Forming die for aviation composite material part

Abstract

The utility model provides a forming die for aviation composite material parts, which comprises a supporting device, a high-temperature-resistant supporting layer, a glass fiber reinforced plastic airtight layer, a high-temperature wood replacing layer and a wear-resistant layer, the high-temperature-resistant supporting layer is connected to the upper surface of the supporting device, and the upper surface of the high-temperature-resistant supporting layer is machined to form a first forming surface; the glass fiber reinforced plastic airtight layer wraps the outer surface of the high-temperature-resistant supporting layer, the high-temperature wood replacing layer is arranged on the upper surface, corresponding to the first forming surface, of the glass fiber reinforced plastic airtight layer, the upper surface of the high-temperature wood replacing layer is machined to form a second forming surface, and the abrasion-resistant layer is arranged on the second forming surface. And the upper surface of the wear-resistant layer is polished to form a third forming surface. The forming die is simple in manufacturing process operation and few in working procedures, the production cycle of the forming die can be shortened by half, meanwhile, the production cost is reduced, the service life of the forming die can meet the research and development requirements, the competitive advantage of products is improved, and the forming die can be further suitable for forming processes such as autoclaves and OOA.

Description

Technical Field

[0001] The utility model relates to the technical field of molding dies, and particularly relates to a molding die for aerospace composite parts. Background Art

[0002] The molding processes of aerospace composite parts generally fall into 5 categories, including autoclave, OOA, filament winding, pultrusion, and liquid molding processes. Among them, the molding die is a necessary process equipment during preparation. Due to process requirements, the molding die needs to be resistant to high temperature and high pressure. Therefore, the die materials are usually selected from aluminum alloy, steel, fiberglass, carbon fiber, chopped fiber, etc. For the aerospace composite parts applied to R & D projects, the existing molding dies in the prior art have defects such as long manufacturing cycle and high cost. Especially for the molding dies made of invar steel and carbon fiber composite materials, the manufacturing cost is extremely high and the manufacturing cycle is also long. Although such dies have the advantage of long service life, for the molding dies applied to R & D projects, the long service life has little significance and positive impact on the R & D projects themselves. This is because for the requirements of R & D projects, the manufacturing cost of the molding die is a more important factor to consider, and shortening the manufacturing cycle of the molding die is more important, which is related to the progress of R & D projects. Summary of the Utility Model

[0003] The purpose of the utility model is to provide a molding die for aerospace composite parts. The molding die is applied to the composite parts of R & D projects, has a relatively short manufacturing cycle, can reduce production costs, and can also be applicable to autoclave and OOA molding processes, meeting the requirements of R & D projects, forming a rapid response mechanism, and improving the competitive advantage of products.

[0004] To achieve the above object, the utility model proposes the following technical solutions:

[0005] A molding die for aerospace composite parts, comprising a support device, a high-temperature resistant support layer, a fiberglass airtight layer, a high-temperature resistant substitute wood layer, and a wear-resistant layer;

[0006] The high-temperature resistant support layer is connected to the upper surface of the support device, and the upper surface of the high-temperature resistant support layer is machined to form a first molding surface;

[0007] The fiberglass airtight layer is coated on the outer surface of the high-temperature resistant support layer. The high-temperature resistant substitute wood layer is arranged on the upper surface of the fiberglass airtight layer corresponding to the first molding surface, and the upper surface of the high-temperature resistant substitute wood layer is machined to form a second molding surface;

[0008] The wear-resistant layer is arranged on the second molding surface, and the upper surface of the wear-resistant layer is polished to form a third molding surface.

[0009] As a preferred technical solution of the present utility model, the FRP airtight layer includes several layers of fiberglass cloth, and the several layers of fiberglass cloth are stacked and wrapped around the outer surface of the high-temperature resistant support layer.

[0010] As a preferred technical solution of the present utility model, the thickness of the fiberglass cloth is 2 mm - 8 mm, and the grammage of the fiberglass cloth is 400 g / m 2 .

[0011] As a preferred technical solution of the present utility model, the thickness of the high-temperature resistant wood substitute layer is 20 mm - 25 mm.

[0012] As a preferred technical solution of the present utility model, the surface roughness of the third forming surface is ≤ Ra1.6.

