Low-altitude aircraft transparent part

Abstract

The utility model belongs to the technical field of aerocar parts, and provides a low-altitude aircraft transparent part which comprises a base material body, a PUR layer and a composite membrane layer, the base material body, the PUR layer and the composite membrane layer are integrally formed in a mold, and the composite membrane layer is formed on the inner side face of the base material body in the mold. The PUR layer is formed on the outer surface of the substrate body in the mold. The base material has the advantages that the toughness and the heat resistance of the base material body are greatly improved, and the bird strike experiment can be effectively met; through reaction molding in the film, the composite film sheet or the hardened coating can effectively improve the scratch resistance and the weather resistance; the composite membrane and the in-membrane forming can be formed in one step on a mold in the process, the production process is shortened and optimized, the production cost is greatly reduced, and the production efficiency and qualification of products can be improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of flying automobile parts and relates to a transparent part for low-altitude aircraft. Background Art

[0002] At present, aviation transparent parts and low-altitude aircraft transparent parts are basically produced by hot bending, molding or vacuum forming of plates, and then processed by CNC, and finally surface polishing. This process is complicated, strict, time-consuming and inefficient. Utility Model Content

[0003] The technical problem to be solved by the utility model is to provide a transparent part for low-altitude aircraft which is scratch-resistant and weather-resistant, reduces and optimizes the production process, greatly reduces the production cost, and improves the production efficiency and qualified rate of the product in view of the current status of the existing technology.

[0004] The technical solution adopted by the utility model to solve the above-mentioned technical problems is: a low-altitude aircraft transparent part, characterized in that it includes a substrate body, a UR layer and a composite membrane layer, the substrate body, the PUR layer and the composite membrane layer are integrally formed in a mold, the composite membrane layer is formed on the inner side surface of the substrate body in the mold, and the PUR layer is formed on the outer surface of the substrate body in the mold.

[0005] As one of the ways, in the above-mentioned low-altitude aircraft transparent part, the substrate body is made of PC material, and the composite film layer is a PC layer and a PMMA layer.

[0006] As another way, in the above-mentioned low-altitude aircraft transparent part, the substrate body is made of PC material, and the composite film layers are PC layer, hardening layer, anti-reflection layer and protective layer in sequence. The hardening layer is formed on the inner side of the PC layer, and the anti-reflection layer is located between the hardening layer and the protective layer.

[0007] As a third method, in the above-mentioned low-altitude aircraft transparent part, the substrate body is made of PC material, and the composite film layer includes a protective coating, a conductive coating, a PC layer, a hardening layer, an anti-reflection layer and a protective layer in sequence. The hardening layer is formed on the inner side of the PC layer, the anti-reflection layer is located between the hardening layer and the protective layer, and a conductive coating is also provided between the protective coating and the PC layer.

[0008] As a fourth method, in the above-mentioned low-altitude aircraft transparent part, the composite film layer includes a PC layer, a first adhesive layer, a dimming layer, a second adhesive layer, a PMMA layer, a hardening layer, an anti-reflection layer and a protective layer in sequence, the dimming layer is located between the two adhesive layers, the PMMA layer is bonded to the inner side of the dimming layer through the first adhesive layer, and the hardening layer, the anti-reflection layer and the protective layer are formed in sequence on the inner side of the PMMA layer.

[0009] Compared with the prior art, the advantages of the present invention are that the toughness and heat resistance of the substrate body are greatly improved, which can effectively meet the bird strike test; through the reaction molding in the film, the composite film or the hardened coating, the scratch resistance and weather resistance can be effectively improved; in terms of technology, the composite film and the film molding can be formed in one step on the mold, which shortens and optimizes the production process, greatly reduces the production cost, and can also improve the production efficiency and qualification of the product. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 It is a schematic diagram of the exploded structure of the transparent parts of this low-altitude aircraft;

[0011] Figure 2 This is a schematic diagram of the structure of the first composite film layer of the transparent part of the low-altitude aircraft;

[0012] Figure 3 This is a schematic diagram of the structure of the second composite film layer of the transparent part of the low-altitude aircraft;

[0013] Figure 4 This is a schematic diagram of the structure of the third composite film layer of the transparent part of the low-altitude aircraft;

[0014] Figure 5 It is a schematic diagram of the structure of the fourth composite film layer of the transparent part of the low-altitude aircraft. DETAILED DESCRIPTION

[0015] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0016] In the description of the present invention, it is necessary to understand that the terms "center", "lateral", "longitudinal", "front", "rear", "left", "right", "up", "down", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the scope of protection of the present invention.

[0017] In the figure, there are a substrate body 100, a PUR layer 200, a PMMA layer 300, a hardening layer 400, an anti-reflection layer 500, a protective layer 600, a conductive coating 700, a dimming layer 800, a first adhesive layer 900, a second adhesive layer 1000, a PC layer 1001, a protective coating 1002, and a composite film layer 1003.

