Refractory alloy copper infiltrated composite and method of making

Abstract

Disclosed are a refractory alloy copper-infiltrated composite material and a preparation method thereof. In the method, elemental powder of a refractory metal is weighed according to a predetermined mass ratio to obtain mixed powder, and the mixed powder is pressed and formed in a cold isostatic pressing machine to obtain a compact; the compact is placed in a spark plasma sintering furnace for sintering to obtain a refractory alloy framework, wherein the temperature is raised to 1800-2200 DEG C under the protection of a hydrogen atmosphere, and the temperature is kept for 25 minutes to form the refractory alloy framework; copper powder is mixed with alcohol, and the mixture is pressed and formed in the cold isostatic pressing machine to obtain a copper compact, which is placed below the refractory alloy framework and then sintered, the temperature is raised to 1250-1350 DEG C under the protection of a hydrogen atmosphere, and the temperature is kept for 25 minutes to obtain the refractory alloy copper-infiltrated composite material.

Description

Technical Field

[0001] This invention relates to the field of refractory alloy technology, and in particular to a refractory alloy copper-infiltrated composite material and its preparation method. Background Technology

[0002] The aerodynamic heat generated during hypersonic vehicle flight can cause the surface temperature of components such as the nose cone and wing leading edge to rise above 2000°C. These components must not only withstand the extreme environment of high-temperature, high-pressure exhaust gases but also possess the ability to resist complex mechanical stresses. These special operating conditions place comprehensive demands on materials, requiring excellent ablation resistance, outstanding high-temperature resistance, and lightweight design. Existing refractory alloy copper-infiltrated composite materials suffer from complex processes and high costs.

[0003] The information disclosed in the background section is only for enhancing the understanding of the background of this invention, and therefore may contain information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0004] This invention proposes a method for preparing copper-infiltrated composite materials from refractory alloys. In the sintering process, this method effectively optimizes the porous structure of the material by precisely controlling the sintering temperature and pressure and scientifically regulating the sintering process parameters. This improvement achieves a significant copper infiltration effect, resulting in a denser and more uniform composite material. This method successfully overcomes the problems of complex processes and high costs in existing refractory alloy copper-infiltrated composite material preparation processes.

[0005] A method for preparing copper-infiltrated refractory alloy composite materials includes, Step 1: Weigh the refractory metal powder according to the predetermined mass ratio and mix them to obtain a mixed powder. Step 2: Press the mixed powder into a compact using a cold isostatic press. Step 3: The pressed billet is placed in a spark plasma sintering furnace to sinter and obtain a refractory alloy skeleton. In the process, under a hydrogen protective atmosphere, the pressed billet is heated to 1800-2200°C and held for 25 minutes to form a refractory alloy skeleton. Step 4: Mix copper powder with alcohol and press it into shape in a cold isostatic press to obtain a copper billet; Step 5: Place the copper block on top of the refractory alloy skeleton and sinter it. Heat the mixture to 1350℃ in a hydrogen atmosphere and hold it for 25 minutes to obtain the refractory alloy copper-infiltrated composite material.

[0006] In the method described, the average particle size of the refractory metal powder is 15–43 μm, and the refractory metal powder includes tungsten powder, molybdenum powder, tantalum powder, niobium powder, and X powder.

[0007] In the method described, weighing refractory metal powder according to a predetermined mass ratio includes weighing and mixing tungsten powder, molybdenum powder, tantalum powder, niobium powder, and X powder in an equiatomic ratio. The X powder is selected from at least one of titanium, zirconium, hafnium, or silicon to adjust the skeleton strength and oxidation resistance.

[0008] In the method described above, in step 1, tungsten powder, molybdenum powder, tantalum powder, niobium powder and X powder are mixed in an equiatomic ratio to form the powder atomized by the rotating motor and then the mixed metal powder is reduced in a hydrogen atmosphere.

[0009] In the method described, in step 2, stearic acid is dissolved in alcohol, mixed powder is added and stirred evenly, dried and then pressed into shape in a cold isostatic press to obtain a porous green body. The obtained porous green body is then sintered without pressure in a sintering furnace to remove stearic acid.

[0010] In the method described, the temperature at which the stearic acid dissolves in alcohol is 40–80°C, the mass percentage of stearic acid in the solution is 1%–3%, the drying temperature is 40–80°C, the drying time is 0.5–4 hours, the pressure used in the pressing process is 200 MPa–650 MPa, and the porous green body is heated to 400°C in a sintering furnace without pressure and held for 10 minutes to remove stearic acid.

