Forming preparation method of light high-overload-resistant ablation-resistant edging structure

Abstract

The invention relates to a forming preparation method of a light high-overload-resistant ablation-resistant edging structure, which is characterized in that the edging structure comprises four parts, namely a front edge (1), a strain layer (2), a heat-proof layer (3) and a metal framework (4), wherein the metal framework (4) is located in the middle, the heat-proof layer (3) wraps the metal framework (4) in the middle, the front edge (1) is located at one end of the heat-proof layer (3) and half wraps the heat-proof layer (3), and a layer of adhesive is coated between the contact surfaces of the front edge (1) and the heat-proof layer (3) to form the strain layer (2); the strain layer (2) plays a role in heat protection and sealing; according to the invention, the fiber preform obtained by three-dimensionally weaving the fibers is used as the reinforcement of the heat-proof layer, so that the strength and rigidity of the material of the heat-proof layer under the special-shaped structural design are ensured, and the heat-proof layer still keeps higher mechanical bearing performance in a high-speed pneumatic shearing environment.

Description

Technical Field

[0001] The present invention relates to a method for forming and preparing a lightweight high-overload-resistant and ablation-resistant edge strip structure, in particular to a method for forming and preparing a lightweight high-overload-resistant and ablation-resistant structure-bearing integrated edge strip structure. Background Art

[0002] The main functions of the edge strip structure are thermal protection and load-bearing. During flight, the edge strip structure plays the role of balancing the flight attitude and increasing the lift of the projectile. In order to reduce the mutual interference of shock waves during high Mach number flight, the leading edge product structure is designed to be an acute angle. During flight, the leading edge surface is subjected to temperatures exceeding 1000°C. In this case, the problem of product force and thermal balance is difficult to solve, and deformation and distortion are prone to occur during the preparation process. The application environment of the product requires that the material has the characteristics of high ablation resistance, low thermal conductivity, high strength and high overload resistance. The Chinese patent (CN 113580711) discloses an ablation-resistant lightweight load-bearing cover plate and its preparation method. The cover plate adopts a three-layer structure, the innermost layer is a high-toughness structural load-bearing layer, and the outermost layer is a thermal protection and ablation-resistant layer. The thermal protection and ablation-resistant layer and the high-toughness structural bearing layer are bonded with high-temperature resistant silicone rubber, meeting the requirements for lightweight, high-strength, ablation-resistant load-bearing properties. However, since the design uses a bonding between the bearing layer and the ablation layer, both of which are composite materials, the problem of thermal expansion mismatch between metal and composite materials at high temperatures is not mentioned. The thermal expansion coefficients of composite materials are smaller than those of metal and composite materials. Moreover, due to their small size and relatively simple structure, they cannot meet the thermal load-bearing requirements of heterogeneous structures such as edge strips. A Chinese patent (CN 112480789) discloses a high-strength, erosion-resistant, and ablation-resistant thermal protective coating material and its preparation method. The components include a film-forming material, a curing agent, and a functional filler. The film-forming material, curing agent, and functional filler are mixed with an organic solvent and stirred to obtain a thermal protective coating. The thermal protective coating is sprayed onto the substrate surface using an air spray process. After curing, a high-strength, erosion-resistant, and ablation-resistant thermal protective coating is obtained. The coating has good thermal insulation properties, low ablation rate, light weight, and high strength, meeting the requirements of lightweight integrated thermal protection materials. However, due to its high thermal conductivity and linear ablation rate, and the overall strength of the coating is lower than that of fiber-reinforced materials, it cannot meet the heat protection requirements of hypersonic aircraft. Summary of the Invention

[0003] The purpose of the present invention is to provide a molding and preparation method for a lightweight, high-overload-resistant, ablation-resistant edge strip structure, and to design a low-density, high-overload-resistant, erosion-resistant, long-lasting thermal insulation edge strip structural component material and net size integrated molding process under the constraints of a heterogeneous structure to meet the requirements of the new generation of hypersonic aircraft for excellent high-temperature oxidation resistance, ablation resistance, thermal insulation performance, high mechanical strength and good thermal matching.