[0013] As a preferred technical solution of the present utility model, the support device includes a support frame and a support steel plate. The support frame includes at least 4 support columns and several connecting rods, and the connecting rods are connected between two adjacent support columns;

[0014] The support steel plate is connected to the top end of the support frame. The upper surface of the support steel plate is polished and cleaned, and the high-temperature resistant support layer is bonded to the upper surface of the support steel plate.

[0015] As a preferred technical solution of the present utility model, the outer surface of the support frame is successively provided with a sandblasting layer, an anti-rust primer layer and a topcoat layer from inside to outside.

[0016] As a preferred technical solution of the present utility model, the bottom end of the support column is provided with a universal rotating caster, and a self-locking component is arranged on the universal rotating caster.

[0017] As a preferred technical solution of the present utility model, the structural dimension accuracy of the first forming surface is within ±0.1 mm.

[0018] As a preferred technical solution of the present utility model, the structural dimension accuracy of the second forming surface is within ±0.5 mm.

[0019] Beneficial effects:

[0020] A molding die for an aviation composite part provided by the present utility model has simple structures of all components of the molding die, and the performance requirements and strength meet the R & D requirements. Its manufacturing process flow is simple and has few processes, so that the production cycle of the molding die can be shortened by half, and the production cost can be reduced at the same time. Moreover, the service life of the molding die can also meet the R & D requirements, forming a rapid response mechanism, improving the competitive advantage of products, and can also be applicable to molding processes such as autoclave and OOA.

[0021] It should be understood that all combinations of the foregoing concepts and additional concepts described in more detail below can be regarded as part of the utility model subject matter of the present disclosure as long as such concepts do not conflict with each other.

[0022] The foregoing and other aspects, embodiments, and features of the teachings of the present utility model can be more fully understood from the following description in conjunction with the accompanying drawings. Other additional aspects of the present utility model, such as the features and / or beneficial effects of exemplary embodiments, will be apparent from the following description or will be learned through the practice of specific embodiments in accordance with the teachings of the present utility model. Brief Description of the Drawings

[0023] The drawings are not drawn to scale with respect to actual reference objects. In the drawings, each identical or approximately identical component shown in each figure may be denoted by the same reference numeral. For the sake of clarity, not every component is labeled in each figure. Now, embodiments of various aspects of the present utility model will be described by way of example and with reference to the drawings, wherein:

[0024] Figure 1 is a schematic structural diagram of a molding die according to an embodiment of the present utility model.

[0025] The meanings represented by the reference numerals in the figures are as follows:

[0026] 1 - Support steel frame, 2 - Support steel plate, 3 - High-temperature support layer, 4 - Fiberglass airtight layer, 5 - High-temperature substitute wood layer, 6 - Wear-resistant layer, 7 - Universal rotating casters, 8 - Self-locking assembly Detailed Description of the Embodiments

[0027] To make the objectives, technical solutions, and advantages of the embodiments of the present utility model clearer, the technical solutions of the embodiments of the present utility model will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are some, but not all, of the embodiments of the present utility model. All other embodiments obtained by those of ordinary skill in the art without creative efforts based on the described embodiments of the present utility model fall within the scope of protection of the present utility model. Unless otherwise defined, the technical terms or scientific terms used herein shall have the ordinary meanings understood by those of ordinary skill in the art belonging to the field of the present utility model.

[0028] In the description of the utility model patent application and the claims, the terms "first", "second" and similar terms do not denote any order, quantity or importance, but are merely used to distinguish different components. Similarly, unless the context clearly indicates otherwise, singular forms such as "a", "an" or "the" and similar terms do not denote a limitation of quantity, but rather indicate the presence of at least one. Terms such as "comprising" or "including" mean that the elements or items appearing before "comprising" or "including" cover the features, wholes, steps, operations, elements and / or components listed after "comprising" or "including", and do not exclude the existence or addition of one or more other features, wholes, steps, operations, elements, components and / or their combinations. Terms such as "upper", "lower", "left" and "right" are only used to represent relative positional relationships, and when the absolute position of the object being described changes, the relative positional relationship may also change accordingly.