[0011] In the method described, in step 3, the heating rate during sintering is 100℃ / min.

[0012] In the method described above, in step 4, the copper content of the refractory alloy copper-infiltrated composite material is 5wt% to 30wt%, and the thermal conductivity and ablation resistance of the refractory alloy copper-infiltrated composite material are controlled by adjusting the copper content.

[0013] A copper-infiltrated refractory alloy composite material, prepared by the method described above.

[0014] An application of the aforementioned refractory alloy copper-infiltrated composite material, wherein the refractory alloy copper-infiltrated composite material is used to manufacture the nose cone of a hypersonic vehicle, the leading edge of a wing, or the nozzle of a rocket engine.

[0015] Compared with the prior art, the present invention has the following advantages: the present invention achieves precise control of porous skeleton structure by optimizing powder particle size, pressing pressure and sintering temperature, adjusting copper content and regulating pore structure to balance strength, thermal conductivity and ablation resistance, and sweating cooling mechanism to meet the requirements of extreme thermal environment of hypersonic aircraft. The single-element powder cold pressing + SPS sintering process is simple and the cost is lower than that of alloy powder preparation. Attached Figure Description

[0016] In the attached diagram: Figure 1 XRD patterns of WMoTaNb / Cu; Figure 2 Schematic diagrams of SEM and EDS of C / C / SiC / WMoTaNb-10%wt.Cu before ablation; Figure 3 A schematic diagram of the ablation rate of WMoTaNb / Cu after 90 s of plasma flame ablation at a heat flux density of 7.6 MW / m2.

[0017] The present invention will be further explained below with reference to the accompanying drawings and embodiments. Detailed Implementation

[0018] To facilitate understanding of the embodiments of the present invention, further explanations and descriptions will be provided below with reference to the accompanying drawings and specific embodiments. The accompanying drawings do not constitute a limitation on the embodiments of the present invention.

[0019] like Figures 1 to 3 As shown, a method for preparing a copper-infiltrated refractory alloy composite material includes, Step 1: Weigh the refractory metal elemental powder according to the predetermined mass ratio and mix them to obtain a mixed powder. The predetermined mass ratio can be configured according to an equimolar ratio, for example, the predetermined mass ratio is used to prepare the powder according to an equimolar ratio. Step 2: Press the mixed powder into a compact using a cold isostatic press. Step 3: The pressed billet is placed in a spark plasma sintering furnace to sinter and obtain a refractory alloy skeleton. In this process, under a hydrogen protective atmosphere, the pressed billet is heated to 1800-2200°C and held for 25 minutes to form a solid solution, thereby forming a refractory alloy skeleton. Step 4: Place the copper block under the refractory alloy skeleton and sinter. Heat to 1350℃ in a hydrogen atmosphere and hold for 25 minutes to obtain the refractory alloy copper-infiltrated composite material. The preferred copper ratio is 5wt% to 30wt%.

[0020] In a preferred embodiment of the method, the average particle size of the refractory metal powder is 15–43 μm, and the refractory metal powder includes tungsten powder, molybdenum powder, tantalum powder, niobium powder, titanium powder, and vanadium powder.

[0021] In a preferred embodiment of the method, weighing refractory metal powder according to a predetermined mass ratio includes weighing and mixing tungsten powder, molybdenum powder, tantalum powder, niobium powder and X powder in an equiatomic ratio, wherein the X powder is selected from at least one of titanium, zirconium, hafnium or silicon to adjust the skeleton strength and oxidation resistance.

[0022] In a preferred embodiment of the method, in step 1, tungsten powder, molybdenum powder, tantalum powder, niobium powder, and X powder are mixed in an equiatomic ratio with the powder atomized by the rotating motor and then reduced in a hydrogen atmosphere.

[0023] In a preferred embodiment of the method, in step 2, stearic acid is dissolved in alcohol, mixed powder is added and stirred evenly, dried and then pressed into shape in a cold isostatic press to obtain a porous green body. The obtained porous green body is then sintered without pressure in a sintering furnace to remove stearic acid.

[0024] In a preferred embodiment of the method, the stearic acid is dissolved in alcohol at a temperature of 40–80°C, the mass percentage of stearic acid in the solution is 1%–3%, the drying temperature is 40–80°C, the drying time is 0.5–4 hours, the pressure used in the pressing process is 200 MPa–650 MPa, and the porous green body is heated to 400°C in a sintering furnace without pressure and held for 10 minutes to remove stearic acid.

