Fuselage skin and assembly

Abstract

The invention belongs to the technical field of fuselages for aerocars, and provides a fuselage skin which comprises a composite material body layer, an assembly body layer is integrally formed on the inner side surface of the composite material body layer and comprises a framework part and a buckle part which are integrally connected, the framework part is connected and attached to the inner side surface of the composite material body layer, and the buckle part is connected and attached to the outer side surface of the composite material body layer. And the buckling part is formed by outwards extending the framework part. The plastic buckle has the advantages that the structure is simple, the plastic buckle part is composed of two parts, the plastic buckle part of the assembly body layer is integrally formed, cracking is avoided, the buckle precision is high, appearance surface treatment is not needed by adopting the PUR layer, meanwhile, the framework part of the assembly body layer plays a role of a reinforcing rib, the technology is simple, cost is low, efficiency is high, and mass production is achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of fuselage products for flying cars, and in particular relates to a fuselage skin and an assembly. Background Art

[0002] Composite materials (not limited to carbon fiber, for example but not limited to glass fiber, etc.) are often needed on the interior of vertical lift (not just vertical lift aircraft, other aircraft are also included, not just used on aircraft, other such as cars, etc.) aircraft to form fuselage interior and exterior trims. When the fuselage interior and exterior trims need to be assembled, holes need to be drilled and riveted on the fuselage interior or exterior trims to install connecting buckles or use adhesive buckles, and then the two are assembled through the buckle structure. This connection method has a complicated process. Adhesive buckles are prone to falling off. Drilling and riveting methods have complicated processes. Plastic buckles are prone to cracking due to post-installation. The overall size deviation is large and manual grinding and matching are required. The buckle positioning accuracy is low, which seriously affects production efficiency. Summary of the invention

[0003] The technical problem to be solved by the present invention is to provide a fuselage skin and assembly which is easy to install, has good matching degree and simple process in view of the current status of the prior art.

[0004] The technical solution adopted by the present invention to solve the above technical problems is: a fuselage skin, including a composite body layer, characterized in that an assembly layer is integrally formed on the inner surface of the composite body layer, and the assembly layer includes an integrally connected skeleton part and a snap-on part, the skeleton part is connected and attached to the inner surface of the composite body layer, and the snap-on part is formed by extending outward from the skeleton part.

[0005] In the above-mentioned fuselage skin, an appearance layer is formed on the outer surface of the composite body layer, and the appearance layer is a PUR layer, and the PUR layer is formed on the outer surface of the composite body layer by injection molding.

[0006] In the above-mentioned fuselage skin, the thickness of the PUR layer is 0.3-0.7 mm.

[0007] In the above-mentioned fuselage skin, the composite body layer is based on a thermoplastic resin and is pre-impregnated with carbon fibers and compression molded. The thermoplastic resin is one or more of PC, PEEK or PET.

[0008] In the above-mentioned fuselage skin, the thickness of the composite body layer is ≥0.2 mm.

[0009] In the above-mentioned fuselage skin, the assembly layer is made of plastic material, including one or more plastic materials such as PC or ABS, and the thickness of the assembly layer is ≥0.8 mm.

[0010] A fuselage outer skin, characterized in that the fuselage outer skin is formed by the above-mentioned fuselage skin.

[0011] A fuselage inner skin, characterized in that the fuselage inner skin is formed by the above-mentioned fuselage skin.

[0012] A fuselage skin assembly is characterized in that it comprises a fuselage outer skin and a fuselage inner skin, and the fuselage outer skin and the fuselage inner skin are assembled together through a snap-fit ​​part.

[0013] Compared with the prior art, the advantages of the present invention are that it has a simple structure and consists of two parts. The plastic buckle part of the assembly layer is formed in one piece and will not crack. The buckle has high precision and the PUR layer does not require surface treatment. At the same time, the skeleton part of the assembly layer acts as a reinforcing rib. The process is simple: low cost, high efficiency, and mass production is possible. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the structure of the outer skin of the fuselage;

[0015] Figure 2 yes Figure 1 BB structural diagram;

[0016] Figure 3 It is a schematic diagram of the structure of the inner skin of the fuselage;

[0017] Figure 4 yes Figure 3 Schematic diagram of CC structure;

[0018] Figure 5 It is a schematic diagram of the cross-sectional structure of the assembly after the inner skin of the fuselage and the outer skin of the fuselage are assembled. DETAILED DESCRIPTION

[0019] The following are specific embodiments of the present invention and the accompanying drawings to further describe the technical solution of the present invention, but the present invention is not limited to these embodiments.

[0020] In the figure, there are a composite body layer 100 , a PUR layer 200 , an assembly layer 300 , a skeleton part 400 , a buckle part 500 , a fuselage outer skin 600 , and a fuselage inner skin 700 .