[0029] The molding die is an important process equipment for the production and molding of aerospace composite parts. For some aerospace composite parts used in R & D projects, the existing molding dies for such parts have defects such as high production cost and long production cycle. However, in R & D projects, the short-cycle requirement for the molding die is often more important than the long service life of the molding die. Therefore, the present utility model provides a molding die for aerospace composite parts applied to R & D projects. The various components of the molding die are simple in structure, which can shorten the production cycle by half and reduce the production cost at the same time. Moreover, the service life of the molding die can also meet the R & D requirements, form a rapid response mechanism, improve the competitive advantage of the product, and can also be applicable to molding processes such as autoclave and OOA.

[0030] The molding die for aerospace composite parts according to the embodiment of the present utility model, as Figure 1 shown, includes a support device, a high-temperature resistant support layer 3, a fiberglass airtight layer 4, a high-temperature resistant substitute wood layer 5 and a wear-resistant layer 6; the high-temperature resistant support layer 3 is connected to the upper surface of the support device, and a first molding surface is formed on the upper surface of the high-temperature resistant support layer 3 by machining. Preferably, the structural dimension accuracy of the first molding surface is within ±0.1 mm; the fiberglass airtight layer 4 covers the outer surface of the high-temperature resistant support layer 3, the high-temperature resistant substitute wood layer 5 is arranged on the upper surface of the fiberglass airtight layer 4 corresponding to the first molding surface, and a second molding surface is formed on the upper surface of the high-temperature resistant substitute wood layer 5 by machining. Preferably, the structural dimension accuracy of the second molding surface is within ±0.5 mm; the wear-resistant layer 6 is arranged on the second molding surface, and a third molding surface is formed on the upper surface of the wear-resistant layer 6 by polishing.

[0031] In an embodiment of the present utility model, the fiberglass airtight layer 4 includes several layers of fiberglass cloth, and the several layers of fiberglass cloth are laminated and coated on the outer surface of the high-temperature resistant support layer, that is, except for the bottom surface of the high-temperature resistant support layer 3 connected to the support device, other surfaces of the high-temperature resistant support layer 3 are coated with fiberglass cloth.

[0032] In some preferred embodiments of the present utility model, the thickness of the fiberglass cloth is 2 mm - 8 mm, and the gram weight of the fiberglass cloth is 400 g / m 2 . The thickness of the high-temperature resistant wood substitute layer 5 is 20 mm - 25 mm. The surface roughness of the third forming surface is ≤ Ra1.6.

[0033] In some specific embodiments of the present utility model, the support device includes a support frame 1 and a support steel plate 2. The support frame 1 includes at least 4 support columns and several connecting rods, and the connecting rods are connected between two adjacent support columns; the support steel plate 2 is connected to the top end of the support frame 1, and the upper surface of the support steel plate 2 is polished and cleaned, and the high-temperature resistant support layer 3 is bonded to the upper surface of the support steel plate 2. To enhance the strength and anti-corrosion performance of the support frame 1, a sandblasting layer, a rust-proof primer layer and a topcoat layer are sequentially provided on the outer surface of the support frame 1 from the inside to the outside.

[0034] During the manufacturing process, the mold needs to be frequently transported, such as transferred from the mold pretreatment workshop to the clean room, from the clean room to the heat curing area, and then from the curing area to the demolding area, etc. Therefore, for convenient movement, in some preferred embodiments of the present utility model, a universal rotating caster 7 is provided at the bottom end of the support column, and the universal rotating caster 7 is provided with a self-locking component 8. The mold can be conveniently transferred to a designated position or area through the universal rotating caster 7, and positioned and locked through the self-locking component 8 to ensure that the mold is fixed firmly. Among them, the universal rotating caster 7 and the self-locking component 8 can adopt existing technologies, and their specific structures and usage principles will not be elaborated here.

[0035] The manufacturing process of the forming mold provided by the embodiment of the present utility model specifically includes the following manufacturing steps:

[0036] Step (1): Bond the high-temperature resistant foam to the upper surface of the support device. After the high-temperature resistant foam is cured and shaped, a high-temperature resistant support layer 3 is formed, and the upper surface of the high-temperature resistant support layer 3 is machined to form a forming surface suitable for the structure of an aviation composite material part, so as to obtain a first semi-finished mold with a first forming surface. Among them, the structure of the first forming surface is determined by the specific structure of the specific aviation composite material part. To ensure the accuracy of the forming mold, the dimensional accuracy of the first forming surface is controlled within ±1 mm.

