse two ends of the skin connecting part through the oblique connecting sections at the two longitudinal ends.

Preferably, the length of the rib plate connecting part in the longitudinal direction is 0.55-0.58 times of the height of the reinforcing rib; and the width of the reinforcing rib is 0.35-0.45 times of the height of the reinforcing rib.

Preferably, the included angle between the oblique connecting section and the skin connecting part is 97-98 degrees.

The beneficial effects are that:

compared with the prior art, the reinforcing rib section design of the composite material reinforcing rib with high out-of-plane compression performance provided by the utility model can be used periodically, so that the lower material use is ensured, the higher buckling characteristic value is provided, and the buckling stability is better.

Drawings

FIG. 1 is a schematic structural view of a composite stiffened panel with high out-of-plane compression properties according to an embodiment of the present application;

FIG. 2 is a cross-sectional view of an embodiment of the present application;

FIG. 3 is a schematic structural view of a reinforcing bar according to an embodiment of the present application;

FIG. 4 is a cross-sectional view of a reinforcing bar according to an embodiment of the present application;

FIG. 5 is a cross-sectional view of a prior art composite stiffened panel;

FIG. 6 is a finite element analysis result of a prior art type I tendon buckling analysis;

fig. 7 is a finite element analysis result of the rib buckling analysis of the embodiment of the present application.

The components in the figure are:

1. a first skin; 2. a second skin; 3. reinforcing ribs; 301. a skin connection; 302. a gusset connecting portion; 303. and the oblique connecting section.

Detailed Description

The utility model will be further illustrated by the following drawings and specific examples, which are carried out on the basis of the technical solutions of the utility model, it being understood that these examples are only intended to illustrate the utility model and are not intended to limit the scope of the utility model.

Example 1:

referring to fig. 1 to 4, the present embodiment discloses a composite stiffened panel with high out-of-plane compression performance, which comprises a first skin 1, a second skin 2 and a stiffener assembly, wherein the first skin 1 and the second skin 2 are respectively arranged on the upper side and the lower side of the stiffener assembly. The reinforcing rib assembly is formed by splicing a plurality of reinforcing ribs 3, the reinforcing ribs 3 structurally comprise skin connecting portions 301 and rib plate connecting portions 302, the skin connecting portions 301 are horizontally arranged, the rib plate connecting portions 302 are vertically arranged, and each reinforcing rib 3 comprises two skin connecting portions 301 and two rib plate connecting portions 302. The upper end and the lower end of each rib plate connecting part 302 are respectively connected with the skin connecting part 301 through an inclined connecting section 303, so that the reinforcing ribs 3 form a closed annular structure, the included angle between the inclined connecting section 303 and the skin connecting part 301 is 97-98 degrees, and the included angle is 97.5 degrees in the embodiment. The length of the rib plate connecting portion 302 is 55-58% of the total height of the reinforcing rib 3, 56.67% is adopted in this embodiment, the width of the reinforcing rib 3, that is, the spacing of the rib plate connecting portions 302 is set to 35% -45% of the total height of the reinforcing rib, and 40% is adopted in this embodiment.

The first skin 1 and the second skin 2 are thin-wall composite material plate-shell structures and are mainly used for resisting the action of tensile compression and in-plane shear load; each stiffener 3 is attached to each other by a gusset connecting portion 302, and arranged to form a stiffener assembly, mainly for resisting out-of-plane shearing and tension loading caused by bending of the plate, and the stiffener 3 is also made of a composite material. The composite material is one or a plurality of combinations of carbon fiber, glass fiber, aramid fiber or basalt fiber reinforced resin matrix composite material. In this embodiment, the first skin 1, the second skin 2 and the skin connecting portion 301 of the stiffener 3 are connected by gluing. The rib plate connecting parts 302 of the reinforcing ribs 3 are also connected by gluing.

Referring to fig. 5 and 6, by carrying out pressure-bearing analysis on the stiffening plate, the buckling characteristic value of the single stiffening rib is 0.011 in the original state of the I-shaped stiffening rib structure. Referring to fig. 7, in the present embodiment, the buckling characteristic value of the single-rod stiffener is 0.153, which is improved by 13 times, for the stiffener structure with the same material and thickness. The structural mode not only ensures the use of lower materials, but also has higher buckling characteristic value and better buckling stability.

The technical means disclosed by the scheme of the utility model is not limited to the technical means disclosed by the embodiment, and also comprises the technical scheme formed by any combination of the technical features. It should be noted that modifications and adaptations to the utility model may occur to one skilled in the art without departing from the principles of the present utility model and are intended to be within the scope of the present utility model.

Claims

1. A composite stiffened panel having high out-of-plane compression properties, characterized by: the skin structure comprises a reinforcing rib component and skin structures respectively arranged at the upper end and the lower end of the reinforcing rib component; the reinforcing rib assembly comprises a plurality of reinforcing ribs (3), the cross section of each reinforcing rib (3) is of a closed annular structure, each reinforcing rib (3) comprises two skin connecting parts (301) which are transversely arranged and two rib plate connecting parts (302) which are longitudinally arranged, each skin connecting part (301) is used for being connected with a skin, each reinforcing rib (3) is connected with each other through each rib plate connecting part (302), and each rib plate connecting part (302) is attached to each other.

2. A composite stiffened panel with high out-of-plane compression performance according to claim 1, wherein: the skin connecting part (301) of the reinforcing rib (3) is in adhesive connection with the skin.

3. A composite stiffened panel with high out-of-plane compression performance according to claim 1, wherein: the rib plate connecting parts (302) of the reinforcing ribs (3) are connected through gluing.

4. A composite stiffened panel with high out-of-plane compression performance according to claim 1, wherein: the rib plate connecting parts (302) are respectively connected with the transverse two ends of the skin connecting part (301) through oblique connecting sections (303) at the two longitudinal ends.

5. A composite stiffened panel with high out-of-plane compression performance according to claim 4, wherein: the length of the rib plate connecting part (302) in the longitudinal direction is 0.55-0.58 times of the height of the reinforcing rib (3); and the width of the reinforcing rib (3) is 0.35-0.45 times of the height of the reinforcing rib (3).

6. A composite stiffened panel with high out-of-plane compression performance according to claim 4 or 5, wherein: the included angle between the oblique connecting section (303) and the skin connecting part (301) is 97-98 degrees.