A radiation-resistant layered metal composite material and its preparation method

Abstract

This application discloses a radiation-resistant layered metal composite material and its preparation method. The preparation method includes: melting and casting an Al-3.5Cu-2Mg-Ni alloy ingot; homogenizing, hot-rolling, and annealing the Al-3.5Cu-2Mg-Ni alloy ingot; and composite rolling the annealed Al-3.5Cu-2Mg-Ni alloy ingot with a tantalum-tungsten alloy plate to obtain the radiation-resistant layered metal composite material. The composition and weight percentage of the Al-3.5Cu-2Mg-Ni alloy ingot are as follows: Si: ≤0.5%, Fe: 0.2-0.6%, Cu: 3-3.8%, Mn: ≤0.05%, Mg: 1.8-2.4%, Ni: 0.8-1.2%, Zn: ≤0.3%, Ti: ≤0.5%, other elements with individual content ≤0.05%, total content ≤0.15%, and the balance being aluminum. The Al-3.5Cu-2Mg-Ni alloy of this application incorporates a certain amount of Cu, Mg, and Ni, which not only improves the alloy's ability to block extranuclear electrons, but also forms precipitates such as Al2Cu and Al2CuMg during the aging process, thereby increasing the aging strengthening effect.

Description

Technical Field

[0001] This application relates to the field of aluminum alloy composite materials technology, specifically to a radiation-resistant metal layered composite material and its preparation method. Background Technology

[0002] Spacecraft, including deep space exploration vehicles, medium- and high-orbit vehicles, and commercial satellites, suffer severe total dose effects from space radiation particle bombardment during their operation, seriously threatening the on-orbit lifespan and reliability of space products. Currently, my country's aerospace sector primarily uses single-element aluminum alloys as protective materials for space radiation. However, with deep space exploration and navigation satellites becoming part of my country's major national strategic missions, single-element aluminum alloys can no longer fully meet the radiation protection requirements for total dose. Foreign countries have developed dissimilar metal patch-type protective materials using aluminum and tantalum, but these require additional support and connection structures, increasing mass and launch costs.

[0003] An existing method for preparing an aluminum-tantalum composite plate involves vacuum diffusion welding. However, this method requires high surface finish, necessitating sequential polishing with 600#, 800#, 1000#, and 1200# sandpaper to a mirror finish, making it unsuitable for industrial production. Furthermore, the maximum tensile strength is only 39 MPa, failing to meet the mechanical performance requirements of aerospace products. Another method involves heterothermal rolling to prepare an aluminum / aluminum / tantalum three-layer composite material, achieving a shear strength of 70 MPa in the aluminum-tantalum layered composite plate. A lightweight, high-strength aluminum-tantalum composite metal sheet and its rolling forming method are also described, but these require vacuuming the heating furnace and purging with argon gas during the rolling process, resulting in high production costs.

[0004] In summary, the room-temperature mechanical properties of aluminum / tantalum layered composite plates prepared by existing technologies are low, making them unsuitable for use as load-bearing structural components in aerospace vehicle payloads. Furthermore, their low space radiation shielding efficiency fails to meet the requirements of deep space exploration missions. Moreover, during the heat treatment process to improve the mechanical and interfacial shear properties of aluminum / tantalum composites, surface oxidation and the formation of interfacial compounds may occur. Additionally, the significant difference in their coefficients of thermal expansion leads to interfacial layer delamination under thermal cycling conditions, resulting in product failure. Summary of the Invention

[0005] To address the aforementioned deficiencies in this field, this application aims to provide a radiation-resistant layered metal composite material and its preparation method.

[0006] According to one aspect of this application, a method for preparing a radiation-resistant layered metal composite material is provided, comprising:

[0007] Melting and casting Al-3.5Cu-2Mg-Ni alloy ingots;

[0008] The Al-3.5Cu-2Mg-Ni alloy ingot was homogenized, hot-rolled, and annealed.