[0025] In a preferred embodiment of the method, in step 3, the heating rate during sintering is 100°C / min.

[0026] In a preferred embodiment of the method, in step 4, the copper content of the refractory alloy copper-infiltrated composite material is 5wt% to 30wt%, and the thermal conductivity and ablation resistance of the refractory alloy copper-infiltrated composite material are controlled by adjusting the copper content.

[0027] A copper-infiltrated refractory alloy composite material, prepared by the method described above.

[0028] The refractory alloy copper-infiltrated composite material is used to manufacture the nose cone of hypersonic aircraft, the leading edge of wings, or the nozzle of rocket engines.

[0029] In one embodiment, a certain proportion of refractory metal elemental powders (W, Mo, Ta, Nb, Ti, V, etc.) are ball-milled and mixed; the mixed refractory alloy powder is placed in a cold isostatic press and pressed into shape; the pressed blank is subjected to spark plasma sintering technology to obtain a refractory alloy skeleton; a certain amount of copper block is placed on the refractory alloy skeleton and sintered again to melt and infiltrate the copper into the skeleton, and finally a refractory alloy composite material is obtained.

[0030] In one embodiment, the drying temperature is 60°C and the drying time is 2 hours. In step 3, when the sintering temperature rises to 400°C, the holding time is 10 minutes.

[0031] In one embodiment, the tungsten-copper infiltration sweating mechanism provides the material with significant advantages. Based on a structure of "high-melting-point tungsten framework + low-melting-point copper filler," copper can rapidly absorb large amounts of heat from high-temperature environments through its phase-change endothermic properties, providing significant cooling even at extreme temperatures of thousands of degrees Celsius in rocket engine nozzles. When the copper vaporizes, it forms a copper vapor insulating film, effectively blocking the ingress of external heat. This not only reduces the risk of the tungsten framework being ablated by oxidation but also enhances the material's high-temperature resistance and structural stability. Simultaneously, the internal pressure difference drives the continuous replenishment of liquid copper, ensuring a continuous and stable heat dissipation process. This allows the material to maintain reliable performance even under extreme high-temperature conditions, thus meeting the stringent requirements of aerospace, military, and other fields. Compared to using alloy powders, the preparation process of ball milling and cold isostatic pressing of elemental powder followed by spark plasma sintering is simpler and less costly.

[0032] Example 1: Equimolar mixture of tungsten, molybdenum, tantalum, and niobium powders + 10wt% copper Composition: Equivalent molar mixture of tungsten, molybdenum, tantalum, and niobium powders: 100wt% Copper powder: 10wt% Preparation steps Powder mixing: Tungsten, molybdenum, tantalum and niobium powders with an average particle size of 15μm are mixed in a certain proportion; Pressing green bodies: Stearic acid concentration: 1% (dissolved in alcohol, 60°C); Drying temperature: 60℃, time: 2 hours; Cold isostatic pressure: 200 MPa; Copper powder is dissolved in alcohol and pressed into a blank using a cold isostatic pressing mold; Drying temperature: 60℃, time: 2 hours; Pressureless degreasing and sintering: hold at 400℃ for 10 minutes; High-temperature sintering skeleton: heating rate 100℃ / min, hold at 1800℃ for 25min; Copper infiltration sintering: The pre-pressed copper block is placed under the frame and held at 1350℃ for 25 minutes; Ablation rate at 2500℃: 0.0120 mm / s The composite material is obtained through cooling. It has a high density and is suitable for high-strength, high-density components. It has good ablation resistance but weak sweating cooling capacity; it has a low cost and is suitable for use in basic ablation-resistant structural components.

[0033] Example 2: Equimolar mixture of tungsten, molybdenum, tantalum, and niobium powders + 30wt% copper Composition: Equivalent molar mixture of tungsten, molybdenum, tantalum, and niobium powders: 100wt% Copper powder: 30 wt% Preparation steps Mixed powder: Tungsten, molybdenum, tantalum and niobium powders are mixed in a certain proportion; Pressing green bodies: Stearic acid concentration: 1% (dissolved in alcohol, 60°C); Drying temperature: 60℃, time: 2 hours; Cold isostatic pressure: 650 MPa; Pressing green bodies: Copper powder is dissolved in alcohol and pressed into a blank using a cold isostatic pressing mold; Drying temperature: 60℃, time: 2 hours; Degreasing and sintering: Hold at 400℃ for 10 minutes; Sintering of the skeleton: Heat to 2200℃ and hold for 25 minutes; Copper infiltration sintering: Hold at 1350℃ for 25 minutes; Ablation rate at 2500℃: 0.0140 mm / s The composite material is obtained after cooling. It has a high copper content, good thermal conductivity, and strong sweating and cooling capacity. The material density is reduced, resulting in significant lightweight advantages; however, the strength is relatively lower, making it suitable for scenarios where heat dissipation is the primary concern and strength requirements are not high; it also exhibits good self-cooling capabilities under extreme high temperatures.