[0018] like Figure 1 and Figure 2 As shown, the low-altitude aircraft transparent component includes a substrate body 100, a PUR layer 200 and a composite film layer 1003. The substrate body 100, the PUR layer 200 and the composite film layer 1003 are integrally formed in a mold. The composite film layer 1003 is formed on the inner side of the substrate body 100 in the mold, and the PUR layer 200 is formed on the outer surface of the substrate body 100 in the mold. Here, the composite film layer 1003 can be formed in one step on the mold, which reduces and optimizes the production process, greatly reduces the production cost, and can also improve the product quality. Production efficiency and qualified rate are improved to improve the toughness and heat resistance of transparent parts, which can effectively meet the bird strike test. Here, the substrate body 100 is made of PC material, and the composite film layer 1003 is a PC layer 1001 and a PMMA layer 300. Various paint layers can be omitted through the PUR layer 200. The substrate body 100 is made of PC material. The first shot is injected into the film through the composite film layer 1003 by IML process. The second shot forms a PUR protective medium on the outer surface through the reaction in the film. The mold is formed in one step to achieve scratch resistance and weather resistance requirements.

[0019] like Figure 2 As shown, as the second method, the substrate body 100 is made of PC material, and the composite film layer 1003 is a PC layer 1001, a hardening layer 400, an anti-reflection layer 500 and a protective layer 600 in sequence. The hardening layer 400 is formed on the inner side of the PC layer 1001, and the anti-reflection layer 500 is located between the hardening layer 400 and the protective layer 600. The hardness of the entire low-altitude aircraft transparent part is enhanced by the hardening layer 400, and the anti-reflection layer 500 can improve the light transmittance of the product.

[0020] like Figure 3As shown, as the third method, the substrate body 100 is made of PC material, and the composite film layer 1003 includes a protective coating 1002, a conductive coating 700, a PC layer 1001, a hardening layer 400, an anti-reflection layer 500 and a protective layer 600 in sequence. The hardening layer 400 is formed on the inner side of the PC layer 1001, and the anti-reflection layer 500 is located between the hardening layer 400 and the protective layer 600. A conductive coating 700 is also provided between the protective coating 1002 and the substrate body 100. Here, the hardening layer 400 is used to enhance the hardness of the entire low-altitude aircraft transparent part. At the same time, the anti-reflection layer 500 can improve the light transmittance of the product, and the conductive coating 700 can meet the windshield heating requirements and meet the deicing and defogging performance.

[0021] like Figure 4 As shown, as the fourth method, the composite film layer 1003 includes a PC layer 1001, a first adhesive layer 900, a dimming layer 800, a second adhesive layer 1000, a PMMA layer 300, a hardening layer 400, an anti-reflection layer 500 and a protective layer 600 in sequence. The dimming layer 800 is located between the two adhesive layers. The PMMA layer 300 is bonded to the inner side of the dimming layer 800 through the first adhesive layer 900. The hardening layer 400, the anti-reflection layer 500 and the protective layer 600 are formed in sequence on the inner side of the PMMA layer 300. Here, the dimming layer 800 can improve the light transmittance of the product and realize the light and dark effect adjustment function of the transparent part. At the same time, the anti-reflection layer 500 can improve the light transmittance of the product and realize the surface scratch resistance and weather resistance requirements.

[0022] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0023] The specific embodiments described herein are merely examples of the spirit of the present invention. Those skilled in the art may make various modifications or additions to the specific embodiments described or replace them in similar ways, but they will not deviate from the spirit of the present invention or exceed the scope defined by the appended claims.

Claims

1. A low-altitude aircraft transparent part, characterized in that: It includes a substrate body, a UR layer and a composite membrane layer. The substrate body, the PUR layer and the composite membrane layer are integrally formed in a mold. The composite membrane layer is formed on the inner side of the substrate body in the mold, and the PUR layer is formed on the outer surface of the substrate body in the mold.

2. A low-altitude aircraft transparent component according to claim 1, characterized in that: The substrate body is made of PC material, and the composite film layer is a PC layer and a PMMA layer.

3. A low-altitude aircraft transparent component according to claim 1, characterized in that: The substrate body is made of PC material, and the composite film layers are PC layer, hardening layer, anti-reflection layer and protective layer in sequence. The hardening layer is formed on the inner side of the PC layer, and the anti-reflection layer is located between the hardening layer and the protective layer.

4. A low-altitude aircraft transparent component according to claim 1, characterized in that: The substrate body is made of PC material, and the composite film layer includes a protective coating, a conductive coating, a PC layer, a hardening layer, an anti-reflection layer and a protective layer in sequence. The hardening layer is formed on the inner side of the PC layer, the anti-reflection layer is located between the hardening layer and the protective layer, and a conductive coating is also provided between the protective coating and the PC layer.

5. The low-altitude aircraft transparent component according to claim 1, characterized in that: The composite film layer includes a PC layer, a first adhesive layer, a dimming layer, a second adhesive layer, a PMMA layer, a hardening layer, an anti-reflection layer and a protective layer in sequence. The dimming layer is located between the two adhesive layers. The PMMA layer is bonded to the inner side of the dimming layer through the first adhesive layer. The hardening layer, the anti-reflection layer and the protective layer are formed in sequence on the inner side of the PMMA layer.

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