[0004] The technical solutions of the present invention are as follows:

[0005] A method for forming and preparing a lightweight, high-overload-resistant, ablation-resistant edge strip structure, characterized in that the edge strip structure comprises a leading edge 1, a strain layer 2, a heat-resistant layer 3, and a metal frame 4. The metal frame 4 is located in the middle, and the heat-resistant layer 3 wraps around the metal frame 4. The leading edge 1 is at one end of the heat-resistant layer 3 and half-wraps the heat-resistant layer 3. A layer of adhesive is applied between the contact surface of the leading edge 1 and the heat-resistant layer 3 to form the strain layer 2. The strain layer 2 provides heat protection and sealing.

[0006] The specific preparation method is as follows:

[0007] Step 1: Prepare a mold for the assembly of the heat-proof layer 3 and the metal frame 4. The mold for the assembly is designed to be a vacuum closed-mold net-size molding mold.

[0008] Step 2: Prepare a fiber preform of the heat protection layer 3. The fiber preform is designed according to the structural dimensions of the product and is a three-dimensional woven structure of long fibers.

[0009] Step 3: Preparation of a low-density, high-temperature-resistant resin matrix in the heat-proof layer 3: Dissolve the high-temperature-resistant resin in a polar organic solvent at room temperature, stir evenly, add a curing agent and hollow ceramic microspheres, and continue stirring to obtain a low-density, high-overload-resistant, ablation-resistant resin matrix, wherein the mass ratio of the high-temperature-resistant resin, organic solvent, curing agent, and hollow ceramic microspheres is 100:100-150:10-30:10-20; heat and stir the mixed resin to reduce the resin viscosity, and set aside;

[0010] Step 4: Prepare the leading edge 1, which is made of a high-temperature resistant refractory metal material and has an ablation-resistant dimension;

[0011] Step 5: Process the metal frame 4 into shape, place the formed metal frame 4 in a sandblasting machine, and perform sandblasting treatment on the surface of the metal frame at a pressure of 0.1-0.3 MPa;

[0012] Step 6: Wrap the fiber preform obtained in step 2 on the surface of the metal frame 4, and sew the fiber preform and the metal frame 4 together with inorganic fibers to ensure the connection strength between the fiber preform and the metal frame 4 to form an assembly;

[0013] Step 7: Place the assembly obtained in step 5 in the cavity of a vacuum closed mold with a net size, and close the mold tightly; then connect the glue injection device, inject the low-density high-temperature resistant resin matrix obtained in step 3 into the glue injection device, and then inject the glue into the mold cavity through the glue injection device to fully infiltrate the assembly in the mold cavity;

[0014] Step 8: heating and co-curing the glue-injected assembly to complete the cross-linking reaction of the low-density, high-temperature-resistant resin;

[0015] Step 9: demoulding the cured product at room temperature and pressure to obtain a glue-injected assembly;

[0016] Step 10. Connect the leading edge 1 to the glue-injected assembly so that the leading edge 1 is half-wrapped at one end of the glue-injected assembly. Rivet holes are punched on the mounting surface. Before installation, add adhesive used to form the strain layer 2 between the leading edge 1 and the glue-injected assembly in contact with the inner surface. The adhesive of the strain layer 2 is evenly distributed between the leading edge 1 and the glue-injected assembly, and then riveting is performed. After riveting, the adhesive used to form the strain layer 2 between the edge 1 and the glue-injected assembly will bond and fix the edge 1 and the glue-injected assembly to form a strain layer 2, which plays the role of bonding and fixing and gap heat protection. The manufacturing process of the present invention is completed.

[0017] The material of the leading edge 1 is one of high-temperature alloy, tungsten-nickel-iron, niobium-tungsten alloy, titanium alloy and titanium-based composite material, and is directly formed by 3D printing.

[0018] The fiber preform in the heat protection layer 3 is made of one or a combination of glass fiber, high silica fiber, quartz fiber, basalt fiber, silicon carbide fiber, carbon fiber, alumina fiber, mullite fiber, silicon nitride fiber, aramid fiber, PBO fiber or polyimide fiber.

[0019] The fiber preform used in the heat protection layer 3 is a three-dimensional woven preform, and the weaving method is one or a combination of shallow cross weaving, three-dimensional five-way weaving, contoured fiber needle felt or suture weaving.

[0020] The high temperature resistant resin of the heat protection layer 3 is one or a combination of barium phenolic, boron phenolic, magnesium phenolic, molybdenum phenolic, modified epoxy resin, silicone resin, ceramic precursor, polycarbosilane and polynitrogen silane. The temperature resistance grade and anti-oxidation and ablation performance are determined according to the thermal environment of the edge strip structural parts.

