A method for preparing a complex structure heat protection product embedded with carbon parts

Abstract

The application relates to a preparation method of an embedded carbon part complex structure heat-proof product, which comprises the following steps: adopting a woven fabric as a reinforcing body, adopting a nano-porous hybrid phenolic resin as a matrix, preparing a snap ring rough product, performing surface hardening treatment on the snap ring rough product, and then processing to obtain a net size heat-proof composite snap ring; a rubber release cloth is laid on the surface of a graphite core mold of a forming mold, a carbon part and the snap ring are positioned on the graphite core mold, and an assembly is formed; the assembly is formed into a preform through a needle punching process; the preform is positioned into the forming mold, the resin is allowed to penetrate the preform through a closed mold glue injection mode, a rough product is obtained through a heating and solidification and low-temperature drying mode, and the excess area of the rough product is removed to obtain the embedded carbon part complex structure heat-proof product. Compared with the prior art, the heat-proof part of a complex structure form is decomposed and modularly prepared, and the optimized preparation of a combined heat-proof material product is realized.

Description

Technical Field

[0001] This invention relates to the field of aerospace heat-resistant composite material preparation technology, and in particular to a method for preparing a complex structure heat-resistant product with embedded carbon components. Background Technology

[0002] With the continuous development of aerospace technology, the performance requirements for heat-resistant materials are becoming increasingly stringent. These materials must possess excellent heat insulation and erosion resistance, as well as good high-temperature mechanical properties. Single heat-resistant materials are no longer sufficient to meet the performance demands of spacecraft. The use of composite materials to fabricate heat-resistant components has become a trend. Combining different materials can effectively leverage their strengths and mitigate their weaknesses to meet the thermal protection requirements of spacecraft. Heat-resistant composite materials are already widely used in rockets, missiles, and other spacecraft, and have significant application potential. In the future, with the continuous development and improvement of heat-resistant composite material technology and the maturation of composite material molding processes, heat-resistant composite materials will be applied in a wider range of fields, making a greater contribution to the development of the aerospace industry. Composite heat-resistant materials are materials with excellent performance and broad application prospects. Their emergence has not only improved the performance and application range of spacecraft but also injected new impetus into the development of the aerospace industry. Summary of the Invention

[0003] The purpose of this invention is to provide a method for preparing a complex heat-resistant product with embedded carbon components, thereby achieving optimized preparation of combined heat-resistant materials.

[0004] The objective of this invention can be achieved through the following technical solution: a method for preparing a heat-resistant product with a complex structure and embedded carbon components, comprising the following steps:

[0005] (1) Preparation of retaining ring: Using woven fabric as reinforcement and nanoporous hybrid phenolic resin as matrix, a rough retaining ring is prepared. The rough retaining ring is then subjected to surface hardening treatment and then processed to obtain a heat-resistant composite retaining ring with net dimensions.

[0006] (2) Assembly of retaining ring and carbon parts: A release cloth with adhesive is laid on the surface of the graphite core mold of the molding die, and the carbon parts and retaining ring are positioned on the graphite core mold to assemble them into an assembly.

[0007] (3) Preparation of lightweight heat-resistant prefabricated structure: The assembly is formed into a prefabricated structure by needle punching process;

[0008] (4) Product molding: Position the preform into the molding mold, use closed mold injection to allow the resin to penetrate the preform, cure and dry to obtain a rough finished product, remove the excess area of ​​the rough finished product to obtain the heat-resistant product with the embedded carbon component complex structure.

[0009] Preferably, the woven fabric is a 2.5D or 3D carbon fiber woven fabric.

[0010] More preferably, the 2.5D carbon fiber woven fabric specifically refers to a woven fabric made by weaving carbon fibers in a 2.5D manner.

[0011] More preferably, the 3D carbon fiber woven fabric specifically refers to a woven fabric made by weaving carbon fibers in a 3D machine.

[0012] Preferably, the woven fabric is an orthogonal triaxial carbon fiber preform.

[0013] Preferably, the material used for the surface hardening treatment in step (1) is one or a combination of two or more of silicone oil, silicone resin and polysilazane resin.

[0014] Preferably, the graphite core mold in step (2) is an assembled core mold, with the upper part of the core mold and the lower part of the core mold connected by graphite bolts and sealed with O-rings.