[0037] In some specific embodiments of the present utility model, the support device includes a support frame 1 and a support steel plate 2. Among them, the support frame 1 is welded by hollow section steel, such as the hollow section steel in GB / T6728-2017 "Cold-formed hollow section steel for structural use" can be used for welding, so as to ensure that the support frame 1 has sufficient strength to support the weight of the forming die. After the support frame 1 is welded, it is subjected to vibratory stress relief treatment to eliminate the welding stress of the frame, and then the support frame 1 is successively subjected to sandblasting treatment, spraying of anti-rust primer and spraying of topcoat to ensure that the support frame 1 has a long service life. Among them, the color of the topcoat can be selected according to the actual use situation, such as orange topcoat can be selected for spraying.

[0038] The support steel plate 2 is connected to the top end of the support frame. To ensure the overall strength and stability of the support device, in some preferred embodiments, the support steel plate 2 is fixedly connected to the top end of the support frame 1 by welding. The support steel plate 2 is mainly used to provide support for the high-temperature support layer 3, the fiberglass airtight layer 4 and the high-temperature wood substitute layer 5 to ensure the accuracy of the surface of the forming die. To ensure the tight connection between the support steel plate 2 and the high-temperature support layer 3, the upper surface of the support steel plate 2 is polished and cleaned, and then the high-temperature foam is bonded to the upper surface of the support steel plate 2 through high-temperature epoxy resin.

[0039] In some specific embodiments of the present utility model, the high-temperature foam is any one of foaming foam, PET foam and PMI foam. Specifically, a suitable high-temperature foam is selected according to the curing temperature required by the forming die, generally 120°C for medium-temperature epoxy and 180°C for high-temperature epoxy.

[0040] Step (2): Apply 3-5 layers of fiberglass cloth on the first forming surface of the first semi-finished mold, and let it stand for 20h-36h to enable the fiberglass cloth to be preliminarily cured to form the fiberglass airtight layer 4, obtaining a second semi-finished mold with the fiberglass airtight layer 4, and perform an airtightness test on the second semi-finished mold.

[0041] Among them, in some preferred embodiments of the present utility model, the thickness of the fiberglass cloth is 2mm-8mm, and the grammage of the fiberglass cloth is 400g / m 2 , and the number of layers of fiberglass cloth laid is determined according to the thickness of a single layer of fiberglass cloth and the required thickness of the forming die.

[0042] In the embodiment of the present utility model, after the glass fiber cloth is preliminarily cured to form the FRP airtight layer 4, it is necessary to perform an airtightness test on the second semi-finished mold with the FRP airtight layer 4. Only when the airtightness of the FRP airtight layer 4 meets the requirements can the next operation be carried out. Otherwise, the quality of the produced formed mold cannot meet the requirements. The specific airtightness test process is as follows: When the mold is empty, the second semi-finished mold is placed in a vacuum bag and sealed. The vacuum bag is evacuated to ≥950 mbar, the air extraction port of the vacuum bag is closed, and the pressure is maintained for 5 minutes. During this period, the pressure of the vacuum bag is detected and recorded. When the pressure drop of the vacuum bag is not greater than 20 mbar, it indicates that the airtightness of the FRP airtight layer is qualified and meets the use requirements, and then the next process can be carried out.

[0043] Step (3): Coat the upper surface of the FRP airtight layer 4 with high-temperature resistant wood substitute resin and let it stand for 20 h - 36 h to form a high-temperature resistant wood substitute layer 5 after the high-temperature resistant wood substitute resin is preliminarily cured. The thickness of the formed high-temperature resistant wood substitute layer 5 is 20 mm - 25 mm, and the thickness tolerance is ensured to be within ±5 mm, and there are no air bubbles or pores on the surface of the high-temperature resistant wood substitute layer 5. Machine process the upper surface of the high-temperature resistant wood substitute layer 5 to obtain a third semi-finished mold with a second formed surface. After the machining is completed, check whether there are defects such as air bubbles or pits on the second formed surface. If there are air bubbles or pores, grind the air bubble or pore area and scrape and coat high-temperature resistant repair putty for repair until the second formed surface is flat, and ensure that the accuracy of the second formed surface is within ±0.5 mm. In actual production, the accuracy requirements can be determined according to the accuracy requirements of the part product.