[0021] The polar organic solvent in the heat-proof layer 3 is one or a combination of methanol, ethanol, n-butanol or isobutanol.

[0022] The curing agent in the heat-proof layer is one or a combination of hexamethylenetetramine, ethylenediamine, p-phenylenediamine and m-phenylenediamine.

[0023] The strain layer 2 is one or a combination of silicone rubber adhesive, polysilazane adhesive, phenolic adhesive, silicate adhesive, phosphate adhesive or organic-inorganic hybrid adhesive; the thickness of the strain layer is 0.1-0.5 mm.

[0024] The heat protection layer 3 and the metal frame 4 are fixed to form an assembly by perforating and sewing double strands of 195tex quartz fiber thread wrapped around the fiber preform reinforcement material on both sides, so as to avoid the fiber preform displacement during the mold closing process and the problem of fiber stretching and tearing.

[0025] The metal skeleton 4 is a lattice structure with a porosity of no more than 20%, a maximum pore size of no more than 3 mm, and a minimum pore size of no less than 0.5 mm. The unit cell of the lattice structure is any one or more of the Bravais lattice structures.

[0026] Features and advantages of the present invention:

[0027] 1. The present invention uses polar organic solvents and hollow ceramic microspheres to modify high-temperature resistant resins to obtain a low-density, high-overload, and ablation-resistant resin system for the injection process, ensuring the material's long-term, high-efficiency thermal insulation performance and resistance to aerodynamic shearing.

[0028] 2. The present invention uses the fiber preform obtained by three-dimensional fiber weaving as the reinforcement of the heat-proof layer, which ensures the strength and rigidity of the heat-proof layer material under the special-shaped structure design, so that the heat-proof layer can still maintain strong mechanical bearing performance under high-speed aerodynamic shear environment.

[0029] 3. The present invention adopts a suturing and fixing method to fix the fiber preform and the metal skeleton, so that the product can be formed in one piece, ensuring the connection strength and thermal matching between the fiber preform and the metal skeleton.

[0030] 4. The present invention designs a vacuum closed-mold net-size molding mold, and the product is molded to near-net-size, which reduces surface fiber damage of thin-walled composite materials, improves production efficiency, and maximizes the material's ablation resistance and heat insulation performance.

[0031] 5. The present invention adds a strain layer to the inner contact surface of the leading edge and the main body assembly to match the mismatch in thermal expansion coefficient between the leading edge and the heat-resistant layer, reducing thermal stress and achieving thermal sealing of the gap. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 , is a schematic diagram of the appearance of the edge strip structural member of the present invention.

[0033] Figure 2 , is a schematic cross-sectional view of the edge strip structural member of the present invention.

[0034] Figure 3 , is a process flow chart for molding the low-density, erosion-resistant, long-lasting thermal insulation edge strip body assembly. DETAILED DESCRIPTION

[0035] A method for forming and preparing a lightweight, high-overload-resistant, ablation-resistant edge strip structure, characterized by:

[0036] Designed for high-Mach, high-heat-flux environments, the strake is composed of four components: a leading edge, a strain layer, a heat shield, and a metal frame. The leading edge is made of a high-temperature, refractory metal material to resist ablation. The strain layer, made of adhesive, fills the gap between the leading edge and the heat shield, providing heat protection and sealing. The heat shield is a fiber preform reinforced layer wrapped around the metal frame, impregnated with a high-temperature resin and co-cured through the RTM process to form the strake body assembly. The leading edge and body assembly are connected by riveting and bonding the strain layer, forming a leading edge-strain layer-body assembly (a sandwich structure of heat shield and metal frame). Finally, assembly forms the strake assembly. The leading edge, constrained by size, is sandwiched between four layers of material, addressing the challenges of lightweight, thermally balanced, ablation-resistant product characteristics, and thermally compatible process characteristics within product size constraints. The dimensional chain of the leading edge sandwich structure allocated to each layer of different materials under dimensional constraints is very weak, only 1-2mm. The appropriate and precise connection method determines the process stability of the product.

[0037] (1) Prepare the main body assembly, and the mold is designed to be a vacuum closed mold net size molding mold.

[0038] (2) The fiber preform in the heat protection layer is designed according to the structural dimensions of the product, and the fiber preform is a three-dimensional woven structure of long fibers.