[0021] like Figure 1 As shown, Figure 1 as well as Figure 2As shown, the fuselage skin includes a composite body layer 100, wherein the composite body layer 100 is based on a thermoplastic resin and pre-impregnated with carbon fiber and molded, the thermoplastic resin is one or more of PC, PEEK or PET, the thickness of the composite body layer 100 is ≥0.2mm, and in particular, the thickness of 0.6-0.8mm is the best. An appearance layer is formed on the outer surface of the composite body layer 100, and the appearance layer is a PUR layer 200. The PUR layer 200 is formed on the outer surface of the composite body layer 100 by injection molding, and the thickness of the PUR layer 200 is 0.3-0.7mm. The PUR layer 200 is also a polyurethane layer, mainly using polyurethane as raw material. When color requirements are required, color paste can be added to the polyurethane raw material. Here, the PUR layer 200 is used instead of the original spray paint, which eliminates the processes such as spray paint and polishing, and the process is simpler, in order to perform transfer connection.

[0022] As a further optimization, an assembly layer 300 is integrally formed on the inner surface of the composite body layer 100. The assembly layer 300 is a plastic material, including one or more plastic materials such as PC or ABS. The thickness of the assembly layer 300 is ≥ 0.8 mm, and 1-1.4 mm is the best. The assembly layer 300 includes an integrally connected skeleton part 400 and a buckle part 500. The skeleton part 400 is connected and attached to the inner surface of the composite body layer 100, and the buckle part 500 is formed by extending outward from the skeleton part 400. Here, the buckle part 500 mainly plays the role of assembly connection. The plastic buckle part 500 that forms the assembly layer 300 in one piece will not crack, has high buckle precision, and eliminates the original bonding and riveting steps. In addition, the skeleton part 400 plays the role of reinforcing ribs for the composite body layer 100, which strengthens the entire composite body layer 100 as a whole. The composite body layer 100 of this patent is first molded in the mold, and then the PUR layer 200 is injection molded. After the mold is turned, the assembly layer 300 is injection molded to form it.

[0023] like Figure 2 , Figure 3 as well as Figure 4 As shown, based on the fuselage skin of the present invention, a fuselage outer skin 600 and a fuselage inner skin 700 can be formed, as shown in FIG. Figure 5 As shown, when the buckle portion 500 of the fuselage outer skin 600 is a clamping head, the buckle portion 500 of the fuselage inner skin 700 is a clamping groove, and when the buckle portion 500 of the fuselage outer skin 600 is a clamping groove, the buckle portion 500 of the fuselage inner skin 700 is a clamping head, as shown in FIG. Figure 5 As shown, the finally formed fuselage skin assembly includes a fuselage outer skin 600 and a fuselage inner skin 700 , and the fuselage outer skin 600 and the fuselage inner skin 700 are assembled together through the snap-fit ​​portion 500 .

[0024] The specific embodiments described herein are merely examples of the spirit of the present invention. Those skilled in the art may make various modifications to the described specific embodiments or replace them with similar methods without departing from the scope defined by the spirit of the present invention.

Claims

1. A fuselage skin, comprising a composite body layer, characterized in that: An assembly layer is integrally formed on the inner surface of the composite body layer. The assembly layer includes a skeleton part and a buckle part that are integrally connected. The skeleton part is connected and attached to the inner surface of the composite body layer, and the buckle part is formed by extending outward from the skeleton part.

2. A fuselage skin according to claim 1, characterized in that: An appearance layer is formed on the outer surface of the composite body layer, and the appearance layer is a PUR layer. The PUR layer is formed on the outer surface of the composite body layer by injection molding.

3. A fuselage skin according to claim 2, characterized in that: The thickness of the PUR layer is 0.3-0.7 mm.

4. A fuselage skin according to claim 1, characterized in that: The composite body layer is based on a thermoplastic resin and is pre-impregnated with carbon fibers and molded. The thermoplastic resin is one or more of PC, PEEK or PET.

5. The fuselage skin according to claim 1, characterized in that: The thickness of the composite body layer is ≥0.2 mm.

6. A fuselage skin according to claim 1, characterized in that: The assembly layer is made of plastic material, including one or more plastic materials such as PC or ABS, and the thickness of the assembly layer is ≥0.8mm.

7. A fuselage outer skin, characterized in that: The fuselage outer skin is formed by the fuselage skin according to any one of claims 1 to 6.

8. A fuselage inner skin, characterized in that: A fuselage inner skin formed by the fuselage skin according to any one of claims 1 to 6.

9. A fuselage skin assembly, characterized in that: It comprises a fuselage outer skin and a fuselage inner skin, and the fuselage outer skin and the fuselage inner skin are assembled together through a snap-fit ​​part.

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