Multifunctional compatible composite material forming method

Abstract

The application provides a multifunctional compatibility composite material forming method, and the steps include: S1, designing and manufacturing a forming die of the multifunctional compatibility composite material; S2, after fixing a split male die in the forming die, brushing a layer of molybdenum disulfide on the surface of the split male die; S3, within the 2-4 hours of the activity period of the molybdenum disulfide, coating a sealing agent on the split male die as an oil-resistant layer; S4, coating an adhesive primer on the split male die coated with the sealing agent, and laying a part of prepreg; S5, after waiting for the sealing agent to vulcanize for 24-36 hours, continuing to lay the remaining prepreg to form a prepreg layer; S6, compacting the prepreg layer, using a vacuum bag to pressurize and solidify, and setting a solidification parameter; S7, after solidification demolding, obtaining the multifunctional compatibility composite material. The application can realize the sequential forming of the oil-resistant layer and the prepreg layer on the same set of molds, can design the forming die according to a certain structure to manufacture a high-temperature-resistant fuel storage structure form, improves the construction efficiency and shortens the construction time.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace functional material forming technology, in particular to a multifunctional compatibility composite material forming method. BACKGROUND

[0002] New spacecrafts are constantly pursuing high efficiency, low cost, long life and high reliability; the inner liner-free composite material structure tank is born under the demand. Due to the large application of the inner liner-free fuel tank in the field of aerospace, the research on the material and forming process technology is more and more urgent. As the carrier of fuel, the most important thing for the tank material is not to react with the stored fuel or be corroded by the fuel. However, as an organic solution, the composite matrix material will be partially dissolved in the fuel, and at the same time, the fuel contains a small amount of additive hydrocarbon compounds, which can penetrate into the composite material through micro voids and affect its mechanical properties. SUMMARY

[0003] The purpose of the present application is to overcome the defects of the prior art, and provide a multifunctional compatibility composite material preparation method, which can realize the sequential forming of the oil-resistant layer and the prepreg layer on the same set of molds, and can design the forming mold according to the structure form to manufacture a high-temperature-resistant fuel storage structure form, improve the construction efficiency and shorten the construction time.

[0004] In order to achieve the above purpose, the following specific technical scheme is adopted in the present application:

[0005] The multifunctional compatibility composite material forming method provided by the present application is realized by using a forming mold, and the forming mold comprises a core mold, a split male mold, a female mold, an upper end frame compression ring, a lower end frame compression ring and a base. The core mold is arranged at the center of the forming mold and fixed on the base. The split male mold is tightly attached to the outer wall of the core mold. The upper end frame compression ring is horizontally fixed on the end face of the core mold. The lower end frame compression ring is horizontally fixed on the bottom surface of the core mold. The female mold covers the outer wall of the split male mold. The multifunctional compatibility composite material forming method comprises the following steps:

[0006] S1. Design and manufacture a forming mold for multifunctional compatibility composite material;

[0007] S2. After fixing the split male mold in the forming mold, a layer of molybdenum disulfide is brushed on the surface of the split male mold;

[0008] S3. Within 2-4 hours of the activity period of the molybdenum disulfide, a sealant is applied on the split male mold to form an oil-resistant layer;

[0009] S4. After applying the sealant on the split male mold, a part of the prepreg is laid on the split male mold after applying the adhesive primer;

[0010] S5. After waiting for 24-36 hours of vulcanization of the sealant, the remaining prepreg is laid to form a prepreg layer.

[0011] S6. Compact the prepreg layer, use a vacuum bag for pressure curing and set the curing parameters;

[0012] S7. After curing and demolding, a multifunctional and compatible composite material is obtained.

[0013] Preferably, the sealant is a polysulfide sealant.

[0014] Preferably, the fibers in the prepreg layer are made of carbon fiber.

[0015] Preferably, the substrate of the prepreg layer is a high-temperature resistant material.

[0016] Preferably, the high-temperature resistant material is a cyanate ester or a bismaleimide resin.

[0017] Preferably, the curing parameters are: temperature 120℃~190℃, time 7~8h, pressure 0.3~0.5MPa, heating rate 0.5℃ / min~2℃ / min, and pressure rate 0.005MPa / min~0.02MPa / min.

[0018] The present invention can achieve the following technical effects:

[0019] 1. This invention can manufacture multifunctional compatible composite materials that combine mechanical properties, heat resistance, and oil resistance, and can be widely used according to actual needs.

[0020] 2. It can realize the sequential molding of oil-resistant layer and prepreg on the same set of molds. At the same time, the molding mold can be designed according to the structural form to produce high-temperature resistant fuel storage structure, which improves construction efficiency and shortens construction time. Attached Figure Description

[0021] Figure 1 This is a flowchart of a multifunctional compatibility composite material molding method provided according to an embodiment of the present invention.

[0022] Figure 2 This is a schematic diagram of the structure of a multifunctional compatibility composite material molding die provided according to an embodiment of the present invention.

[0023] Figure 3 This is a schematic diagram of a multifunctional compatibility composite material provided according to an embodiment of the present invention.

[0024] The reference numerals in the attached drawings include: 1. Prepreg layer; 2. Oil-resistant layer; 3. Core mold; 4. Split male mold; 5. Female mold; 6. Upper frame pressure ring; 7. Lower frame pressure ring; 8. Base. Detailed Implementation

[0025] In the following description, embodiments of the invention will be described with reference to the accompanying drawings. In the description below, the same modules are denoted by the same reference numerals. Where the same reference numerals are used, their names and functions are also the same. Therefore, their detailed description will not be repeated.