[0015] Preferably, in step (2), the carbon component and the retaining ring are bonded together by spot bonding with an organosilicon adhesive.

[0016] Preferably, the positioning process in step (2) uses laser beams for correction.

[0017] Preferably, the carbon component is a ring-shaped component.

[0018] More preferably, the carbon component is a ring-shaped component made of carbon ceramic material.

[0019] Preferably, in step (3), the assembly is preformed using a quasi-three-dimensional needle punching process, and the density of the preform is 0.45 g / cm³. 3 -0.65g / cm 3 The precast structure uses carbon fiber cloth with a surface density of 150 g / cm³. 3 -400 g / cm 3 The carbon fiber mesh tread density is 60 g / cm³. 3 -85 g / cm 3 .

[0020] More preferably, the preform structure formed by the quasi-three-dimensional needle punching process is a composite of an alternating layer of carbon fiber cloth and a layer of carbon fiber mesh.

[0021] More preferably, during the needle punching process, 5-10 g / m² of material is sprayed onto each layer of the mesh. 2 Resin diluent.

[0022] More preferably, the resin in the resin diluent is one of the PF series of nanoporous hybrid phenolic resins.

[0023] More preferably, the solvent in the resin diluent is an alcohol.

[0024] More preferably, the resin in the resin diluent has a resin mass fraction of 5-10 wt%.

[0025] Preferably, in step (3), the needle density of the preform is 20-60 needles / cm. 2 Local areas are reinforced using suturing techniques, with a suture spacing density between 5mm and 20mm.

[0026] Preferably, in step (4), the resin is one of the PF series of nanoporous hybrid phenolic resins.

[0027] Preferably, in step (4), the injection rate of the closed mold injection is 200g / min-350g / min, and the injection pressure is 0-0.6MPa.

[0028] Preferably, in step (4), the mold is heated to 60-70°C to depressurize the interior of the mold;

[0029] Preferably, in step (4), the different parts of the forming mold are made of different materials, with the core mold being made of graphite and the other parts being made of P20 mold steel.

[0030] A heat-resistant product with a complex structure and embedded carbon components is prepared by the above-mentioned method.

[0031] Compared with the prior art, the present invention has the following beneficial effects:

[0032] 1. This invention decomposes complex heat-resistant components and prepares them in a modular fashion, thus achieving optimized preparation of combined heat-resistant material products;

[0033] 2. Traditional composite material molding dies are mostly metal combination dies. This invention takes into account the thermal matching of various materials and selects different materials for different parts of the mold to achieve optimized product preparation.

[0034] 3. The modular manufacturing scheme of this invention not only achieves precise positioning of carbon parts, but also improves the molding efficiency of the product;

[0035] 4. This invention optimizes the original complex structure of heat-resistant products into a composite carbon-carbon structure by rationally selecting materials and optimizing the preparation scheme, which simplifies the structure and reduces assembly.

[0036] 5. This invention introduces materials such as silicone oil, silicone resin and polysilazane resin to treat the surface of the retaining ring, which not only improves the hardness of the inner surface of the product, but also ensures the ceramicization of the product surface at high temperature, effectively increasing the heat-resistant product's inner resistance to ablation and erosion.

[0037] 6. This invention effectively leverages the strengths and avoids the weaknesses of heat-resistant products by changing the fiber weaving structure in different areas, thereby reducing product weight while significantly improving performance;

[0038] 7. This invention provides an effective heat protection and insulation solution, which solves the problems of heat protection, heat insulation, erosion resistance and mechanical performance requirements of different parts of the same component in spacecraft, and realizes the preparation of a heat protection product with a complex structure of embedded carbon components;

[0039] 8. The method provided by this invention can expand the product development ideas of designers and manufacturers of heat-resistant products and promote the development of heat-resistant product manufacturing technology. Attached Figure Description

[0040] Figure 1 This is a schematic diagram of the graphite core mold of a heat-resistant product molding die with an embedded carbon component.

[0041] Figure 2 This is a perspective view of the graphite core mold of a heat-resistant product molding die with a complex structure containing embedded carbon parts, according to the present invention.

[0042] Figure 3 This is a cross-sectional view of a prefabricated body according to the present invention.

[0043] Figure 4 This is a schematic diagram of the structure of a complex heat-resistant product with embedded carbon components according to the present invention.