[0009] The annealed Al-3.5Cu-2Mg-Ni alloy ingot was composite rolled with tantalum-tungsten alloy plate to obtain a radiation-resistant metal layered composite material.

[0010] The composition and weight percentage of the Al-3.5Cu-2Mg-Ni alloy ingot are as follows: Si: ≤0.5%, Fe: 0.2~0.6%, Cu: 3~3.8%, Mn: ≤0.05%, Mg: 1.8~2.4%, Ni: 0.8~1.2%, Zn: ≤0.3%, Ti: ≤0.5%, other elements with individual content ≤0.05%, total content ≤0.15%, and the balance being aluminum.

[0011] According to some embodiments of this application, the homogenization process includes: heating to 492-498°C at a rate of 80-100°C / h, holding for ≥1.5h for every 40mm of alloy ingot thickness, rapidly heating to 500-510°C after holding for 10-15h, and then air-cooling the ingot after the holding time is completed.

[0012] According to some embodiments of this application, the hot rolling temperature is 470±10℃, the heating time is ≥1.5h, the initial rolling temperature is 440±20℃, the final rolling temperature is ≥270℃, and the reduction per pass is ≤40%.

[0013] According to some embodiments of this application, the annealing temperature is 350–380°C and the holding time is 3–6 hours.

[0014] According to some embodiments of this application, the single-pass reduction in composite rolling is 35-40%.

[0015] According to some embodiments of this application, the preparation method further includes: sequentially subjecting the radiation-resistant metal layered composite material to solution treatment and aging treatment.

[0016] According to some embodiments of this application, the solution treatment includes: heating to 190-210°C at a rate of 5-10°C / min and holding for 25-35 min under a nitrogen protective atmosphere, then raising the temperature to 495-505°C at a rate of 10-15°C / min and holding for 1.5-2 h.

[0017] According to some embodiments of this application, the aging treatment includes: immediately aging the solution-treated radiation-resistant layered composite material under a nitrogen protective atmosphere.

[0018] According to some embodiments of this application, the aging treatment temperature is 180–250°C, and the holding time is ≥12h.

[0019] According to another aspect of this application, a radiation-resistant metal layered composite material is also provided, which is an Al-3.5Cu-2Mg-Ni alloy-tantalum-tungsten alloy layered composite material;

[0020] The composition and weight percentage of the Al-3.5Cu-2Mg-Ni alloy ingot are as follows: Si: ≤0.5%, Fe: 0.2~0.6%, Cu: 3~3.8%, Mn: ≤0.05%, Mg: 1.8~2.4%, Ni: 0.8~1.2%, Zn: ≤0.3%, Ti: ≤0.5%, other elements with individual content ≤0.05%, total content ≤0.15%, and the balance being aluminum;

[0021] In the Al-3.5Cu-2Mg-Ni alloy-tantalum-tungsten alloy layered composite material, the tantalum layer accounts for 15%-75%;

[0022] The radiation-resistant layered metal composite material of this application has a tensile strength ≥500MPa, a yield strength ≥380MPa, and a shear strength ≥100MPa.

[0023] Compared with the prior art, this application has at least the following beneficial effects:

[0024] This application provides a radiation-resistant layered metal composite material, which is an Al-3.5Cu-2Mg-Ni alloy-tantalum-tungsten alloy layered composite material. The Al-3.5Cu-2Mg-Ni alloy of this application incorporates a certain amount of Cu, Mg, and Ni, which not only improves the alloy's ability to block extranuclear electrons, but also forms precipitates such as Al2Cu and Al2CuMg during the aging process, thereby increasing the age-hardening effect.

[0025] The composite material of this application has excellent radiation shielding performance. Under the same surface density, the shielding effect is more than 790% higher than that of elemental aluminum material under the continuous electron spectrum (0.5-5 MEV) irradiation in the high-orbit quasi-Earth orbit. Moreover, it has better mechanical properties, with tensile strength ≥500MPa, yield strength ≥380MPa, and shear strength ≥100MPa.

