Aviation composite material part and forming device thereof
Through the integrated molding of the inner and outer plates and gas/water assisted molding of thermoplastic materials, the complex and non-recyclable problems of existing aviation parts are solved, and lightweight, environmentally friendly and efficient production of aviation composite parts is achieved.
Patent Information
- Application Number
- CN202510445336.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-10
- Publication Date
- 2025-07-01
AI Technical Summary
Existing aviation parts are made of thermosetting materials, with complex manufacturing processes and complex structures, unrecyclable materials, heavy weight and low strength.
The inner plate body and the outer plate body are composed of thermoplastic materials, and are integrated by thermoplastic molding. A reinforced inner cavity is formed between the inner plate body and the outer plate body, and a gas-assisted or water-assisted molding is used, and molded with upper and lower molds.
It achieves simple structure and lightweight, improves product strength and stiffness, recyclable materials, and is easy to surface treatment, reduces costs and improves production efficiency.
Smart Images
Figure CN120228933A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of fuselage products for flying cars, and particularly relates to an aviation composite part and its forming device. Background Art
[0002] Aviation parts are mainly used for the fuselage of aircraft, mainly including cabin doors, interior and exterior decorative covers, and reinforcing beams, etc. Existing aviation parts are generally composed of thermosetting materials, and aviation parts are mainly composed of an inner plate and an outer plate. Because thermosetting materials are used, the inner plate and the outer plate need to be formed separately by a autoclave during manufacturing, and then the inner plate and the outer plate are connected together by glue bonding or laser welding, and then puttying and painting operations are carried out in the middle. The whole process is complex, the structure is complex, the overall material is non-recyclable, and the weight is heavy and the overall strength is low. Summary of the Invention
[0003] The technical problem to be solved by the present invention is to provide an aviation composite part and its forming device with simple structure, convenient manufacturing and low cost in view of the current situation of the prior art.
[0004] The technical solution adopted by the present invention to solve the above technical problem is: an aviation composite part, characterized in that it includes an inner plate body and an outer plate body, both the inner plate body and the outer plate body are composed of thermoplastic materials, the inner plate body and the outer plate body are thermoformed into a whole, and an enhanced inner cavity is formed between the inner plate body and the outer plate body by gas-assisted or water-assisted means.
[0005] In the above-mentioned aviation composite part, there is a gas nozzle or a water nozzle between the inner plate body and the outer plate body.
[0006] In the above-mentioned aviation composite part, the outer plate body is made of a resin matrix mixed with fibers, the resin matrix is one of PA66, PA6, PPS or PC, the fiber is glass fiber or carbon fiber, and the fibers are distributed in a random orientation or a directional laying manner.
[0007] In the above-mentioned aviation composite part, the thickness of the outer plate body is 0.22 - 2 mm.
[0008] In the above-mentioned aviation composite part, the inner plate body is made of a resin matrix mixed with fibers, the resin matrix is one of PA66, PA6, PPS or PC, the fiber is glass fiber or carbon fiber, and the fibers are distributed in a random orientation or a directional laying manner.
[0009] In the above-mentioned aviation composite part, the thickness of the inner plate body is 0.22 - 2 mm.
[0010] In the above-mentioned aircraft composite part, the resin matrices of the inner plate body and the outer plate body have the same polarity and are compatible, or an additive is added between the resin matrices of the inner plate body and the outer plate body to make them compatible.
[0011] This patent also provides a forming device for an aircraft composite part, which is 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. There is an injection channel for gas-assisted or water-assisted injection between the upper mold and the lower mold. The inner plate body is molded by the first upper mold and the lower mold. The molded inner plate body is placed on the lower mold, and the outer plate body is laid on the inner plate body. After the second upper mold and the lower mold are closed, gas or liquid is filled through the injection channel and then molded into an aircraft composite part.
[0012] In the above-mentioned forming device for an aircraft composite part, the inner plate body and the outer plate body are formed separately. Among them, the inner plate body is molded and pre-formed into the shape of a gas or liquid channel, and the outer plate body is in a flat plate shape.
[0013] Compared with the prior art, the advantages of the present invention are that it adopts an integral demolding method, with precise positioning and a simple overall structure. It not only reduces the weight, but also greatly increases the strength and stiffness of the product. Moreover, the material is recyclable, more environmentally friendly, does not require puttying for surface treatment, and the overall process is simple: low cost, high efficiency, and suitable for mass production. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 is a schematic structural diagram of the inner plate body and the outer plate body of this aircraft composite part;
[0015] Figure 2 is Figure 1 is a schematic structural diagram after assembly;
[0016] Figure 3 is a schematic forming structure diagram of the forming device for this aircraft composite part. DETAILED DESCRIPTION OF THE INVENTION
[0017] The following are specific embodiments of the present invention in combination with the drawings, and the technical solutions of the present invention will be further described, but the present invention is not limited to these embodiments.
[0018] In the figure, inner plate body 100; outer plate body 200; inner cavity 300; first upper mold 401; second upper mold 402; lower mold 500; gas nozzle or water nozzle 600; injection channel 700.