[0044] Figure 5 This is a cross-sectional view of a complex structure heat-resistant product with embedded carbon components according to the present invention.

[0045] Figure 6 This is a schematic diagram of the structure of a molding die for a heat-resistant product with a complex structure and embedded carbon components according to the present invention.

[0046] Wherein: 1-Upper part of core mold, 2-Lower part of core mold, 3-Positioning boss, 4-Annular sealing ring, 5-Locking bolt, 6-Lightweight heat-insulating layer, 7-First retaining ring, 8-Carbon part, 9-Second retaining ring. Detailed Implementation

[0047] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. These embodiments are based on the technical solution of the present invention and provide detailed implementation methods and specific operating procedures. However, the scope of protection of the present invention is not limited to the following embodiments.

[0048] The fibers, resins, adhesives, and diluents in the examples can be appropriately selected according to the actual situation, and used as raw materials for the preparation method of a heat-resistant product with a complex structure of embedded carbon components.

[0049] A method for preparing a heat-resistant product with a complex structure and embedded carbon components includes the following steps:

[0050] Step 1, Snap Ring Preparation: Using woven fabric as reinforcement and nanoporous hybrid phenolic resin as matrix, heat-resistant composite snap rings and rough snap ring products are prepared. The rough snap ring products are subjected to surface hardening treatment, and then the rough snap ring products are processed with high precision to obtain heat-resistant composite snap rings with net dimensions.

[0051] Step 2, Assembly of retaining ring and carbon parts: A layer of adhesive release cloth is laid on the surface of the graphite core mold of the molding die, and the carbon parts and composite material retaining ring are positioned on the graphite core mold to assemble the assembly.

[0052] Step 3: Preparation of lightweight heat-resistant prefabricated structure: The assembly is transported to the prefabricated structure preparation workshop and the prefabricated structure is formed using a quasi-three-dimensional needle punching process.

[0053] Step 4, Product Molding: Position the preform into the molding mold, use closed-mold injection to allow the resin to fully impregnate the preform, use heating curing and low-temperature drying to obtain a rough finished product, and use machining to remove the excess area of ​​the product to obtain a heat-resistant product with a complex structure of embedded carbon parts.

[0054] The following detailed description is based on specific embodiments.

[0055] Example 1

[0056] A method for preparing a heat-resistant product with a complex structure and embedded carbon components includes the following steps:

[0057] Step 1: Preparation of clasp

[0058] The orthogonal triaxial carbon fiber preforms of the retaining rings were placed into retaining ring molding molds. Nanoporous hybrid phenolic resin PF-55 was injected into the molds using a pressure injection method, and the gas in the molds was expelled using a pressure degassing method, with the degassing pressure controlled below 6 bar. The molds were then placed in a heating device to allow the resin to cure at 100℃ for 36 hours. After the resin had cured, the rough retaining rings were placed on a drying fixture for drying at 50℃ for 6 hours, followed by drying at 100℃ for 24 hours.

[0059] The polysilazane resin was diluted to a concentration of 70 wt% using an alkane-based diluent. The rough clasp was placed in the polysilazane resin dilution solution, and the dilution solution was impregnated onto the surface of the rough clasp using a vacuum impregnation method. The vacuum degree of vacuum impregnation needed to be above 950 mbar, and the impregnation was performed 6 times, with each impregnation lasting 20 minutes. After impregnation, the clasp was placed in a heating device and heated to 90℃ for 8 hours to allow the surface impregnation layer to solidify. The rough clasp was then sent to the processing workshop for processing. The rough clasp was positioned, and then the first clasp 7 and the second clasp 9 were obtained using a high-precision five-axis machining center. The dimensions of the clasp were then checked and prepared for use.

[0060] Step 2: Assemble the retaining ring and carbon component

[0061] like Figures 1-2 As shown, adhesive release cloth is laid on the surfaces of the upper part 1 and the lower part 2 of the core mold. The silicone adhesive is dotted on the mating surface of the retaining rings. The first retaining ring 7 and the second retaining ring 9 are respectively positioned on the carbon part 8 to obtain a pre-assembled body. The pre-assembled body is positioned on the lower part 2 of the core mold. An annular sealing ring 4 is placed in the sealing groove of the lower part 2 of the core mold. The upper part 1 of the core mold is positioned on the lower part 2 of the core mold using the positioning boss 3. The upper part 1 of the core mold and the lower part 2 of the core mold are locked together using locking bolts 5. Assembly fixtures are used for limiting the position, and the silicone adhesive is allowed to cure.