[0034] Example 3: Equimolar mixture of tungsten, molybdenum, tantalum, and niobium powders + 20wt% copper 100 wt% of a mixture of tungsten, molybdenum, tantalum, and niobium in equal molar amounts. Copper powder: 20 wt% Preparation steps Mixed powder: Tungsten, molybdenum, tantalum and niobium powders are mixed in a certain proportion; Pressing green bodies: Stearic acid concentration: 2%; Drying temperature: 60℃, time: 2 hours; Pressure: 400 MPa; Copper powder is dissolved in alcohol and pressed into a blank using a cold isostatic pressing mold; Drying temperature: 60℃, time: 2 hours; Degreasing and sintering: Hold at 400℃ for 10 minutes; Sintering of the skeleton: Heat to 2000℃ and hold for 25 minutes; Copper infiltration sintering: Hold at 1350℃ for 25 minutes; Performance testing: Ablation rate at 2500℃: 0.0098 mm / s The composite material is obtained through cooling. It has excellent overall performance, balancing strength, density, and ablation resistance; its evaporation cooling efficiency is moderate, making it suitable for most aerospace structural components; the process is stable and has good repeatability, making it suitable as a standardized production solution.

[0035] Example 4: 80% tungsten powder + 5% molybdenum powder + 5% tantalum powder + 10% copper Tungsten powder: 80 wt% Molybdenum powder: 5 wt% Tantalum powder: 5 wt% Copper powder: 10 wt% Preparation steps Mixing: Mix the various metal powders (average particle size: 30-40 μm); Pressing green bodies: Stearic acid concentration: 2.5%; Drying temperature: 70℃, time: 1 hour; Pressure: 500 MPa; Degreasing and sintering: Hold at 400℃ for 10 minutes; Sintering of the skeleton: Heat to 2100℃ and hold for 25 minutes; Copper infiltration sintering: Hold at 1350℃ for 25 minutes; Performance testing: Ablation rate at 2500℃: 0.13 mm / s The composite material was obtained by cooling. The addition of Mo and Ta significantly improved the oxidation resistance; it exhibited stronger resistance to ablation in high-temperature and oxygen-rich environments; and it maintained good mechanical properties and controllable density.

[0036] Example 5: 75% tungsten powder + 5% molybdenum powder + 5% tantalum powder + 5% niobium powder + 10% copper Tungsten powder: 75 wt% Molybdenum powder: 5 wt% Tantalum powder: 5 wt% Niobium powder: 5 wt% Copper powder: 10 wt% Preparation steps Powder mixing: Five kinds of metal powders (average particle size: 35μm) are mixed; Pressing green bodies: Stearic acid concentration: 2%; Drying temperature: 60℃, time: 2 hours; Pressure: 550 MPa; Degreasing and sintering: Hold at 400℃ for 10 minutes; Sintering of the skeleton: Heat to 2150℃ and hold for 25 minutes; Copper infiltration sintering: Hold at 1350℃ for 25 minutes; Performance testing: Ablation rate at 2500℃: 0.12 mm / s The composite material is obtained through cooling. The multi-element alloy skeleton enhances the overall thermal stability and oxidation resistance; the moderate copper content provides good sweating and cooling properties; and the material density is controlled within a reasonable range, balancing strength and lightweight. It performed excellently in ablation tests under simulated hypersonic flight conditions and was identified as the best technical effect embodiment of the present invention.

[0037] Comparative example: without added Mo / Ta / Nb elements, etc. Tungsten powder: 90 wt% Copper powder: 10 wt% Performance testing: Ablation rate at 2500℃: 0.08 mm / s The preparation steps are the same as in Example 1. Compared with the sample containing Mo / Ta / Nb, more obvious surface ablation occurs in the high-temperature oxidation environment; the oxidation resistance decreases and the service life is shortened; thus, it is shown that the present invention can significantly improve the material performance by introducing alloying elements.

