Molding method of omega-shaped thin-wall cavity composite material and metal embedded part

Abstract

The invention discloses a forming method of an omega-shaped thin-wall cavity composite material and a metal embedded part. The forming method comprises the steps that S10, materials are prepared; s20, gluing a glue film; s30, paving and pasting; s40, prepressing is carried out; s50, performing hot compaction; s60, curing is carried out; the method has the beneficial effects that the groove is designed in the metal embedded part through the method, the adhesive film is attached to the interior of the groove, deformation can be achieved in the cooling process after curing, internal stress generated due to the fact that thermal expansion coefficients of the metal embedded part and the composite material are not matched is counteracted, and the problem that deformation is generated due to too large internal stress is solved; and the dimensional stability of the composite material is greatly improved.

Description

Technical Field

[0001] The present invention relates to a forming method for Ω-shaped thin-walled cavity composite materials and metal embedded parts. Background Art

[0002] In the fields of modern industry and engineering, composite materials are widely used in industries such as aerospace, automotive manufacturing, building structures, and medical devices due to their excellent mechanical properties, light weight, high strength, and designability. Especially the Ω-shaped thin-walled cavity structure, due to its special geometric shape, can provide good mechanical support and space enclosure, so it is particularly important in applications requiring high strength and light weight.

[0003] However, there are some technical challenges in the traditional forming methods for composite materials and metal embedded parts. First, the thermal expansion coefficients of metals and composite materials are usually different, which may cause the generation of internal stresses during curing and use, leading to deformation or damage of the structure. Second, the bonding strength between the composite material and the metal embedded part is insufficient, which may cause delamination or debonding of the structure when stressed. In addition, the residual gas during the forming process may also cause the formation of bubbles and voids, affecting the structural integrity and mechanical properties of the product. In view of this, the present invention proposes a forming method for Ω-shaped thin-walled cavity composite materials and metal embedded parts to solve the above problems. Summary of the Invention

[0004] The purpose of the present invention is to provide a forming method for Ω-shaped thin-walled cavity composite materials and metal embedded parts to solve the problems raised in the above background art.

[0005] To achieve the above purpose, the present invention provides the following technical solutions: A forming method for Ω-shaped thin-walled cavity composite materials and metal embedded parts, characterized by comprising the following steps: S10. Material preparation: Prepare composite materials, metal embedded parts, and a film adhered around the metal embedded parts; S20. Film adhesion: Open grooves on the surface of the metal embedded part and closely adhere the film in the grooves; S30. Laying: Apply a release agent on the surface of the metal tooling. After the release agent dries, lay the composite material on the Ω-shaped metal forming tooling according to the design requirements, and repeat this step to lay multiple layers on the surface of the metal tooling. During the laying process of the composite material, embed the metal embedded part in step S20 into the Ω shape between two layers of the composite material and fix it through the film; S40. Preloading: The metal embedded parts completed in S30 are encapsulated with auxiliary materials such as isolation film, breather felt, and vacuum bag, and vacuum preloading is carried out. S50. Hot Compaction: After S40 is completed, 1 - 3 layers of composite materials are continuously laid on the Ω-shaped composite material in S30. The laying position is adapted to the metal embedded parts, and it is encapsulated again with auxiliary materials such as isolation film, breather felt, and vacuum bag, and then sent into the autoclave for hot compaction. S60. Curing: After S50 is completed, composite materials are continuously laid. The laying position is adapted to the metal embedded parts. After laying, vacuum preloading is carried out, then it is encapsulated, and then sent into the autoclave for pressure curing.

[0006] As an improvement of the above technical solution, the composite material is composed of a resin-based composite material and a fiber-reinforced material, and the metal embedded parts are made of titanium alloy material.

[0007] As an improvement of the above technical solution, in S20, the groove is opened at the position where the metal embedded parts contact the composite material.

[0008] As an improvement of the above technical solution, in S20, two groups of adhesive films are attached in the groove, and the thickness of the two groups of adhesive films is greater than the depth of the groove.

[0009] As an improvement of the above technical solution, in S50, the hot compaction conditions are: hot compaction temperature 40°C - 60°C, hot compaction pressure 0.3 Mpa - 0.6 Mpa, and hot compaction time at least 30 min.

[0010] As an improvement of the above technical solution, in S50, heating starts when the pressure reaches the set pressure. During the hot compaction stage, keep vacuum pumping at least -60 KPa and preload for at least 30 min.