[0062] Step 3: Preparation of lightweight heat-resistant prefabricated structure

[0063] After the silicone adhesive has fully cured, the assembly of the core mold, retaining ring, and carbon component is transported to the preform workshop for preform preparation (e.g., Figure 3 The required needle spacing for prefabricated bodies is 25 needles / cm. 2 The areal density of needle-punched carbon fiber cloth is 200 g / cm³. 2 The carbon fiber mesh tread density is 60 g / cm³. 2 During the preform preparation process, each layer of the mesh needs to be sprayed with a 5-10 wt% concentration of nanoporous hybrid phenolic resin PF-45, with a spraying basis weight of 5-10 g / m². 2 This ensures sufficient rigidity of the precast structure. The final density of the precast structure is 0.45 g / cm³. 3 The inner 8-10mm of the assembly area on the upper and lower end faces of the lightweight heat-resistant structure needs to be stitched together, with a stitch spacing of 5mm*5mm.

[0064] Step 4: Molding of lightweight heat-insulating layer

[0065] Position the lower part 2 of the core mold on the forming mold (e.g.) Figure 6The lower mold is assembled into various mold sections. The preform is placed in a sealed mold cavity. The mold is then transferred to a heating device and heated to 50°C. PF-55 resin is injected into the mold using vacuum negative pressure and screw pressure. The injection rate is required to be 300g / min. When resin overflows from the mold outlet, the gas inside the mold is expelled using a gradient pressurization method. The maximum degassing pressure should be less than 5 bar. When the resin inside the mold completely impregnates the preform and all air bubbles are expelled, the injection is stopped.

[0066] The heating equipment temperature is raised to 90℃. When the mold temperature reaches 60℃, the discharge ball valve at the lower end of the molding mold is opened to discharge pressure from the mold. The discharge is performed four times, with a discharge time of 3 seconds. The resin curing time is 36 hours. After the mold cools to room temperature, the side blocks of the molding mold are removed, allowing the rough product to dry along with the core mold. The initial drying temperature is 50℃, and the drying time is 10 hours. The temperature is then raised to 90℃, and the drying time is 27 hours. The dried lightweight heat-insulating layer 6 is transferred to the processing workshop along with the core mold. The end face of the lightweight heat-insulating layer is machined using a machining method. Specifically, rough machining is first performed using milling, and the final 0.5mm allowance is machined using grinding, ultimately obtaining a complex structure heat-insulating product with embedded carbon components (such as...). Figures 4-5 ).

[0067] In this embodiment, the material properties of the retaining ring are as follows: tensile strength: 375 MPa, compressive strength: 300 MPa, flexural strength: 300 MPa, shear strength: 35 MPa, thermal conductivity: 0.25 W / (m·K), specific heat capacity: 1.1 J / (g·K).

[0068] Lightweight heat-insulating layer material properties: tensile strength 165MPa, compressive strength 200MPa, flexural strength 160MPa, shear strength 10.9MPa, thermal conductivity 0.115W / (m·K), specific heat capacity 1.09J / (g·K).

[0069] The product obtained by this invention can meet the requirements of spacecraft for heat protection, heat insulation, erosion resistance and mechanical properties of different parts of the same component, and can be applied to integrated nozzles of spacecraft engines, etc.

[0070] Example 2

[0071] A method for preparing a heat-resistant product with a complex structure and embedded carbon components includes the following steps:

[0072] Step 1: Preparation of clasp

[0073] The orthogonal triaxial carbon fiber preforms of the retaining rings were placed into retaining ring molding molds. Nanoporous hybrid phenolic resin PF-55 was injected into the molds using a pressure injection method, and the gas in the molds was expelled using a pressure degassing method, with the degassing pressure controlled below 6 bar. The molds were then placed in a heating device to allow the resin to cure at 100℃ for 36 hours. After the resin had cured, the rough retaining rings were placed on a drying fixture for drying at 50℃ for 6 hours, followed by drying at 100℃ for 24 hours.

