Sandwich type carbon fiber aircraft body shell

Abstract

The utility model discloses a sandwich type carbon fiber aircraft body shell. The interlayer type carbon fiber aircraft body shell comprises a foaming material layer, a plurality of layers of carbon fiber cloth are arranged on the upper side and the lower side of the foaming material layer, the carbon fiber cloth and the foaming material layer have an aircraft body shell model, and resin and curing agents are arranged between the carbon fiber cloth and the foaming material layer and between the adjacent layers of carbon fiber cloth. The problem that in the prior art, the pursuit of people for the light weight of the aircraft body shell cannot be met is solved.

Description

Technical Field

[0001] The utility model relates to the technical field of carbon fiber materials, in particular to a sandwich-type carbon fiber aircraft body shell. Background Art

[0002] Due to the excellent properties of carbon fiber composite materials such as light weight, high strength, corrosion resistance, and impact resistance, some manufacturers currently apply carbon fiber composite materials to the production of aircraft body shells to meet people's pursuit of lightweight aircraft body shells. In the production process, generally, multiple layers of carbon fiber cloth (fiber length greater than 20 mm) are combined with resin and curing agent, and are integrally formed in a mold through heating and pressing. Through the above method, the weight of the aircraft body shell has been greatly reduced. However, it still cannot meet people's pursuit of lightweight aircraft body shells. Summary of the Utility Model

[0003] The purpose of the utility model is to address the deficiencies of the existing technology and provide a sandwich-type carbon fiber aircraft body shell that can further meet people's pursuit of lightweight aircraft body shells.

[0004] To achieve the above purpose, the technical solution adopted by the sandwich-type carbon fiber aircraft body shell of the utility model is as follows:

[0005] A sandwich-type carbon fiber aircraft body shell includes a foaming material layer. Several layers of carbon fiber cloth are arranged on the upper and lower sides of the foaming material layer. The carbon fiber cloth and the foaming material layer have the shape of an aircraft body shell. Resin and curing agent are provided between the carbon fiber cloth and the foaming material layer and between adjacent layers of carbon fiber cloth.

[0006] Preferably, the number of layers of carbon fiber cloth on the upper and lower sides of the foaming material layer is equal.

[0007] Preferably, the number of layers of carbon fiber cloth on the upper and lower sides of the foaming material layer is two layers.

[0008] Preferably, the number of layers of carbon fiber cloth on the upper and lower sides of the foaming material layer is three layers.

[0009] Preferably, the thickness of the carbon fiber cloth is 0.05 - 0.5 mm, and the thickness of the foaming material layer is 0.2 - 2 mm.

[0010] Preferably, the patterns of adjacent layers of carbon fiber cloth intersect with each other.

[0011] Preferably, the foaming material layer is a polymethacrylimide layer.

[0012] Compared with the existing technology, the utility model has the following advantages:

[0013] 1. Since the foaming material has good mechanical properties, heat distortion temperature and chemical stability, and its density is much smaller than that of the carbon fiber composite material, placing the foaming material layer in the middle as a sandwich layer can further reduce the weight of the aircraft body shell, meeting people's pursuit of lightweight of the aircraft body shell.

[0014] 2. The carbon fiber cloth and the foaming material layer are preformed into the shape of the aircraft body shell to facilitate the pressing of the finished product.

[0015] 3. The number of layers of the carbon fiber cloth on both the upper and lower sides of the foaming material layer is equal to ensure the balanced force on the foaming material layer during pressing. Description of the Drawings

[0016] Figure 1 is a schematic structural view of the sandwich - type carbon fiber aircraft body shell in Embodiment 1;

[0017] Figure 2 is a schematic structural view of the sandwich - type carbon fiber aircraft body shell in Embodiment 2.

[0018] Among them, 1 is the foaming material layer, and 2 is the carbon fiber cloth. Detailed Embodiment

[0019] The following further clarifies the present invention in conjunction with the drawings and specific embodiments. It should be understood that these embodiments are only used to illustrate the present invention and not to limit the scope of the present invention. After reading the present invention, various equivalent modifications made by those skilled in the art to the present invention all fall within the scope defined by the appended claims of this application.