[0039] (3) Preparation of the resin matrix in the heat-proof layer: dissolving the high-temperature resistant resin in a polar organic solvent at room temperature, stirring evenly, adding a curing agent and hollow ceramic microspheres, and continuing to stir to obtain a low-density, high-overload, and ablation-resistant resin matrix, wherein the mass ratio of the high-temperature resistant resin, solvent, curing agent, and hollow ceramic microspheres is 100:100-150:10-30:10-20;

[0040] (4) Wrapping the fiber preform obtained in step (2) on the surface of the skeleton, sewing the fiber preform and the skeleton with inorganic fibers to ensure the connection strength between the fiber preform and the skeleton, and forming an assembly.

[0041] (5) The main body assembly obtained in step (4) is placed in the cavity of a vacuum closed mold with a net size, and the mold is closed and fastened, and then connected to the injection molding equipment.

[0042] (6) The mixed resin is heated and stirred to reduce the resin viscosity, and the low-density, high-temperature resistant resin matrix prepared in step (3) is injected into the mold cavity to fully infiltrate the main body assembly.

[0043] (7) heating and co-curing the injected assembly to complete the cross-linking reaction of the low-density, high-temperature resistant resin;

[0044] (8) Demolding the product after curing to obtain the main body assembly.

[0045] (9) The leading edge is connected to the main body assembly, and riveting holes are punched on the installation surface. Before installation, a strain layer is added to the inner surface of the leading edge and the side strip structure body, which can play the role of bonding and fixing and gap heat protection. The main body assembly is inserted into the leading edge and riveting is completed.

[0046] The leading edge material is one of high-temperature alloy, tungsten-nickel-iron, niobium-tungsten alloy, titanium alloy, and titanium-based composite material, and can be directly formed by 3D printing.

[0047] The fiber preform in the heat protection layer is made of one or a combination of glass fiber, high silica fiber, quartz fiber, basalt fiber, silicon carbide fiber, carbon fiber, alumina fiber, mullite fiber, silicon nitride fiber, aramid fiber, PBO fiber, and polyimide fiber.

[0048] The fiber preform used in the heat protection layer is a three-dimensional woven preform, and the weaving method is one or a combination of shallow cross weaving, three-dimensional five-way weaving, contoured fiber needle felt, and suture weaving.

[0049] The high-temperature resistant resin in the heat-proof layer is one or a combination of barium phenolic, boron phenolic, magnesium phenolic, molybdenum phenolic, modified epoxy resin, silicone resin, ceramic precursor, polycarbosilane, and polynitrogen silane. The temperature resistance grade and anti-oxidation and ablation performance are determined according to the thermal environment of the edge strip structural parts.

[0050] The polar organic solvent in the heat-proof layer is one or a combination of methanol, ethanol, n-butanol and isobutanol.

[0051] The curing agent in the heat-proof layer is one or a combination of hexamethylenetetramine, ethylenediamine, p-phenylenediamine and m-phenylenediamine.

[0052] The strain layer is one or a combination of silicone rubber adhesive, polysilazane adhesive, phenolic adhesive, silicate adhesive, phosphate adhesive, and organic-inorganic hybrid adhesive. The thickness of the strain layer is 0.1-0.5 mm.

[0053] The heat-proof layer and the metal frame are fixed to form an assembly by means of double-strand perforated stitching of 195tex quartz fiber lines wrapped around the fiber preform reinforcement material on both sides, so as to avoid the displacement of the fiber preform during the mold closing process and the occurrence of fiber stretching and tearing.

[0054] The metal skeleton is a lattice structure with a porosity of no more than 20%, a maximum pore size of no more than 3 mm, and a minimum pore size of no less than 0.5 mm. The unit cell of the lattice structure is any one or more Bravais lattice structures.

[0055] The lightweight, high-overload-resistant, ablation-resistant, integrated composite material edge strip structural component body is manufactured using a net size molding process. The overall dimensions of the product after demoulding are the final product dimensions, and no subsequent machining process is required.

[0056] Example:

[0057] The present invention can be better understood according to the following examples. However, the content described in this embodiment is only used to illustrate the present invention, and should not and will not limit the present invention described in the claims.

[0058] (1) Prepare the main body assembly, and the mold is designed to be a vacuum closed mold net size molding mold.