[0038] This method retains the sweating and cooling properties of tungsten-copper infiltrating materials, while Mo and Ta elements enhance the oxidation resistance of the composite material, thus significantly improving its ablation resistance in high-temperature aerobic environments. Furthermore, the strength of the material can be adjusted by modifying the copper content and setting different sintering temperatures. While preserving the ablation resistance of tungsten-copper infiltrating materials, the skeletal structure of the tungsten alloy reduces the density of the composite material, achieving both low density and excellent ablation resistance. The pore structure and pore size of the porous preform can be controlled by adjusting the pressure and holding time of the hydraulic press.

[0039] This invention uses a mixture of refractory metal powders such as tungsten, molybdenum, tantalum, and niobium as the framework material, and mixes various high-melting-point metals (such as W, Mo, Ta, and Nb) in a certain proportion. This improves the thermal stability and high-temperature strength of the framework structure; Mo, Ta, and Nb elements can form a dense oxide layer, significantly enhancing oxidation and ablation resistance; the multi-element alloy framework has superior overall performance compared to a single tungsten framework; and it effectively avoids the problem of rapid oxidation failure of traditional pure tungsten materials in high-temperature aerobic environments. X powders (such as titanium, zirconium, hafnium, or silicon) are introduced to adjust the framework properties. A small amount of X powder is added to the metal powder to optimize the framework structure and properties. This improves wettability and diffusion behavior during sintering; enhances the interfacial bonding force of the porous framework, improving mechanical properties; increases the oxidation resistance of the material by adding active elements; and forms a stable oxide film at high temperatures, delaying the ablation process of the framework. The average particle size of the powder is controlled to be 15–43 μm, limiting the particle size range of the metal powders used. If the particle size is too small, it will easily agglomerate and affect the molding process; if it is too large, it will lead to uneven pore distribution. A moderate particle size is conducive to obtaining a uniform porous structure and improving the efficiency of subsequent copper infiltration. It can ensure the strength of the skeleton while achieving controllable porosity to meet the requirements of sweating and cooling. It can also help the diffusion and bonding between particles during sintering and improve the density of the material.

[0040] Stearic acid, used as a binder, is dissolved in alcohol and then added to the metal powder for mixing. This process acts as a lubricant and binder, improving powder flowability during pressing; facilitating pressing and reducing crack defects; and ensuring easy removal without leaving harmful residues during subsequent sintering. Alcohol, as a solvent, evaporates quickly and does not affect subsequent process steps. The mixed powder is dried at low temperatures (40–80℃, 0.5–4h) to thoroughly remove alcohol and moisture, preventing bubbles or stratification during pressing; controlling the degree of dryness to avoid powder agglomeration; ensuring consistency and repeatability in subsequent pressing and sintering processes; and providing a good physical foundation for subsequent green body forming. The hydraulic press pressure is controlled between 200MPa and 650MPa, and different pressing pressures are used to control the green body density and porosity. Higher pressure results in a denser green body, but reduced porosity hinders subsequent copper infiltration. Moderate pressure yields an ideal pore structure, supporting effective copper infiltration. It allows for control over the microstructure of the porous framework and enables flexible matching of performance requirements across different applications by adjusting the pressure. Pressureless debinding sintering (400℃ for 10 min) involves heating to 400℃ in air to remove the binder. This safely removes stearic acid, preventing carbonization contamination during subsequent high-temperature sintering. The temperature should not be too high to avoid premature metal reaction or oxidation. This provides a clean matrix for subsequent framework sintering and ensures sintering quality and material structural integrity. High-temperature sintering under hydrogen protection (1800–2200℃, heating rate 100℃ / min).

