Fuselage skin and assembly

Abstract

The utility model belongs to the technical field of fuselages for aerocars, and provides a fuselage skin and assembly, 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, the assembly body layer comprises a skeleton part and a buckle part which are integrally connected, the skeleton 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 utility model has the advantages that the structure is simple, the plastic buckling part which is composed of two parts and integrally forms the assembly body layer is not cracked, the buckling precision is high, the appearance surface treatment is not needed by adopting the PUR layer, the framework part of the assembly body layer plays a role of a reinforcing rib, the process is simple, the cost is low, the efficiency is high, and the mass production is realized.

Description

Technical Field

[0001] This utility model belongs to the technical field of fuselage products for flying cars, specifically relating to a fuselage skin and assembly. Background Technology

[0002] Vertical takeoff and landing (VTOL) aircraft (not just VTOL aircraft, but other aircraft as well as automobiles) often require the use of composite materials (not limited to carbon fiber, but also including, but not limited to, fiberglass) to form interior and exterior fuselage components. When assembling these components, drilling and rivet installation are necessary to attach connecting clips or adhesive clips. This connection method is complex; adhesive clips are prone to detachment, and drilling and rivet installation is complicated. Plastic clips are prone to cracking after installation, resulting in large dimensional deviations and requiring manual grinding for matching. The low positioning accuracy of the clips severely impacts production efficiency. Utility Model Content

[0003] The technical problem to be solved by this utility model is to provide a fuselage skin and assembly that is easy to install, has good matching degree, and is simple to manufacture, in light of the current state of the technology.

[0004] The technical solution adopted by this utility model to solve the above-mentioned technical problems is as follows: a fuselage skin and assembly, including 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 an integrally connected skeleton part and a buckle part, 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.

[0005] In the aforementioned fuselage skin and assembly, an outer surface layer is formed on the outer surface of the composite body layer. The outer surface layer is a PUR layer, which is injection molded onto the outer surface of the composite body layer.

[0006] In the aforementioned fuselage skin and assembly, the thickness of the PUR layer is 0.3-0.7 mm.

[0007] In the aforementioned fuselage skin and assembly, the composite body layer uses thermoplastic resin as a matrix, pre-impregnated with carbon fiber, and molded. The thermoplastic resin is one or more of PC, PEEK, or PET.

[0008] In the aforementioned fuselage skin and assembly, the thickness of the composite body layer is ≥0.2mm.

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

[0010] An outer fuselage skin, characterized in that the outer fuselage skin is formed from the aforementioned fuselage skin.

[0011] An inner fuselage skin, characterized in that it is formed from the aforementioned fuselage skin.

[0012] A fuselage skin and assembly, characterized in that it includes an outer fuselage skin and an inner fuselage skin, the outer fuselage skin and the inner fuselage skin being assembled together by a snap-fit ​​part.

[0013] Compared with the prior art, the advantages of this utility model are that it has a simple structure, consisting of two parts, and the plastic buckle part of the assembly layer is integrally formed, which will not crack, has high buckling precision, uses a PUR layer and does not require surface treatment, and the skeleton part of the assembly layer acts as a reinforcing rib. The process is simple, the cost is low, the efficiency is high, and it is suitable for mass production. Attached Figure Description

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

[0015] Figure 2 yes Figure 1 Schematic diagram of the BB-oriented structure;

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

[0017] Figure 4 yes Figure 2 A schematic diagram of the CC-direction structure;

[0018] Figure 5 This is a cross-sectional structural diagram of the assembly of the inner and outer fuselage skins. Detailed Implementation

[0019] The following are specific embodiments of the present invention, which are described in conjunction with the accompanying drawings. However, the present invention is not limited to these embodiments.

[0020] In the figure, the composite body layer is 100; the PUR layer is 200; the assembly layer is 300; the skeleton part is 400; the buckle part is 500; the outer skin of the fuselage is 600; and the inner skin of the fuselage is 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 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, especially 0.6-0.8mm. An appearance layer is formed on the outer surface of the composite body layer 100. The appearance layer is a PUR layer 200. The PUR layer 200 is injection molded on the outer surface of the composite body layer 100. The thickness of the PUR layer 200 is 0.3-0.7mm. The PUR layer 200 is a polyurethane layer, mainly using polyurethane as the raw material. When color is required, color paste is added to the polyurethane raw material. Here, the PUR layer 200 is used to replace the original painting, saving the painting and sanding processes, making the process simpler, in order to facilitate the conversion and 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 made of plastic material, including PC or ABS or one or more plastic materials. The thickness of the assembly layer 300 is ≥0.8mm, preferably 1-1.4mm. The assembly layer 300 includes an integrally connected skeleton part 400 and a snap-fit ​​part 500. The skeleton part 400 is connected and attached to the inner surface of the composite body layer 100, and the snap-fit ​​part 500 extends outward from the skeleton part 400. The snap-fit ​​part 500 here mainly serves as an assembly connection. The plastic snap-fit ​​part 500, which is integrally formed into the assembly layer 300, will not crack and has high snap-fit ​​precision, eliminating the original bonding and riveting steps. In addition, the skeleton part 400 also serves as a reinforcing rib for the composite body layer 100, which enhances the overall strength of the composite body layer 100. In this patent, the composite body layer 100 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 the composite body layer.

[0023] like Figure 2 , Figure 3 as well as Figure 4 As shown, based on the fuselage skin of this patent, an outer fuselage skin 600 and an inner fuselage skin 700 can be formed, such as... Figure 5 As shown, when the latching part 500 of the outer fuselage skin 600 is a latch head, then the latching part 500 of the inner fuselage skin 700 is a latch slot; when the latching part 500 of the outer fuselage skin 600 is a latch slot, then the latching part 500 of the inner fuselage skin 700 is a latch head. Figure 5 As shown, the final fuselage skin assembly includes an outer fuselage skin 600 and an inner fuselage skin 700, which are assembled together by a snap-fit ​​part 500.

[0024] The specific embodiments described herein are merely illustrative examples of the spirit of this utility model. Those skilled in the art to which this utility model pertains may make various modifications to the described specific embodiments or adopt similar methods to replace them, but without departing from the scope defined by the spirit of this utility model.

Claims

1. A fuselage skin and assembly comprising a composite body layer, characterised in that, The assembly layer is integrally formed on the inner side surface of the composite body layer, and the assembly layer comprises a skeleton part and a buckle part which are integrally connected.

2. A fuselage skin and assembly according to claim 1, wherein, The appearance layer is formed on the outer side surface of the composite body layer, and the appearance layer is a PUR layer which is injection molded on the outer side surface of the composite body layer.

3. A fuselage skin and assembly according to claim 2, wherein, The thickness of the PUR layer is 0.3-0.7 mm.

4. A fuselage skin and assembly according to claim 1, wherein, The composite body layer is formed by using thermoplastic resin as a base, pre-impregnating carbon fibers and molding.

5. A fuselage skin and assembly according to claim 1, wherein, The thickness of the composite body layer is greater than or equal to 0.2 mm.

6. A fuselage skin and assembly according to claim 1, wherein, The assembly layer is made of plastic material, and the assembly layer comprises one or more kinds of PC or ABS plastic material, and the thickness of the assembly layer is greater than or equal to 0.8 mm.

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