Aviation composite material part and forming device thereof

Abstract

The utility model belongs to the technical field of fuselage products for aerocars, and provides an aviation composite material part and a forming device thereof, the aviation composite material part comprises an inner plate body and an outer plate body, the inner plate body and the outer plate body are both made of thermoplastic materials, and the inner plate body and the outer plate body are formed into a whole through an upper mold and a lower mold in a thermoplastic mode. And a reinforced inner cavity is formed between the inner plate body and the outer plate body through gas assistance or water assistance. The utility model has the advantages that: an integrated demoulding mode is adopted, the position is accurate, the whole structure is simple, the weight is reduced, the strength and rigidity of the product are greatly increased, the material is recyclable, the environment-friendly effect is realized, puttying is not needed in surface treatment, 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, specifically relating to an aviation composite material component and its molding device. Background Technology

[0002] Aviation components are mainly used in aircraft fuselages and include cabin doors, interior and exterior trim panels, and reinforcing beams. Existing aviation components are generally made of thermosetting materials. Aviation components are mainly composed of inner and outer panels. Because thermosetting materials are used, the inner and outer panels need to be formed separately in an autoclave during manufacturing. Then, the inner and outer panels are joined together by adhesive bonding or laser welding. After that, puttying and painting are carried out. The whole process is complicated, the structure is complicated, the materials are not recyclable, and the weight is heavy with low overall strength. Utility Model Content

[0003] The technical problem to be solved by this utility model is to provide an aerospace composite material part and its molding device that are simple in structure, easy to manufacture and low in cost, 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: an aerospace composite material component, characterized in that it includes an inner plate and an outer plate, both of which are composed of thermoplastic materials, and the inner plate and the outer plate are thermoplastically molded into a whole, and a reinforced inner cavity is formed between the inner plate and the outer plate through air-assisted or water-assisted processes.

[0005] In one of the aforementioned aerospace composite material components, an air nozzle or water nozzle is provided between the inner plate and the outer plate.

[0006] In the aforementioned aerospace composite material component, the outer plate is made of a resin matrix mixed with fibers. The resin matrix is ​​one of PA66, PA6, PPS or PC, and the fibers are glass fibers or carbon fibers, distributed in a random orientation or oriented layup manner.

[0007] In the aforementioned aerospace composite material component, the thickness of the outer plate is 0.22-2 mm.

[0008] In the aforementioned aerospace composite material component, the inner plate is made of a resin matrix mixed with fibers. The resin matrix is ​​one of PA66, PA6, PPS or PC, and the fibers are glass fibers or carbon fibers, distributed in a random orientation or oriented layup manner.

[0009] In the aforementioned aerospace composite material component, the thickness of the inner plate is 0.22-2 mm.

[0010] In the aforementioned aerospace composite material component, the resin matrices of the inner plate and the outer plate have the same polarity and are compatible, or additives are added between the resin matrices of the inner plate and the outer plate to make them compatible.

[0011] This patent also provides a molding device for aerospace composite material parts, characterized in that it includes an upper mold and a lower mold, the upper mold is divided into a first upper mold and a second upper mold, wherein there is a gas-assisted or water-assisted injection channel between the upper mold and the lower mold, the inner plate is molded by the first upper mold and the lower mold, the molded inner plate is placed on the lower mold, and the outer plate is laid on the inner plate, after the second upper mold and the lower mold are closed, gas or liquid is injected through the injection channel and the aerospace composite material parts are molded out.

[0012] In the aforementioned molding apparatus for aerospace composite material parts, the inner plate and the outer plate are molded separately. The inner plate is molded and pre-formed with the shape of a gas or liquid channel, while the outer plate is flat.

[0013] Compared with the existing technology, the advantages of this utility model are that it adopts an integrated molding method, which is precise in position and simple in overall structure. It not only reduces the weight, but also greatly increases the strength and rigidity of the product. Moreover, the material is recyclable, which is more environmentally friendly. The surface treatment does not require puttying, and the overall process is simple, low in cost, high in efficiency, and has mass production capability. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the inner and outer plate structures of the aerospace composite material parts;

[0015] Figure 2 yes Figure 1 This is a schematic diagram of the assembled structure;

[0016] Figure 3 This is a schematic diagram of the molding structure of the molding device for composite material parts of this aircraft. Detailed Implementation

[0017] 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.

[0018] In the figure, the inner plate is 100; the outer plate is 200; the inner cavity is 300; the first upper mold is 401; the second upper mold is 402; the lower mold is 500; the air nozzle or water nozzle is 600; and the injection channel is 700.