[0020] Embodiment 1, as Figure 1 shown, a sandwich - type carbon fiber aircraft body shell includes a foaming material layer 1. The foaming material layer is a polymethacrylimide layer, the thickness of the polymethacrylimide layer is 0.4 mm, two layers of carbon fiber cloth 2 are arranged on each of the upper and lower sides of the foaming material layer. The carbon fiber cloth and the foaming material layer have the shape of the aircraft body shell to facilitate the pressing of the finished product. The thickness of the carbon fiber cloth is 0.1 mm, and the patterns of the adjacent layers of carbon fiber cloth are staggered with each other, which can improve the connection firmness between the carbon fiber cloths. The number of layers of the carbon fiber cloth on the upper and lower sides is the same to ensure the balanced force on the foaming material layer during pressing. Resin and curing agent are applied between the carbon fiber cloth and the foaming material layer and between the adjacent layers of carbon fiber cloth to increase the connection firmness between the carbon fiber cloth and the foaming material layer and between the adjacent layers of carbon fiber cloth.

[0021] Embodiment 2, as Figure 2As shown in the figure, a sandwich - type carbon fiber aircraft fuselage shell includes a foaming material layer 1. The foaming material layer is a polymethacrylimide layer with a thickness of 0.5 mm. Three layers of carbon fiber cloth 2 are arranged on each of the upper and lower sides of the polymethacrylimide layer. The carbon fiber cloth and the foaming material layer have the shape of the aircraft fuselage shell, which is convenient for pressing the finished product. The thickness of the carbon fiber cloth is 0.15 mm. The patterns of adjacent layers of carbon fiber cloth are staggered with each other, which can improve the connection firmness between carbon fiber cloths. The number of carbon fiber cloth layers on the upper and lower sides is the same, ensuring the balanced force on the foaming material layer during pressing. Resin and curing agent are applied between the carbon fiber cloth and the foaming material layer and between adjacent layers of carbon fiber cloth to increase the connection firmness between the carbon fiber cloth and the foaming material layer and between adjacent layers of carbon fiber cloth.

[0022] The specific working process and principle of a sandwich - type carbon fiber aircraft fuselage shell: Since polymethacrylimide has good mechanical properties, heat distortion temperature and chemical stability, and its density (0.05 - 0.6 g / cm 3 ) is much smaller than the density of carbon fiber composite materials (1.4 - 1.8 g / cm 3 ), placing the foaming material layer in the middle as a sandwich can further reduce the weight of the aircraft fuselage shell. Compared with the all - carbon fiber composite material structure, the utility model can reduce the weight by more than 40% under the same wall thickness and can maintain high strength and related properties, thus meeting people's pursuit of lightweight aircraft fuselage shells.

Claims

1. A sandwich - type carbon fiber aircraft fuselage shell, Characterized in that: It includes a foaming material layer, and several layers of carbon fiber cloth are arranged on the upper and lower sides of the foaming material layer. The carbon fiber cloth and the foaming material layer have the shape of an aircraft fuselage shell, and resin and curing agent are arranged between the carbon fiber cloth and the foaming material layer and between adjacent layers of carbon fiber cloth.

2. The sandwich - type carbon fiber aircraft fuselage shell according to claim 1, Characterized in that: The number of layers of carbon fiber cloth on the upper and lower sides of the foaming material layer is equal.

3. The sandwich - type carbon fiber aircraft fuselage shell according to claim 2, Characterized in that: The number of layers of carbon fiber cloth on the upper and lower sides of the foaming material layer is two layers.

4. The sandwich - type carbon fiber aircraft fuselage shell according to claim 2, Characterized in that: The number of layers of carbon fiber cloth on the upper and lower sides of the foaming material layer is three layers.

5. The sandwich - type carbon fiber aircraft fuselage shell according to any one of claims 1 - 4, Characterized in that: The thickness of the carbon fiber cloth is 0.05 - 0.5 mm, and the thickness of the foaming material layer is 0.2 - 2 mm.

6. The sandwich - type carbon fiber aircraft fuselage shell according to claim 5, Characterized in that: The patterns of adjacent layers of carbon fiber cloth intersect each other.

7. The sandwich - type carbon fiber aircraft fuselage shell according to claim 5, Characterized in that: The foaming material layer is a polymethacrylimide layer.

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