[0074] The polysilazane resin was diluted to a concentration of 60 wt% using an alkane-based diluent. The rough clasp was placed in the polysilazane resin dilution, and the dilution was impregnated onto the surface of the rough clasp using a vacuum impregnation method. The vacuum level during impregnation needed to be above 950 mbar, and the impregnation was performed three times, with each impregnation lasting 30 minutes. The impregnated clasp was then placed in a heating device at 80°C for 6 hours to allow the surface impregnation layer to solidify. The rough clasp was then sent to the processing workshop for machining. The rough clasp was positioned, and then machined using a high-precision five-axis machining center to obtain the first clasp 7 and the second clasp 9. The dimensions of the clasps were then checked for future use.

[0075] Step 2: Assemble the retaining ring and carbon component

[0076] Adhesive release cloth is laid on the surfaces of the upper part 1 and the lower part 2 of the core mold. The silicone adhesive is dotted on the mating surface of the retaining rings, and the first retaining ring 7 and the second retaining ring 9 are respectively positioned on the carbon part 8 to obtain a pre-assembled body. The pre-assembled body is positioned on the lower part 2 of the core mold, and an annular sealing ring 4 is placed in the sealing groove of the lower part 2 of the core mold. The upper part 1 of the core mold is positioned on the lower part 2 of the core mold using the positioning boss 3. The upper part 1 of the core mold and the lower part 2 of the core mold are locked together using locking bolts 5. Assembly fixtures are used for limiting the position, and the silicone adhesive is allowed to cure.

[0077] Step 3: Preparation of lightweight heat-resistant prefabricated structure

[0078] After the silicone adhesive has fully cured, the assembly of the core mold, retaining ring, and carbon component is transported to the preform workshop for preform preparation. The required needle spacing for the preform is 25 needles / cm. 2 The areal density of needle-punched carbon fiber cloth is 200 g / cm³. 2 The carbon fiber mesh tread density is 60 g / cm³. 2 During the preform preparation process, each layer of the mesh needs to be sprayed with a 5-10 wt% concentration of nanoporous hybrid phenolic resin PF-45, with a spraying basis weight of 5-10 g / m². 2 This ensures sufficient rigidity of the precast structure. The final density of the precast structure is 0.45 g / cm³. 3The inner 8-10mm of the assembly area on the upper and lower end faces of the lightweight heat-resistant structure needs to be stitched together, with a stitch spacing of 5mm*5mm.

[0079] Step 4: Molding of lightweight heat-insulating layer

[0080] Position the lower part 2 of the core mold on the lower mold of the molding mold, assemble the various parts of the molding mold, place the preform in the sealed mold cavity, transfer the mold to the heating equipment, heat the mold to 60°C, and use vacuum negative pressure and screw pressure to inject PF-55 resin into the mold. The injection rate is required to be 300g / min. When the resin overflows from the mold outlet, use gradient pressure to expel the gas in the mold. The maximum degassing pressure should be less than 5 bar. Stop the injection when the resin in the mold completely wets the preform and the air bubbles in the mold are fully expelled.

[0081] The heating equipment temperature is raised to 90℃. When the mold temperature reaches 60℃, the discharge ball valve at the lower end of the molding mold is opened to discharge pressure from the mold. The discharge is performed 5 times, with a discharge time of 2 seconds. The resin curing time is 36 hours. After the mold cools to room temperature, the side block of the molding mold is removed, allowing the rough product to dry along with the core mold. The initial drying temperature is 50℃, and the drying time is 12 hours. The temperature is then raised to 90℃, and the drying time is 30 hours. The dried lightweight heat-insulating layer 6 is transferred to the processing workshop along with the core mold. The end face of the lightweight heat-insulating layer is machined using a machining method. Specifically, rough machining is performed first using milling, and the final 0.5mm allowance is machined using grinding, ultimately obtaining a heat-insulating product with a complex structure of embedded carbon components.

[0082] Example 3

[0083] A method for preparing a heat-resistant product with a complex structure and embedded carbon components includes the following steps:

[0084] Step 1: Preparation of clasp

[0085] The orthogonal triaxial carbon fiber preforms of the retaining rings were placed into retaining ring molding molds. Nanoporous hybrid phenolic resin PF-55 was injected into the molds using a pressure injection method, and the gas in the molds was expelled using a pressure degassing method, with the degassing pressure controlled below 6 bar. The molds were then placed in a heating device to allow the resin to cure at 100℃ for 36 hours. After the resin had cured, the rough retaining rings were placed on a drying fixture for drying at 50℃ for 6 hours, followed by drying at 100℃ for 24 hours.