[0019] like Figure 1 and Figure 2As shown, this aerospace composite material component includes an inner plate 100 and an outer plate 200. Both the inner plate 100 and the outer plate 200 are composed of thermoplastic materials and are molded. They can be used for cabin doors, interior and exterior trim panels, and reinforcing beams, etc. The outer plate 200 is made of a resin matrix mixed with fibers. The resin matrix is ​​one of PA66, PA6, PPS, or PC, and the fibers are glass fiber or carbon fiber. The fibers are distributed in a random orientation or oriented layup manner. Thus, the entire outer plate 200 is not only lightweight but also a recyclable material, making it more environmentally friendly. The thickness of the product can be set according to actual needs. In this embodiment, Taking aerospace composite material parts as an example, the thickness of the outer plate 200 is 0.22-2mm. Similarly, the inner plate 100 is made of resin matrix mixed with fiber. The resin matrix is ​​one of PA66, PA6, PPS or PC, and the fiber is glass fiber or carbon fiber. The fiber is distributed in a random orientation or oriented layup manner. The thickness of the inner plate 100 is 0.22-2mm. In order to make the inner plate 100 and the outer plate 200 more bonded, the resin matrix of the inner plate 100 and the outer plate 200 have the same polarity and can be fused together, or additives are added between the resin matrix of the inner plate 100 and the outer plate 200 to make them fused together.

[0020] To increase the overall strength of the product and reduce its overall weight, the inner panel 100 and the outer panel 200 are thermoplastically molded into a single unit. A reinforced inner cavity 300 is formed between the inner panel 100 and the outer panel 200 through air-assisted or water-assisted molding. The axial extension direction of the inner cavity 300 is consistent with the stress direction of the composite material. Here, the inner cavity 300 not only reduces the weight but also greatly increases the bending stiffness between the reinforced inner panel and the outer panel 200. To facilitate the molding of the entire inner cavity 300, an air nozzle or water nozzle 600 is provided between the inner panel 100 and the outer panel 200.

[0021] like Figure 3As shown, this patent also provides a molding device for aerospace composite material parts, mainly including an upper mold and a lower mold 500. The upper mold is divided into a first upper mold 401 and a second upper mold 402. Here, the inner plate 100 and the outer plate 200 are molded separately. The inner plate 100 is pre-formed with gas or liquid channels by mold compression molding. The inner plate 100 is formed by compression molding through the first upper mold 401 and the lower mold. The outer plate 200 is flat. Here, there is a gas-assisted or water-assisted injection channel 700 between the upper mold and the lower mold 500. First, the pre-formed inner plate 100 is placed on the lower mold 500. An outer plate 200 is laid on the inner plate 100. After the second upper mold 402 and the lower mold 500 are closed, gas or liquid is injected through the injection channel 700 to simultaneously mold the aerospace composite material parts. Since the resin matrix of the inner plate 100 and the outer plate 200 have the same polarity, after heating during molding, the inner plate 100 and the outer plate 200 fuse into a whole. The entire product is integrally molded and includes the inner cavity 300. The entire device not only reduces the weight of the product, but also greatly increases the product strength and rigidity. Moreover, the material is recyclable, making it more environmentally friendly. Surface treatment does not require puttying, and the overall process is simple.

[0022] 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. An aerospace composite part, characterized in that, The inner plate body and the outer plate body are both made of thermoplastic material, the inner plate body and the outer plate body are integrally formed by thermoplastic forming, and a reinforced inner cavity is formed between the inner plate body and the outer plate body by air-assisted or water-assisted.

2. An aircraft composite part according to claim 1, wherein, The inner plate body and the outer plate body have an air nozzle or a water nozzle therebetween.

3. An aircraft composite part according to claim 1, wherein, The outer plate body is made of a resin matrix mixed with fibers, the resin matrix is one of PA66, PA6, PPS or PC, and the fibers are glass fibers or carbon fibers, which are distributed in a random orientation or in a directional layering manner.

4. An aircraft composite part according to claim 1, wherein, The thickness of the outer plate body is 0.22-2mm.

5. An aircraft composite part according to claim 1, wherein, The inner plate body is made of a resin matrix mixed with fibers, the resin matrix is one of PA66, PA6, PPS or PC, and the fibers are glass fibers or carbon fibers, which are distributed in a random orientation or in a directional layering manner.

6. An aircraft composite part according to claim 1, wherein, The thickness of the outer plate body is 0.22-2mm.

7. An aircraft composite part according to claim 1, wherein, The resin matrix of the inner plate body and the outer plate body has the same polarity and can be fused, and / or additives are added between the resin matrix of the inner plate body and the outer plate body to make them fused.

8. A molding apparatus for an aeronautical composite component, for molding the aeronautical composite component according to claim 1, characterized in that, The upper mold is divided into a first upper mold and a second upper mold, wherein the upper mold and the lower mold have an injection channel for air-assisted or water-assisted injection therebetween, the inner plate body is formed by the first upper mold and the lower mold, the formed inner plate body is placed on the lower mold, the outer plate body is laid on the inner plate body, the second upper mold and the lower mold are closed, and then the aviation composite material part is formed by injecting gas or liquid through the injection channel.

9. The device for forming an aeronautical composite component according to claim 8, characterized in that, The inner plate body and the outer plate body are formed respectively, wherein the inner plate body is formed by molding and the shape of the gas or liquid channel is pre-formed, and the outer plate body is in the form of a flat plate.

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