Inner plate reinforcing structure of fuselage skin

Abstract

The utility model belongs to the technical field of fuselages for aerocars, and provides a fuselage skin inner plate reinforcing structure which comprises a skin outer plate layer, a connecting part and an inner plate reinforcing layer. The skin outer plate layer and the inner plate reinforcing layer are connected into a whole through a connecting part, and the cavity is located between the skin outer plate layer and the inner plate reinforcing layer. The utility model has the advantages that the structure is simple, the weight is reduced through the inner plate reinforcing layer, the strength and the rigidity of the product are greatly improved, the whole 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, and specifically relates to a fuselage skin inner panel reinforcement structure. Background Technology

[0002] The skin is the main structure of the aircraft fuselage and widely uses composite materials. Composite materials have a variety of superior properties, including high specific strength, high specific modulus, good fatigue resistance, excellent high temperature performance, good shock absorption and good fracture safety. The skin mainly transmits tensile, compressive and shear loads. Existing skins are not only complex in structure and heavy in weight, but also have low overall strength and complex molding process. Utility Model Content

[0003] The technical problem to be solved by this utility model is to provide a fuselage skin inner panel reinforcement structure that is simple in structure, easy to manufacture, and has high strength, 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 inner panel reinforcement structure, characterized in that it includes an outer skin panel layer, a connecting part and an inner panel reinforcement layer, wherein the inner panel has a cavity, and the outer skin panel layer and the inner panel reinforcement layer are connected as a whole through the connecting part and the cavity is located between the outer skin panel layer and the inner panel reinforcement layer.

[0005] In the aforementioned fuselage skin inner panel reinforcement structure, the outer skin panel is made of composite material, which includes thermosetting composite material or thermoplastic composite material.

[0006] In the aforementioned fuselage skin inner panel reinforcement structure, the inner panel reinforcement layer can also be selected as a thermosetting composite material, thermoplastic composite material, plastic, or metal material.

[0007] In the aforementioned fuselage skin inner panel reinforcement structure, the resin matrix of the composite material can be plastic, glass, or ceramic, and the fiber of the composite material can be carbon fiber or glass fiber.

[0008] In one of the aforementioned fuselage skin inner panel reinforcement structures, the outer skin panel layer and the inner panel reinforcement layer are connected by bonding, hot melting, or chemical fusion.

[0009] In the aforementioned fuselage skin inner panel reinforcement structure, the outer skin panel layer and the inner panel reinforcement layer are connected as one unit and simultaneously placed into a molding die, and the cavity is formed under high pressure within the die.

[0010] As another approach, in the aforementioned fuselage skin inner panel reinforcement structure, the outer skin layer and the inner panel reinforcement layer are connected by welding, screwing, or snap-fitting.

[0011] In the aforementioned fuselage skin inner panel reinforcement structure, the inner panel reinforcement layer is separately formed into a cavity and connected to the outer skin panel layer as a whole through a connecting part.

[0012] Compared with the prior art, the advantages of this utility model are its simple structure. The inner plate reinforcement layer not only reduces the weight, but also greatly increases the product strength and rigidity. Furthermore, the overall process is simple, low in cost, high in efficiency, and mass-producible. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall structure of the fuselage skin inner panel reinforcement structure;

[0014] Figure 2 This is a structural diagram of one type of reinforcement structure for the inner panel of the fuselage skin;

[0015] Figure 3 This is a schematic diagram of the second type of reinforcement structure for the inner panel of the fuselage skin. Detailed Implementation

[0016] 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.

[0017] In the figure, the outer skin layer is 100; the connecting part is 200; the inner panel reinforcement layer is 300; and the cavity is 400.

[0018] like Figure 1 As shown, the fuselage skin inner panel reinforcement structure includes an outer skin layer 100, a connecting part 200, and an inner panel reinforcement layer 300. The outer skin layer 100 is made of composite material, including thermosetting composite material or thermoplastic composite material. The resin matrix of the composite material can be plastic, glass, or ceramic, and the fiber of the composite material can be carbon fiber or glass fiber. In aircraft, carbon fiber is preferred. The inner panel reinforcement layer 300 can also be made of thermosetting composite material, thermoplastic composite material, plastic, or metal material. In this embodiment, composite material is preferred. To increase the strength of the entire fuselage skin, the inner panel has a cavity 400, such as... Figure 2As shown, the outer skin panel 100 and the inner panel reinforcement layer 300 are connected as a whole and simultaneously placed into the molding die. The cavity 400 is formed in the die using internal high-pressure molding. Internal high-pressure molding uses liquid or gas to deform the material by controlling the pressure, thereby forming the cavity 400. One or two molds can be selected during molding. The outer skin panel 100 and the inner panel reinforcement layer 300 are connected as a whole by the connecting part 200, and the cavity 400 is located between the outer skin panel 100 and the inner panel reinforcement layer 300. In order to ensure the reliability of the connection, the connecting part 200 between the outer skin panel 100 and the inner panel reinforcement layer 300 is formed by bonding, hot melting or chemical fusion. Here, before the internal high-pressure molding of the inner panel reinforcement layer 300, the connecting part 200 is used to make the outer skin panel 100 and the inner panel reinforcement layer 300 fuse together, thereby preventing leakage during internal high-pressure molding.

[0019] like Figure 3 As shown, the outer skin layer 100 and the inner panel reinforcement layer 300 in the fuselage skin inner panel reinforcement structure are processed separately. The inner panel reinforcement layer 300 is formed separately to create a cavity 400. In this embodiment, the outer skin layer 100 and the inner panel reinforcement layer 300 are connected by welding, screwing, or snap-fitting to form a connection part 200, such as laser welding, vibration friction welding, etc. The connection part 200 is used to connect the outer skin layer 100 to the inner panel layer 100 as a whole, which not only reduces the weight but also greatly increases the product strength and rigidity. Moreover, the overall process is simple, low in cost, high in efficiency, and has mass production capability.

[0020] 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 inner panel stiffening structure, characterized by, The skin outer plate layer, the connecting part and the inner plate reinforcing layer are connected as a whole by the connecting part, and the cavity is located between the skin outer plate layer and the inner plate reinforcing layer.

2. A fuselage skin inner panel stiffening structure as claimed in claim 1, characterised in that, The skin outer plate layer is made of a composite material, and the composite material includes a thermosetting composite material or a thermoplastic composite material.

3. A fuselage skin inner panel stiffening structure as claimed in claim 2, characterised in that, The inner plate reinforcing layer can also be selected from a thermosetting composite material, a thermoplastic composite material, a plastic material or a metal material.

4. A fuselage skin inner panel stiffening structure as claimed in claim 2, characterised in that, The resin matrix of the composite material can be plastic, glass or ceramic, and the fiber of the composite material is carbon fiber or glass fiber.

5. A fuselage skin inner panel stiffening structure as claimed in claim 1, wherein, The skin outer plate layer and the inner plate reinforcing layer are connected by an adhesive, hot melt or chemical fusion connecting part.

6. A fuselage skin inner panel stiffening structure as claimed in claim 5, characterised in that, The skin outer plate layer and the inner plate reinforcing layer are connected as a whole and are simultaneously put into a forming mold, and the cavity is formed by high-pressure forming in the mold.

7. A fuselage skin inner panel stiffening structure as claimed in claim 1, wherein, The skin outer plate layer and the inner plate reinforcing layer are connected by a welding, screwing or clamping connecting part.

8. A fuselage skin inner panel stiffening structure as claimed in claim 7, characterised in that, The inner plate reinforcing layer is separately formed with the cavity, and is connected with the skin outer plate layer as a whole by the connecting part.

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