CN221198197U

CN221198197U - Large-size thin-wall semi-closed cavity thermoplastic composite material fairing

Info

Publication number: CN221198197U
Application number: CN202322839938.XU
Authority: CN
Inventors: 曹峰; 王艳丽; 蒋斌林; 康龙辉; 孙英超; 郝桂珍
Original assignee: Jiangxi Hongdu Aviation Industry Group Co Ltd
Current assignee: Jiangxi Hongdu Aviation Industry Group Co Ltd
Priority date: 2023-10-23
Filing date: 2023-10-23
Publication date: 2024-06-21
Anticipated expiration: 2033-10-23

Abstract

The utility model relates to a thermoplastic composite material structure, in particular to a large-size thin-wall semi-closed cavity thermoplastic composite material fairing. When the fairing is designed by adopting the traditional metal materials, the chord plane is used as the parting plane, and the part is in a large-size thin-wall structure due to the complex shape, so that the utilization rate of the part processing materials is low, the processing period is long, the production cost of the part is high, and the batch production and delivery capacity of the part is restricted. The utility model provides a large-size thin-wall semi-closed cavity thermoplastic composite material fairing, which comprises an upper fairing skin and a lower fairing skin, wherein the upper fairing skin and the lower fairing skin are formed by adopting a thermoplastic composite material through compression molding, the wall thickness is 2-5mm, the upper fairing skin and the lower fairing skin are respectively arranged on a machine body and are connected with each other, and a sinking area is arranged at the boundary of the interconnection of the upper fairing skin and the lower fairing skin. The molding cycle is short, the production efficiency is high, and the redundant prepreg during layering can be recycled under certain conditions, so that the manufacturing cost can be reduced.

Description

Large-size thin-wall semi-closed cavity thermoplastic composite material fairing

Technical Field

The utility model relates to a thermoplastic composite material structure, in particular to a large-size thin-wall semi-closed cavity thermoplastic composite material fairing.

Background

To achieve a good aerodynamic profile and better aerodynamic efficiency, fairings are often provided at the connection of the missile wing and body of the missile. When a certain fairing is designed by adopting a traditional metal material, a chord plane is used as a parting surface, and the part is of a relatively complex shape and a large-size thin-wall structure, so that the utilization rate of part processing materials is relatively low, the processing period is relatively long, the production cost of the part is relatively high, and the batch production and delivery capacity of the part is restricted.

Disclosure of utility model

The utility model aims at the prior art, and provides a large-size thin-wall semi-closed cavity thermoplastic composite fairing, which can obtain better aerodynamic appearance, effectively reduce the weight of the fairing and reduce the manufacturing cost.

The utility model provides a large-size thin-wall semi-closed cavity thermoplastic composite material fairing, which comprises an upper fairing skin and a lower fairing skin, wherein the upper fairing skin and the lower fairing skin are formed by adopting a thermoplastic composite material through compression molding, the wall thickness is 2-5mm, the upper fairing skin and the lower fairing skin are respectively arranged on a machine body and are connected with each other, and a sinking area is arranged at the boundary of the interconnection of the upper fairing skin and the lower fairing skin.

Advantageously, the sinking depth is 3mm and the width is 25mm.

Advantageously, the wall thickness is 3mm.

Advantageously, the upper fairing skin is of a large-opening curved surface structure, and the opening of the upper fairing skin avoids the front edge and the rear edge of the fairing appearance; the lower rectification skin is of a small curved surface cover type structure, and the curved surface radian is small.

Advantageously, the fairing is used for the connection of the missile wing to the body of the missile.

Advantageously, the upper fairing skin and the body of the bullet, the lower fairing skin and the body of the bullet, and the upper fairing skin and the lower fairing skin are connected by means of screw-airtight blade nuts.

Advantageously, the upper fairing skin has a number of upper attachment holes and the lower fairing skin has a number of lower attachment holes.

Advantageously, the outside of the fairing encloses the missile wing structure and the inside encloses the missile wing main joint and the folding mechanism.

In the scheme, the fairing consists of an upper fairing skin and a lower fairing skin, wherein the upper fairing skin comprises an arc-shaped area of the whole front edge and the rear edge to form a semi-closed cavity thin-wall structure, and the lower fairing skin is connected with the upper fairing skin under the action of a flap. The fairing wraps the main joint of the missile wing and the folding structure of the missile wing, so that the missile wing is smoothly connected with the missile body. The connecting parts of the upper rectifying skin and the lower rectifying skin avoid the windward areas of the front edge and the rear edge, thereby effectively reducing aerodynamic resistance.

The upper rectifying skin and the lower rectifying skin are connected into a whole through screws, and connecting holes are respectively designed at the edges of the large openings of the upper rectifying skin and the lower rectifying skin and are used for fixing the rectifying cover.