[0026] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not constitute a limitation thereof.

[0027] Figure 1 The flowchart of the multifunctional compatibility composite material molding method provided by an embodiment of the present invention is shown.

[0028] like Figure 1 As shown in the figure, a multifunctional compatibility composite material molding method provided by an embodiment of the present invention includes the following steps:

[0029] S1. Design and manufacture multi-functional compatible composite material molding dies.

[0030] S2. After fixing the segmented male mold 4, apply a layer of molybdenum disulfide to the surface of the male mold.

[0031] The purpose is to facilitate the separation of the sealant from the molding die after it has cured (demolding).

[0032] S3. During the 2-4 hour active period of molybdenum disulfide, apply sealant to the segmented male mold 4 to form an oil-resistant layer 2.

[0033] S4. After applying the adhesive primer to the segmented male mold 4 with the sealant, lay a portion of the prepreg.

[0034] It is beneficial for the sealant to bond with the prepreg layer 1, so that it will not detach.

[0035] S5. After the sealant has cured for 24-36 hours, continue laying the remaining prepreg. The sealant can be cured at room temperature, and after curing, it becomes a sealing material with good adhesion.

[0036] S6. After compacting the prepreg, use a vacuum bag for pressure curing. Set the curing parameters as follows: temperature 120℃~190℃, time 7~8h, pressure 0.3~0.5MPa, heating rate 1.5℃ / min, and pressure rate 0.015MPa / min.

[0037] S7. After curing, demold to obtain a multifunctional and compatible composite material.

[0038] Figure 2 The structure of the multifunctional compatible composite material molding die provided in an embodiment of the present invention is shown.

[0039] like Figure 2 As shown in the figure, a multifunctional compatibility composite material molding die provided in this embodiment of the invention includes a core mold 3, a segmented male mold 4, a female mold 5, an upper frame pressure ring 6, a lower frame pressure ring 7, and a base 8. The core mold 3 is placed in the center of the molding die and fixed on the base 8. The segmented male mold 4 is tightly attached to the outer wall of the core mold 3. The upper frame pressure ring 6 is horizontally fixed on the end face of the core mold 3, and the lower frame pressure ring 7 is horizontally fixed on the bottom surface of the core mold 3. The female mold 5 covers the outer wall of the segmented male mold 4 and leaves a gap between the female mold 5 and the segmented male mold 4.

[0040] Figure 3 The multifunctional compatibility composite material provided by an embodiment of the present invention is shown.

[0041] like Figure 3 As shown, the oil-resistant layer 2 is closely attached to the inner side of the prepreg layer 1. The sealant is polysulfide sealant, which can be cured at room temperature as the oil-resistant layer 2. The fibers in the prepreg layer 1 are selected from carbon fiber materials with excellent strength and modulus. The matrix in the prepreg layer 1 is selected from cyanate ester or bismaleimide resin with excellent high temperature resistance, mechanical properties and processability.

[0042] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0043] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

[0044] The specific embodiments of the present invention described above do not constitute a limitation on the scope of protection of the present invention. Any other corresponding changes and modifications made in accordance with the technical concept of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A method for molding a multifunctional compatible composite material, using a molding die, the molding die comprising a core mold (3), a segmented male mold (4), a female mold (5), an upper frame pressure ring (6), a lower frame pressure ring (7), and a base (8), wherein the core mold (3) is placed at the center of the molding die and fixed on the base (8), the segmented male mold (4) is tightly attached to the outer wall of the core mold (3), the upper frame pressure ring (6) is horizontally fixed to the end face of the core mold (3), the lower frame pressure ring (7) is horizontally fixed to the bottom surface of the core mold (3), and the female mold (5) covers the outer wall of the segmented male mold (4), characterized in that, Includes the following steps: S1. Design and manufacture molding dies for multifunctional and compatible composite materials; S2. After fixing the segmented male mold (4) in the molding mold, a layer of molybdenum disulfide is applied to the surface of the segmented male mold (4). S3. During the 2-4 hour active period of molybdenum disulfide, a sealant is applied to the segmented male mold (4) to form an oil-resistant layer (2); S4. After applying an adhesive primer to the segmented male mold (4) coated with the sealant, lay a portion of the prepreg. S5. The sealant is a polysulfide sealant. The sealant is cured at room temperature. After the sealant has been vulcanized for 24-36 hours, the remaining prepreg is laid to form a prepreg layer (1). S6. Compact the prepreg layer (1), use a vacuum bag for pressure curing and set the curing parameters; S7. After curing and demolding, a multifunctional and compatible composite material is obtained.

2. The multifunctional compatibility composite material molding method as described in claim 1, characterized in that, The fibers in the prepreg layer (1) are made of carbon fiber.

3. The multifunctional compatibility composite material molding method as described in claim 1 or 2, characterized in that, The substrate of the prepreg layer (1) is a high-temperature resistant material.

4. The multifunctional compatibility composite material molding method as described in claim 3, characterized in that, The high-temperature resistant material is a cyanate ester or a bismaleimide resin.

5. The multifunctional compatibility composite material molding method as described in claim 1, characterized in that, The curing parameters are as follows: temperature 120℃~190℃, time 7~8h, pressure 0.3~0.5MPa, heating rate 0.5℃ / min~2℃ / min, and pressure rate 0.005MPa / min~0.02MPa / min.

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