[0086] The polysilazane resin was diluted to 80 wt% using an alkane-based diluent. The rough clasp was placed in the polysilazane resin dilution, and the dilution was impregnated onto the surface of the rough clasp using a vacuum impregnation method. The vacuum level during impregnation needed to be above 950 mbar, and the impregnation was repeated 8 times, with each impregnation lasting 15 minutes. The impregnated clasp was then placed in a heating device at 85°C for 7 hours to allow the surface impregnation layer to solidify. The rough clasp was then sent to the processing workshop for machining. The rough clasp was positioned, and then machined using a high-precision five-axis machining center to obtain the first clasp 7 and the second clasp 9. The dimensions of the clasps were then checked for future use.

[0087] Step 2: Assemble the retaining ring and carbon component

[0088] Adhesive release cloth is laid on the surfaces of the upper part 1 and the lower part 2 of the core mold. The silicone adhesive is dotted on the mating surface of the retaining rings, and the first retaining ring 7 and the second retaining ring 9 are respectively positioned on the carbon part 8 to obtain a pre-assembled body. The pre-assembled body is positioned on the lower part 2 of the core mold, and an annular sealing ring 4 is placed in the sealing groove of the lower part 2 of the core mold. The upper part 1 of the core mold is positioned on the lower part 2 of the core mold using the positioning boss 3. The upper part 1 of the core mold and the lower part 2 of the core mold are locked together using locking bolts 5. Assembly fixtures are used for limiting the position, and the silicone adhesive is allowed to cure.

[0089] Step 3: Preparation of lightweight heat-resistant prefabricated structure

[0090] After the silicone adhesive has fully cured, the assembly of the core mold, retaining ring, and carbon component is transported to the preform workshop for preform preparation. The required needle spacing for the preform is 25 needles / cm. 2 The areal density of needle-punched carbon fiber cloth is 200 g / cm³. 2 The carbon fiber mesh tread density is 60 g / cm³. 2 During the preform preparation process, each layer of the mesh needs to be sprayed with a 5-10 wt% concentration of nanoporous hybrid phenolic resin PF-45, with a spraying basis weight of 5-10 g / m². 2 This ensures sufficient rigidity of the precast structure. The final density of the precast structure is 0.45 g / cm³. 3 The inner 8-10mm of the assembly area on the upper and lower end faces of the lightweight heat-resistant structure needs to be stitched together, with a stitch spacing of 5mm*5mm.

[0091] Step 4: Molding of lightweight heat-insulating layer

[0092] Position the lower part 2 of the core mold on the lower mold of the molding mold, assemble the various parts of the molding mold, place the preform in the sealed mold cavity, transfer the mold to the heating equipment, heat the mold to 40°C, and use vacuum negative pressure and screw pressure to inject PF-55 resin into the mold. The injection rate is required to be 300g / min. When the resin overflows from the mold outlet, use gradient pressure to expel the gas in the mold. The maximum degassing pressure should be less than 5 bar. Stop the injection when the resin in the mold completely wets the preform and the air bubbles in the mold are fully expelled.

[0093] The heating equipment temperature is raised to 90℃. When the mold temperature reaches 60℃, the discharge ball valve at the lower end of the molding mold is opened to discharge pressure from the mold. The discharge is performed 3 times, with a discharge time of 5 seconds. The resin curing time is 36 hours. After the mold cools to room temperature, the side block of the molding mold is removed, allowing the rough product to dry along with the core mold. The initial drying temperature is 50℃, and the drying time is 8 hours. The temperature is then raised to 90℃, and the drying time is 24 hours. The dried lightweight heat-insulating layer 6 is transferred to the processing workshop along with the core mold. The end face of the lightweight heat-insulating layer is processed by machining. Specifically, rough machining is first performed by milling, and the final 0.5mm allowance is processed by grinding, ultimately obtaining a heat-insulating product with a complex structure of embedded carbon components.