The fairing is formed by adopting the thermoplastic composite material in a compression molding way, the molding cycle is short, the production efficiency is high, and the redundant prepreg during layering can be recycled under a certain condition, so that the manufacturing cost can be reduced.

The beneficial effects are that: the front edge and the rear edge of the fairing are of an integral thin-wall structure, so that aerodynamic resistance is effectively reduced, and engineering application of a large-size thin-wall semi-closed cavity structure is realized by adopting a high-performance thermoplastic composite material, so that batch production and manufacturing capacity of the fairing are improved, and manufacturing cost is greatly reduced.

Drawings

FIG. 1 is an upper fairing skin;

FIG. 2 is a lower fairing skin;

FIG. 3 is a schematic diagram of a fairing;

FIG. 4 is a schematic view of a fairing wrapped missile wing.

1-Upper rectifying skin, 2-lower rectifying skin, 3-missile wing structure, 4-missile wing main joint, folding mechanism, 5-upper connecting hole and 6-lower connecting hole

Detailed Description

A large-size thin-wall semi-closed cavity thermoplastic composite fairing is divided into an upper fairing skin 1 and a lower fairing skin 2. The upper fairing skin 1 is of a large-opening curved surface structure, and the openings of the upper fairing skin 1 avoid the front edge and the rear edge of the fairing shape, so that the smoothness of the front edge and the rear edge facing the wind is ensured. The lower rectifying skin 2 is of a small curved surface cover type structure, and the curved surface radian is small. The upper fairing skin 1 and the lower fairing skin 2 are both thin-walled structures, typically 3mm thick. The upper rectifying skin 1 is provided with a sinking area at the connecting boundary with the lower rectifying skin 2, the sinking depth is 3mm, and the width is 25mm.

The fairing and the body of the bullet and the upper fairing skin 1 and the lower fairing skin 2 are connected through screw-airtight supporting plate nuts. The upper rectifying skin 1 and the lower rectifying skin 2 are fixed on the body of the bullet respectively by 16 and 12 screws at the upper connecting hole 5 and the lower connecting hole 6, and are connected with the upper rectifying skin 1 and the lower rectifying skin 2 through 7 screws. The outside of the fairing wraps the missile wing structure 3, the inside wraps the missile wing main joint and the folding mechanism 4, and the inside opening is connected with the missile body. The use of fairings greatly reduces the aerodynamic drag of the missile wing main joint and the missile wing folding mechanism.

The unfolding and folding processes of the missile wing are all in the fairing package, so that aerodynamic resistance is effectively reduced. Meanwhile, when the missile wing or the folding structure is maintained or inspected, maintenance can be performed by unscrewing the fixing screws of the upper rectifying skin and the missile body and the connecting screws of the upper rectifying cover and the lower rectifying cover.

Claims

1. A large-size thin-wall semi-closed cavity thermoplastic composite fairing is characterized in that: the upper rectifying skin (1) and the lower rectifying skin (2) are molded by adopting a thermoplastic composite material, the wall thickness is 2-5mm, the upper rectifying skin (1) and the lower rectifying skin (2) are respectively arranged on a machine body and are connected with each other, and a sinking area is arranged at the boundary of the interconnection of the upper rectifying skin (1) and the lower rectifying skin (2).

2. The large-size thin-walled semi-closed thermoplastic composite fairing of claim 1, wherein: the depth of the sinking area is 3mm and the width is 25mm.

3. The large-size thin-walled semi-closed thermoplastic composite fairing of claim 1, wherein: the wall thickness was 3mm.

4. The large-size thin-walled semi-closed thermoplastic composite fairing of claim 1, wherein: the upper rectifying skin (1) is of a large-opening curved surface structure, and the opening of the upper rectifying skin (1) avoids the front edge and the rear edge of the appearance of the fairing; the lower rectifying skin (2) is of a small curved surface flap type structure.

5. The large size thin wall semi-closed thermoplastic composite fairing as recited in any one of claims 1-4, wherein: the fairing is used for the connection part of the missile wing and the missile body of the missile.

6. The large-size thin-walled semi-closed thermoplastic composite fairing of claim 5, wherein: the upper rectifying skin (1) and the body of the bullet, the lower rectifying skin (2) and the body of the bullet and the upper rectifying skin (1) and the lower rectifying skin (2) are connected through screw-airtight supporting plate nuts.

7. The large-size thin-walled semi-closed thermoplastic composite fairing of claim 6, wherein: the upper rectifying skin (1) is provided with a plurality of upper connecting holes (5), and the lower rectifying skin (2) is provided with a plurality of lower connecting holes (6).

8. The large-size thin-walled semi-closed thermoplastic composite fairing of claim 5, wherein: the outside of the fairing wraps the missile wing structure (3), and the inside wraps the missile wing main joint and the folding mechanism (4).