[0011] As an improvement of the above technical solution, in S50, the gas is pre-discharged before hot compaction, and the gas between the metal embedded parts and the composite material is discharged again through hot compaction.

[0012] Compared with the prior art, the beneficial effects of the present invention are: By designing grooves on the metal embedded parts and attaching adhesive films in the grooves through the above method, it can deform during the cooling process after curing, offset the internal stress generated by the mismatch of the thermal expansion coefficients of the metal embedded parts and the composite material, solve the problem of deformation caused by excessive internal stress, and greatly improve the dimensional stability of the composite material; Using auxiliary materials such as isolation film, breather felt, and vacuum bag for encapsulation and preloading ensures the close fit between the composite material and the metal embedded parts, and enhances the overall structural strength of the formed part; Through the hot compaction and pressurized curing steps in an autoclave, a firm bond between the composite material and the metal embedded part is achieved, improving the mechanical properties and environmental resistance of the formed part; This method is applicable to combinations of various composite materials and metal embedded parts, has good versatility and adaptability, and can meet the requirements of different application scenarios. Description of the Drawings

[0013] Figure 1 It is a schematic diagram of the position of the metal work and the metal embedded part of the present invention; Figure 2 It is a schematic diagram of the structure of the metal embedded part of the present invention. Detailed Embodiments

[0014] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0015] Embodiment: As Figure 1-2 shown, this embodiment proposes a forming method for an Ω-shaped thin-walled cavity composite material and a metal embedded part, including the following steps: S10. Material preparation: Prepare a composite material, a metal embedded part, and a film adhered around the metal embedded part; S20. Film adhesion: Open grooves on the surface of the metal embedded part and closely adhere the film in the grooves; S30. Laying: Apply a release agent on the surface of the metal tooling. After the release agent dries, lay the composite material on the Ω-shaped metal forming tooling according to the design requirements, and repeat this step. Lay multiple layers on the surface of the metal tooling. During the laying process of the composite material, embed the metal embedded part in step S20 into the Ω shape of two layers of composite materials and fix it through the film; S40. Pre-pressing: Package the metal embedded part completed in step S30 with auxiliary materials such as a separator film, a breather felt, and a vacuum bag, and perform vacuum pre-pressing; S50. Hot compaction: After step S40 is completed, lay 1 to 3 more layers of composite materials on the Ω-shaped composite material in step S30. The laying position is adapted to the metal embedded part, and package it again with auxiliary materials such as a separator film, a breather felt, and a vacuum bag, and send it into an autoclave for hot compaction; S60. Curing: After S50 is completed, continue to lay the composite material, with the laying position adapted to the metal embedded part. After laying, perform vacuum pre-pressing, then encapsulate it, and send it into an autoclave for pressure curing.

[0016] In this embodiment, by designing a groove on the metal embedded part through the above method and fitting a glue film in the groove, it can deform during the cooling process after curing, offsetting the internal stress generated by the mismatch of the thermal expansion coefficients between the metal embedded part and the composite material, solving the problem of deformation caused by excessive internal stress, and greatly improving the dimensional stability of the composite material; Using auxiliary materials such as isolation film, breather felt, and vacuum bag for encapsulation and pre-pressing ensures the close fit between the composite material and the metal embedded part, enhancing the overall structural strength of the formed part; Through the hot compaction and pressure curing steps in the autoclave, a firm bond between the composite material and the metal embedded part is achieved, improving the mechanical properties and environmental resistance of the formed part; This method is applicable to combinations of various composite materials and metal embedded parts, with good versatility and adaptability, and can meet the requirements of different application scenarios.

[0017] Specifically, the composite material is composed of a resin-based composite material and a fiber-reinforced material, and the metal embedded part is made of titanium alloy material.

[0018] In this embodiment, the resin-based composite material combined with the fiber-reinforced material can provide excellent mechanical properties, such as high strength, high modulus, and good fatigue resistance. This combination enables the composite material to exhibit higher stability and reliability when bearing loads.

[0019] Specifically, in S20, the groove is opened at the position where the metal embedded part contacts the composite material.

[0020] In this embodiment, by opening a groove at the position where the metal embedded part contacts the composite material, the contact area between the two can be increased, thereby improving the adhesion and connection strength between the composite material and the metal embedded part; the design of the groove helps to disperse local stress, reduce stress concentration, and thus reduce the risk of material fatigue and fracture caused by stress concentration; fitting a glue film tightly in the groove can ensure the sealing between the glue film and the metal embedded part, preventing air or gas from penetrating into the cavity between the metal embedded layer and the composite material, thus preventing air leakage. The design of the groove helps to form a more stable structure during the curing process because the fitting of the glue film in the groove can provide additional support and fixation, enhancing the stability of the overall structure.