[0044] Step (4): Spray wear-resistant gel coat on the second formed surface of the third semi-finished mold and let it stand for 20 h - 36 h to form a wear-resistant layer 6 after the wear-resistant gel coat is preliminarily cured. Polish the upper surface of the wear-resistant layer 6 to obtain a fourth semi-finished mold with a third formed surface, wherein the surface roughness of the third formed surface ≤ Ra1.6.

[0045] Step (5): Place the fourth semi-finished mold in an oven or drying room for heating and curing to improve the TG value and high-temperature resistance of the mold. In actual production, the parameters of the heating and curing treatment are determined according to the characteristics of the material. For example, if it is required that the formed mold has a high-temperature resistance of 120 °C, the curing temperature can be raised to 130 °C, held for 2 h, and cooled naturally. After the heating and curing treatment is completed, comprehensively detect the obtained mold, including detecting its formed surface, ensuring that the surface roughness ≤ Ra1.6, and there are no voids, pits and other defects visible on the formed surface, and the airtightness, dimensional accuracy, etc. all meet the requirements. Only when all the item indicators are qualified can the formed mold be obtained.

[0046] Although the present utility model has been disclosed above with the preferred embodiments, it is not intended to limit the present utility model. Those of ordinary skill in the technical field to which the present utility model pertains can make various modifications and refinements without departing from the spirit and scope of the present utility model. Therefore, the protection scope of the present utility model shall be subject to what is defined by the claims.

Claims

1. A molding die for an aerospace composite part, characterized in that, It includes a support device, a high-temperature resistant support layer (3), a fiberglass airtight layer (4), a high-temperature resistant substitute wood layer (5) and a wear-resistant layer (6); The high-temperature resistant support layer (3) is connected to the upper surface of the support device, and the upper surface of the high-temperature resistant support layer (3) is machined to form a first formed surface; The fiberglass airtight layer (4) covers the outer surface of the high-temperature resistant support layer (3), the high-temperature resistant substitute wood layer (5) is arranged on the upper surface of the fiberglass airtight layer (4) corresponding to the first formed surface, and the high-temperature resistant substitute wood layer (5) is formed by curing and machining high-temperature resistant substitute wood resin to form a second formed surface; The wear-resistant layer is arranged on the second formed surface, and the upper surface of the wear-resistant layer (6) is polished to form a third formed surface.

2. The forming die for the aviation composite material part according to claim 1, characterized in that, The fiberglass airtight layer (4) includes several layers of fiberglass cloth, and several layers of the fiberglass cloth are laminated and covered on the outer surface of the high-temperature resistant support layer (3).

3. The molding die for aerospace composite parts according to claim 2, wherein, The thickness of the glass fiber cloth is 2 mm - 8 mm, and the grammage of the glass fiber cloth is 400 g / m 2 .

4. The forming die for aviation composite parts according to claim 1, characterized in that, The thickness of the high-temperature resistant substitute wood layer (5) is 20mm - 25mm.

5. The forming die for an aviation composite part according to claim 1, wherein, The surface roughness of the third formed surface is ≤ Ra1.

6.

6. The forming die for the aviation composite material part according to claim 1, characterized in that, The support device includes a support frame (1) and a support steel plate (2), the support frame includes at least 4 support columns and several connecting rods, and the connecting rods are connected between two adjacent support columns; The support steel plate (2) is connected to the top of the support frame (1), the upper surface of the support steel plate (2) is polished and cleaned, and the high-temperature resistant support layer (3) is bonded to the upper surface of the support steel plate (2).

7. The forming die for the aviation composite material part according to claim 6, characterized in that, The outer surface of the support frame (1) is sequentially provided with a sandblasting layer, an anti-rust primer layer and a topcoat layer from the inside to the outside.

8. The molding die for the aviation composite material part according to claim 6, characterized in that, The bottom end of the support column is provided with a universal rotating caster (7), and the universal rotating caster (7) is provided with a self-locking component (8).

9. The forming die for the aviation composite material part according to claim 1, wherein The structural dimension accuracy of the first formed surface is within ±0.1mm.

10. The forming die for the aviation composite material part according to claim 1, characterized in that, The structural dimension accuracy of the second formed surface is within ±0.5mm.

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