[0041] The framework is sintered by rapid heating to a high temperature in a hydrogen atmosphere. Hydrogen acts as a reducing atmosphere to prevent high-temperature oxidation; rapid heating inhibits grain coarsening, maintaining a fine-grained structure; it increases sintering density while preserving controllable porosity; resulting in a porous framework structure with high strength and good thermal conductivity. Copper is placed in the framework for pressureless copper infiltration sintering (1350℃, 25min), utilizing gravity and capillary action. This avoids reliance on high-pressure equipment, simplifying the process; it utilizes the fluidity of liquid copper and capillary action to achieve uniform infiltration; after filling the framework pores, copper forms a continuous phase, enhancing thermal conductivity and evaporative cooling capacity; and it enables the functional design of the composite material's internal structure. The copper content is controlled between 5wt% and 30wt%, and the composite material's properties are controlled by adjusting the amount of copper added. Low copper content (5-10%) is suitable for high-strength, low-heat-dissipation requirements; medium copper content (15-20%) balances strength and cooling performance; high copper content (25-30%) provides strong sweating cooling capacity, suitable for extreme high-temperature environments; achieving the goal of customizing material performance according to different working conditions. The porous framework structure is controlled to achieve the sweating cooling mechanism, with porosity and pore size distribution controlled by pressing pressure and sintering parameters. The pore structure determines the distribution and flow path of copper; reasonable porosity helps to form a stable sweating cooling effect; allowing copper to continuously evaporate at high temperatures to form a heat-insulating gas film, delaying framework ablation, is one of the core mechanisms for achieving ablation resistance in this invention. Material density control achieves a balance between lightweighting and performance, adjusting material density through porosity and component ratio. Compared to traditional pure tungsten materials, the composite material of this invention has a lower density; achieving lightweighting while ensuring high-temperature resistance and ablation resistance; particularly suitable for weight-sensitive components in the aerospace field; providing a new material solution for weight reduction in aircraft structures.

[0042] Although embodiments of the present invention have been described above in conjunction with the accompanying drawings, the present invention is not limited to the specific embodiments and application fields described above. The specific embodiments described above are merely illustrative and instructive, and not restrictive. Those skilled in the art can make many other forms based on the guidance of this specification and without departing from the scope of protection of the claims of the present invention, and all of these are within the scope of protection of the present invention.

Claims

1. A method for preparing a copper-infiltrated refractory alloy composite material, characterized in that, It includes, Step 1: Weigh the refractory metal powder according to the predetermined mass ratio and mix them to obtain a mixed powder. Step 2: Press the mixed powder into a compact using a cold isostatic press. Step 3: The pressed billet is placed in a spark plasma sintering furnace to sinter and obtain a refractory alloy skeleton. In the process, under a hydrogen protective atmosphere, the pressed billet is heated to 1800-2200°C and held for 25 minutes to form a refractory alloy skeleton. Step 4: Mix copper powder with alcohol and press it into shape in a cold isostatic press to obtain a copper billet; Step 5: Place the refractory alloy skeleton under the skeleton and sinter it. Heat the mixture to 1350℃ in a hydrogen atmosphere and hold it for 25 minutes to obtain the refractory alloy copper-infiltrated composite material.

2. The method according to claim 1, characterized in that, Preferably, the average particle size of the refractory metal powder is 15-43 μm, and the refractory metal powder includes tungsten powder, molybdenum powder, tantalum powder, niobium powder, and X powder.

3. The method according to claim 1, characterized in that, Weighing refractory metal powders according to a predetermined mass ratio includes weighing and mixing tungsten powder, molybdenum powder, tantalum powder, niobium powder, and X powder in equal atomic ratios. The X powder is selected from at least one of titanium, zirconium, hafnium, or silicon to adjust the skeleton strength and oxidation resistance.

4. The method according to claim 1, characterized in that, In step 2, stearic acid is dissolved in alcohol, mixed powder is added and stirred evenly, dried and then pressed into shape in a cold isostatic press to obtain a porous green body. The obtained porous green body is then sintered without pressure in a sintering furnace to remove stearic acid.

5. The method according to claim 4, characterized in that, The stearic acid is dissolved in alcohol at a temperature of 40–80°C, the mass percentage of stearic acid in the solution is 1%–3%, the drying temperature is 40–80°C, the drying time is 0.5–4 hours, the pressure used in the pressing process is 200 MPa–650 MPa, and the porous green body is heated to 400°C in a sintering furnace without pressure and held for 10 minutes to remove stearic acid.

6. The method according to claim 1, characterized in that, In step 3, the heating rate during sintering is 100℃ / min.

7. The method according to claim 1, characterized in that, In step 4, the copper content of the refractory alloy copper-infiltrated composite material is 5wt% to 30wt%. The thermal conductivity and ablation resistance of the refractory alloy copper-infiltrated composite material are controlled by adjusting the copper content.

8. A copper-infiltrated refractory alloy composite material, characterized in that, It is prepared by the method described in any one of claims 1-7.

9. An application of the copper-infiltrated refractory alloy composite material as described in claim 8, characterized in that, The refractory alloy copper-infiltrated composite material is used to manufacture the nose cone and wing leading edge of hypersonic aircraft.

Images