[0059] (2) Preparation of a low-density, high-temperature-resistant resin matrix: Dissolve an organosilicon phenolic resin in n-butanol at room temperature, stir evenly, add ethylenediamine and hollow ceramic microspheres, and continue stirring to obtain a low-density, ablation-resistant resin matrix, wherein the mass ratio of the organosilicon phenolic resin, n-butanol, ethylenediamine, and hollow ceramic microspheres is 100:150:16:10;

[0060] (3) Place the metal frame in a sandblasting machine and perform sandblasting on the surface of the metal frame at a pressure of 0.1-0.3 MPa;

[0061] (4) Wrapping the fiber preform obtained in step (2) on the surface of the skeleton, sewing the fiber preform and the skeleton with quartz fiber to ensure the connection strength between the fiber preform and the skeleton, and forming an assembly;

[0062] (5) At room temperature, a fiber preform woven with quartz fibers in an orthogonal three-way weaving manner is placed in a net-size molding mold cavity. After the mold is closed and tightened, the glue injection equipment is connected. The low-density resin injection viscosity is within the range of 100-200 MPa / s. The low-density high-temperature resistant resin matrix prepared in step (1) is injected into the mold cavity. The maximum injection pressure does not exceed 0.8 MPa, so that it is fully infiltrated with the preform.

[0063] (6) Heat and stir the mixed resin to reduce the resin viscosity, and inject the high temperature resistant resin matrix prepared in step (3) into the mold cavity to fully infiltrate the main body assembly.

[0064] (7) heating and co-curing the injected assembly to complete the cross-linking reaction of the low-density, high-temperature resistant resin;

[0065] (8) Demolding the cured product at room temperature and pressure to obtain a body assembly;

[0066] (9) The front edge is connected to the main body assembly, and riveting holes are drilled on the installation surface. Before installation, a strain layer is added to the inner surface of the front edge and the side strip structure body. The thickness of the strain layer is 0.1-0.2mm. It can also play the role of bonding and heat protection of the gap. After the main body assembly is inserted into the front edge, the riveting is completed.

[0067] Dimensional means no deformation, and anti-ablation dimensional means anti-ablation and no deformation.

Claims

1. A method for forming and preparing a lightweight, high-overload-resistant, ablation-resistant edge strip structure, characterized in that: The edge strip structure comprises four parts: a leading edge (1), a strain layer (2), a heat protection layer (3) and a metal frame (4); wherein the metal frame (4) is located in the middle, the heat protection layer (3) wraps the metal frame (4) in the middle, the leading edge (1) is at one end of the heat protection layer (3) and half wraps the heat protection layer (3), and a layer of adhesive is applied between the contact surface of the leading edge (1) and the heat protection layer (3) to form a strain layer (2); the strain layer (2) plays a role of heat protection and sealing; the specific preparation method is as follows: Step 1: preparing a mold for the assembly of the heat-proof layer (3) and the metal frame (4), wherein the mold for the assembly is designed to be a vacuum closed-mold net-size molding mold; Step 2: preparing a fiber preform of the heat-proof layer (3). The fiber preform is designed according to the structural dimensions of the product and is a three-dimensional woven structure of long fibers. Step 3: Preparation of a low-density, high-temperature-resistant resin matrix in the heat-proof layer (3): Dissolve the high-temperature-resistant resin in a polar organic solvent at room temperature, stir evenly, add a curing agent and hollow ceramic microspheres, and continue stirring to obtain a low-density, high-overload-resistant, ablation-resistant resin matrix, wherein the mass ratio of the high-temperature-resistant resin, the organic solvent, the curing agent, and the hollow ceramic microspheres is 100:100-150:10-30:10-20; heat and stir the mixed resin to reduce the resin viscosity, and set aside; Step 4, preparing the leading edge (1): the leading edge (1) is made of a high temperature resistant refractory metal material, and the high temperature resistant refractory metal material is used to resist ablation; Step 5: Processing the metal skeleton (4) into shape, placing the formed metal skeleton 4 in a sandblasting machine, and performing sandblasting treatment on the surface of the metal skeleton at a pressure of 0.1-0.3 MPa; Step 6: Wrap the fiber preform obtained in step 2 on the surface of the metal frame 4, and sew the fiber preform and the metal frame (4) with inorganic fibers to ensure the connection strength between the fiber preform and the metal frame 4 to form an assembly; Step 7: Place the assembly obtained in step 5 in the cavity of a vacuum closed mold with a net size, and close the mold tightly; then connect the glue injection device, inject the low-density high-temperature resistant resin matrix obtained in step 3 into the glue injection device, and then inject the glue into the mold cavity through the glue injection device to fully infiltrate the assembly in the mold cavity; Step 8: heating and co-curing the glue-injected assembly to complete the cross-linking reaction of the low-density, high-temperature-resistant resin; Step 9: demoulding the cured product at room temperature and pressure to obtain a glue-injected assembly; Step 10, the leading edge (1) is connected to the glue-injected assembly so that the leading edge (1) is half-wrapped at one end of the glue-injected assembly, and a rivet hole is punched on the mounting surface. Before mounting, an adhesive for forming a strain layer (2) is added between the leading edge (1) and the glue-injected assembly where they are connected and contacted with the inner profile. The adhesive for the strain layer (2) is evenly distributed between the leading edge (1) and the glue-injected assembly, and then riveting is performed. After riveting, the adhesive for forming the strain layer (2) between the leading edge (1) and the glue-injected assembly will bond and fix the leading edge (1) and the glue-injected assembly to form a strain layer (2), which plays the role of bonding and fixing and gap heat protection. The manufacturing process of the present invention is completed.