[0019] Such as Figure 1 and Figure 2As shown, this aviation composite component includes an inner plate body 100 and an outer plate body 200. Both the inner plate body 100 and the outer plate body 200 are made of thermoplastic materials and are formed by compression molding. They can be used for cabin doors, interior and exterior decorative covers, and reinforcing beams, etc. Among them, the outer plate body 200 is made of a resin matrix mixed with fibers. The resin matrix is one of PA66, PA6, PPS, or PC, and the fiber is glass fiber or carbon fiber. The fibers are distributed in a random orientation or a directional lay-up manner. In this way, the entire outer plate body 200 is not only light in weight but also a recyclable material, which is more environmentally friendly. Here, the thickness of the product can be set according to actual needs. Taking the aviation composite component in this embodiment as an example, the thickness of the outer plate body 200 is 0.22 - 2 mm. Similarly, the inner plate body 100 is made of a resin matrix mixed with fibers. The resin matrix is one of PA66, PA6, PPS, or PC, and the fiber is glass fiber or carbon fiber. The fibers are distributed in a random orientation or a directional lay-up manner. The thickness of the inner plate body 100 is 0.22 - 2 mm. In order to make the bonding between the inner plate body 100 and the outer plate body 200 stronger, the polarities of the resin matrices of the inner plate body 100 and the outer plate body 200 are the same and can be compatible, or additives are added between the resin matrices of the inner plate body 100 and the outer plate body 200 to make the two compatible.
[0020] In order to increase the strength of the entire product and reduce the overall weight, the inner plate body 100 and the outer plate body 200 are thermoformed into a whole, and an enhanced inner cavity 300 is formed between the inner plate body 100 and the outer plate body 200 by gas-assisted or water-assisted means. The axial extension direction of the inner cavity 300 is consistent with the force-bearing direction of the composite material. Here, the inner cavity 300 not only reduces the weight but also greatly increases the flexural stiffness between the enhanced inner body and the outer plate body 200. In order to facilitate the forming of the entire inner cavity 300, there is a gas nozzle or a water nozzle 600 between the inner plate body 100 and the outer plate body 200.
[0021] Such as Figure 3As shown, this patent also provides a forming device for aviation composite 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 body 100 and the outer plate body 200 are formed separately. Among them, the inner plate body 100 is formed by die pressing with a mold and the shape of a gas or liquid channel is pre-formed in advance. The inner plate body 100 is formed by die pressing with the first upper mold 401 and the lower mold. The outer plate body 200 is in a flat plate shape. Here, there is an injection channel 700 for gas-assisted or water-assisted injection between the upper mold and the lower mold 500. First, the formed inner plate body 100 is placed on the lower mold 500, and the outer plate body 200 is laid on the inner plate body 100. After the second upper mold 402 and the lower mold 500 are closed, gas or liquid is filled through the injection channel 700 while die pressing to form an aviation composite part. Here, since the resin matrices of the inner plate body 100 and the outer plate body 200 have the same polarity, when die pressing, after heating, the inner plate body 100 and the outer plate body 200 are fused into a whole, and the whole product is integrally die pressed and includes an inner cavity 300. Through the whole device, the product not only reduces weight, but also greatly increases the strength and stiffness of the product, and the material is recyclable, more environmentally friendly, no puttying is required for surface treatment, and the overall process is simple.
[0022] The specific embodiments described herein are merely illustrative of the spirit of the present invention. Those skilled in the art of the present invention can make various modifications to the described specific embodiments or use similar ways to substitute, but will not deviate from the scope defined by the spirit of the present invention.
Claims
1. An aviation composite material component, characterized in that: It comprises an inner plate body and an outer plate body, both of which are made of thermoplastic material, are thermoplastically formed into a whole, 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 aviation composite material component according to claim 1, characterized in that: An air nozzle or a water nozzle is provided between the inner plate body and the outer plate body.
3. The aviation composite material component according to claim 1, characterized in that: The outer plate body is made of resin matrix mixed with fibers, the resin matrix is one of PA66, PA6, PPS or PC, the fibers are glass fibers or carbon fibers, and the fibers are distributed in a random orientation or directional layering manner.
4. The aviation composite material component according to claim 1, characterized in that: The thickness of the outer plate is 0.22-2 mm.
5. The aviation composite material component according to claim 1, characterized in that: The inner plate body is made of a resin matrix mixed with fibers, the resin matrix is one of PA66, PA6, PPS or PC, the fibers are glass fibers or carbon fibers, and the fibers are distributed in a random orientation or directional layering manner.
6. The aviation composite material component according to claim 1, characterized in that: The thickness of the inner plate is 0.22-2 mm.
7. The aviation composite material component according to claim 1, characterized in that: The resin matrices of the inner plate body and the outer plate body have the same polarity and can be melted together, or additives are added between the resin matrices of the inner plate body and the outer plate body to make the two melt together.
8. A molding device for aviation composite material parts, used for molding the aviation composite material parts as claimed in claim 1, 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 an air-assisted or water-assisted injection channel is provided between the upper mold and the lower mold, the inner panel is molded by the first upper mold and the lower mold, the molded inner panel is placed on the lower mold, and the outer panel is laid on the inner panel, and after the second upper mold and the lower mold are closed, gas or liquid is filled through the injection channel and then the aviation composite material parts are molded out.
9. The molding device for aviation composite material parts according to claim 8, characterized in that: The inner plate body and the outer plate body are formed separately, wherein the inner plate body is molded and pre-formed into the shape of a gas or liquid channel, and the outer plate body is in a flat plate shape.