[0094] This invention provides a method for manufacturing a complex heat-resistant product with embedded carbon components. This method decomposes the complex heat-resistant component into modular components, optimizing the manufacturing process through an innovative manufacturing scheme. Machining is used to ensure the dimensional accuracy and positioning of key parts, while surface treatment enhances the product's localized heat-resistant and erosion-resistant capabilities. Furthermore, this invention fully considers the thermal compatibility between the materials of each mold component, designing a multi-material combination mold. The heat-resistant product manufactured using this method exhibits excellent heat insulation performance, effectively improving the product's internal quality and erosion resistance, reducing the difficulty of product manufacturing and assembly processes, and significantly lowering manufacturing costs.

[0095] The above description of the embodiments is provided to enable those skilled in the art to understand and use the invention. It will be apparent to those skilled in the art that various modifications can be made to these embodiments, and the general principles described herein can be applied to other embodiments without inventive effort. Therefore, the present invention is not limited to the above embodiments, and any improvements and modifications made by those skilled in the art based on the disclosure of the present invention without departing from the scope of the invention should be within the protection scope of the present invention.

Claims

1. A method for preparing a heat-resistant product with a complex structure and embedded carbon components, characterized in that, Includes the following steps: (1) Preparation of retaining ring: Using woven fabric as reinforcement and nanoporous hybrid phenolic resin as matrix, a rough retaining ring is prepared. The rough retaining ring is then subjected to surface hardening treatment to obtain a heat-resistant composite retaining ring. (2) Assembly of retaining ring and carbon parts: A release cloth with adhesive is laid on the surface of the graphite core mold of the molding die, and the carbon parts and retaining ring are positioned on the graphite core mold to assemble them into an assembly. (3) Preparation of lightweight heat-resistant prefabricated structure: The assembly is formed into a prefabricated structure by needle punching process; (4) Product molding: Position the preform into the molding mold, use closed mold injection to allow the resin to penetrate the preform, cure and dry to obtain a rough finished product, remove the excess area of ​​the rough finished product to obtain the heat-resistant product with the embedded carbon component complex structure.

2. The method for preparing a complex structure heat-resistant product with embedded carbon components according to claim 1, characterized in that, The woven fabric is a 2.5D or 3D woven fabric.

3. The method for preparing a complex structure heat-resistant product with embedded carbon components according to claim 1, characterized in that, The surface hardening treatment in step (1) uses one or a combination of two or more of the following materials: silicone oil, silicone resin, and polysilazane resin.

4. The method for preparing a complex structure heat-resistant product with embedded carbon components according to claim 1, characterized in that, The graphite core mold mentioned in step (2) is an assembled core mold. The upper part of the core mold and the lower part of the core mold are connected by graphite bolts and sealed with O-rings.

5. The method for preparing a complex structure heat-resistant product with embedded carbon components according to claim 1, characterized in that, In step (2), the carbon component and the retaining ring are spot-bonded using silicone adhesive.

6. The method for preparing a heat-resistant product with a complex structure and embedded carbon components according to claim 1, characterized in that, In step (3), the assembly is preformed using a quasi-three-dimensional needle punching process, and the density of the preform is 0.45 g / cm³. 3 -0.65g / cm 3 The precast structure uses carbon fiber cloth with a surface density of 150 g / cm³. 3 -400 g / cm 3 The carbon fiber mesh tread density is 60 g / cm³. 3 -85 g / cm 3 During the needle punching process, spray 5-10g / m² of material onto each layer of the mesh. 2 Resin diluent.

7. The method for preparing a heat-resistant product with a complex structure and embedded carbon components according to claim 1, characterized in that, In step (3), the needle density of the preform is 20-60 needles / cm. 2 Local areas are reinforced using suturing techniques, with a suture spacing density between 5mm and 20mm.

8. The method for preparing a complex heat-resistant product with embedded carbon components according to claim 1, characterized in that, In step (4), the resin is one of the PF series of nanoporous hybrid phenolic resins; The injection rate of the closed mold injection is 200g / min-350g / min, and the injection pressure is 0-0.6MPa.

9. The method for preparing a complex structure heat-resistant product with embedded carbon components according to claim 1, characterized in that, In step (4), the mold is heated to 60-70℃ to depressurize the inside of the mold; The different parts of the molding die are made of different materials; the core mold is made of graphite, and the other parts are made of P20 mold steel.

10. A heat-resistant product with a complex structure and embedded carbon components, characterized in that, It is prepared by the preparation method described in any one of claims 1 to 9.

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