[0021] Specifically, in S20, two groups of glue films are fitted in the groove, and the thickness of the two groups of glue films is greater than the depth of the groove.

[0022] In this embodiment, two layers of adhesive films are used. The adhesive films can effectively prevent air or gas from penetrating into the cavity between the metal embedded layer and the composite material, thereby preventing air leakage.

[0023] Specifically, in S50, the hot pressing conditions are as follows: the hot pressing temperature is 40°C to 60°C, the hot pressing pressure is 0.3 Mpa to 0.6 Mpa, and the hot pressing time is at least 30 min.

[0024] Specifically, in S50, heating starts after the pressure reaches the set pressure. During the hot pressing stage, keep the vacuum pumping at least -60 KPa and pre-press for at least 30 min.

[0025] In this case, the set pressure is 0.3 Mpa to 0.6 Mpa, and the specific value is selected according to the actual situation.

[0026] Specifically, in S50, the gas is pre-exhausted before hot pressing, and the gas between the metal embedded part and the composite material is exhausted again through hot pressing.

[0027] In this embodiment, by exhausting the gas between the metal embedded part and the composite material before and during hot pressing, the formation of bubbles and voids during the curing process can be prevented. Bubbles and voids will reduce the mechanical properties of the composite material and affect the strength and durability of the product.

[0028] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A method for forming an Ω-shaped thin-walled cavity composite material and a metal embedded part, characterized in that: The following steps are involved: S10. Material preparation: Prepare composite materials, metal embedded parts, and adhesive films wrapped around the metal embedded parts; S20, film lamination: A groove is formed on the surface of the metal embedded part, and the adhesive film is tightly fitted in the groove; S30, paving: Apply a release agent on the surface of the metal tooling. After the release agent is dry, lay the composite material on the Ω-shaped metal forming tooling according to the design requirements, and repeat this step. Lay multiple layers on the surface of the metal tooling. During the laying of the composite material, embed the metal embedded parts in S20 into the Ω-shaped of the two layers of composite material and fix them with adhesive film; S40, preload: The metal embedded parts completed in S30 are packaged by using an isolation film, breathable felt, and vacuum bag auxiliary materials, and vacuum-prepressed; S50, hot compaction: When S40 is completed, 1 to 3 layers of composite materials are continuously laid on the Ω-type composite materials in S30, and the laying positions are adapted to the metal embedded parts, and the composite materials are again packaged with isolation film, breathable felt, and vacuum bag auxiliary materials, and then sent to the autoclave for hot compaction; S60, curing: When S50 is completed, continue to lay the composite material, and the laying position is adapted to the metal embedded parts. After the laying is completed, vacuum pre-press, then package, and send it to the autoclave for pressurized curing.

2. The method for forming an Ω-shaped thin-walled cavity composite material and a metal embedded part according to claim 1, characterized in that: The composite material is composed of a resin-based composite material and a fiber-reinforced material, and the metal embedded parts are made of a titanium alloy material.

3. The method for forming an Ω-shaped thin-walled cavity composite material and a metal embedded part according to claim 1, characterized in that: In S20 , a groove is formed at a position where the metal embedded part contacts the composite material.

4. The method for forming an Ω-shaped thin-walled cavity composite material and a metal embedded part according to claim 1, characterized in that: In S20, two sets of adhesive films are attached to the groove, and the thickness of the two sets of adhesive films is greater than the depth of the groove.

5. The method for forming an Ω-shaped thin-walled cavity composite material and a metal embedded part according to claim 1, characterized in that: In S50, the hot pressing conditions are: hot pressing temperature of 40°C to 60°C, hot pressing pressure of 0.3 Mpa to 0.6 Mpa, and hot pressing time of at least 30 minutes.

6. The method for forming an Ω-shaped thin-walled cavity composite material and a metal embedded part according to claim 5, characterized in that: In S50, heating is started when the pressure reaches the set pressure, and the vacuum is maintained at at least -60 KPa during the hot pressing stage, and the pre-pressing is at least 30 minutes.

7. The method for forming an Ω-shaped thin-walled cavity composite material and a metal embedded part according to claim 1, characterized in that: In S50 , the gas is exhausted before hot compaction, and the gas between the metal embedded part and the composite material is exhausted again by hot compaction.

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