2. The method for forming and preparing a lightweight high overload resistant and ablation resistant edge strip structure according to claim 1, characterized in that: The material of the leading edge (1) is one of high-temperature alloy, tungsten-nickel-iron, niobium-tungsten alloy, titanium alloy and titanium-based composite material, and is directly formed by 3D printing.

3. The method for forming and preparing a lightweight high overload resistant and ablation resistant edge strip structure according to claim 1 or 2, characterized in that: The fiber preform in the heat-proof layer (3) is made of one or a combination of glass fiber, high silica fiber, quartz fiber, basalt fiber, silicon carbide fiber, carbon fiber, alumina fiber, mullite fiber, silicon nitride fiber, aramid fiber, PBO fiber or polyimide fiber.

4. The method for forming and preparing a lightweight high overload resistant and ablation resistant edge strip structure according to claim 1 or 3, characterized in that: The fiber preform used in the heat protection layer (3) is a three-dimensional woven preform, and the weaving method is one or a combination of shallow cross-link weaving, three-dimensional five-way weaving, contoured fiber needle felt or suture weaving.

5. The method for forming and preparing a lightweight high overload resistant and ablation resistant edge strip structure according to claim 1 or 4, characterized in that: The high temperature resistant resin of the heat protection layer (3) is one or a combination of barium phenolic resin, boron phenolic resin, magnesium phenolic resin, molybdenum phenolic resin, modified epoxy resin, silicone resin, ceramic precursor, polycarbosilane and polynitrogen silane, and the temperature resistance grade and anti-oxidation and ablation performance are determined according to the thermal environment of the edge strip structural parts.

6. The method for forming and preparing a lightweight high overload resistant and ablation resistant edge strip structure according to claim 1 or 5, characterized in that: The polar organic solvent in the heat-proof layer (3) is one or a combination of methanol, ethanol, n-butanol or isobutanol.

7. The method for forming and preparing a lightweight high overload resistant and ablation resistant edge strip structure according to claim 1 or 5, characterized in that: The curing agent in the heat-proof layer is one or a combination of hexamethylenetetramine, ethylenediamine, p-phenylenediamine and m-phenylenediamine.

8. The method for forming and preparing a lightweight high overload resistant and ablation resistant edge strip structure according to claim 1 or 5, characterized in that: The strain layer (2) is one or a combination of organic silicone rubber adhesive, polysilazane adhesive, phenolic adhesive, silicate adhesive, phosphate adhesive or organic-inorganic hybrid adhesive; the thickness of the strain layer is 0.1-0.5 mm.

9. The method for forming and preparing a lightweight high overload resistant and ablation resistant edge strip structure according to claim 1 or 5, characterized in that: The heat-proof layer (3) and the metal frame (4) are fixed to form an assembly by means of a double-strand perforated 195tex quartz fiber thread wrapped around the fiber preform reinforcement material on both sides, thereby avoiding the problem of displacement of the fiber preform during the mold closing process and the occurrence of fiber stretching and tearing.

10. The method for forming and preparing a lightweight high overload resistant and ablation resistant edge strip structure according to claim 1 or 5, characterized in that: The metal skeleton (4) is a lattice structure with a porosity of no more than 20%, a maximum pore size of no more than 3 mm, and a minimum pore size of no less than 0.5 mm. The unit cell of the lattice structure is any one or more of the Bravais lattice structures.

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