[0026] This application also provides a method for preparing a radiation-resistant layered metal composite material, which does not undergo significant deformation during heat treatment, maintains a good plate shape, and does not require straightening after heat treatment. Furthermore, the preparation method of this application includes a homogenization annealing step, which essentially eliminates the microsegregation generated during casting, facilitating the uniform distribution of precipitated phases during subsequent aging and resulting in more uniform performance. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the structure of the radiation-resistant metal layered composite material of this application.

[0028] Figure 2 This is a schematic diagram illustrating the proton-blocking ability of different elements.

[0029] Figure 3 This diagram illustrates the electron blocking ability of different elements.

[0030] Figure 4 This is a product image of the radiation-resistant metal layered composite material prepared in Example 1 of this application.

[0031] Figure 5 This is a product image of the radiation-resistant metal layered composite material prepared in Example 2 of this application.

[0032] Figure 6 This is a product image of the radiation-resistant metal layered composite material prepared in Example 3 of this application.

[0033] Figure 7 A product diagram of the radiation-resistant metal layered composite material prepared for Comparative Example 1 of this application.

[0034] Figure 8 The image shows product diagrams of the radiation-resistant metal layered composite materials prepared in Examples 2 and 3 of this application.

[0035] Figure 9 The SEM microstructure of Al-3.5Cu-2Mg-Ni alloy after different homogenization heat treatments is shown.

[0036] Figure 10 The SEM microstructure of Al-3.5Cu-2Mg-Ni aluminum alloy after different two-stage homogenization heat treatments. Detailed Implementation

[0037] The technical solution of this application will be clearly and completely described below with reference to the embodiments of this application. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0038] It should be particularly noted that similar substitutions and modifications made to this application are obvious to those skilled in the art, and they are all considered to be included in this application. Those skilled in the art can obviously make modifications or appropriate alterations and combinations to the methods and applications described herein without departing from the content, spirit, and scope of this application to implement and apply the technology of this application. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments.

[0039] Unless otherwise specified, this application is conducted under standard conditions or conditions recommended by the manufacturer. The raw materials or excipients used, as well as the reagents or instruments used, whose manufacturers are not specified, are all conventional products that can be obtained commercially.

[0040] The following is a detailed description of this application.

[0041] Satellites operating in orbit primarily encounter space radiation environments including radiation belt electrons, radiation belt protons, solar cosmic ray protons and heavy ions, and galactic cosmic ray protons and heavy ions. Among these, radiation belt electrons and radiation belt protons are the main sources of total dose effect. The shielding effectiveness of materials with different atomic numbers varies. Generally, materials with higher atomic numbers provide better electron shielding, mainly because they exhibit greater elastic scattering of electrons (proportional to Z² / A). Since materials with lower atomic numbers typically have a larger Z / A ratio, they are more effective at blocking protons per unit equivalent thickness. Therefore, materials with lower atomic numbers are generally preferred for proton shielding.

[0042] according to Figure 2 , Figure 3 As shown, Ta and W elements have a strong ability to block extranuclear electrons, while Al, Mg, Cu, and Ni elements have a strong ability to block protons. Therefore, this application uses Al-3.5Cu-2Mg-Ni alloy and tantalum-tungsten alloy to prepare a novel aluminum / tantalum layered composite material by rolling. Under the same areal density, its shielding and protection effect is more than 90% higher than that of elemental aluminum material.

[0043] The technical solution of this application will be further described below with reference to specific embodiments.

[0044] Example 1:

[0045] The composition of Al-3.5Cu-2Mg-Ni alloy ingot is as follows: Si content is 0.4%, Fe content is 0.52%, Cu content is 3.7%, Mn content is 0.01%, Mg content is 2.4%, Ni content is 1.1%, Zn content is 0.01%, and Ti content is 0.02%.

[0046] Ingot casting: Al-3.5Cu-2Mg-Ni alloy ingots are smelted and cast according to the designed composition ratio; the ingot thickness is 480mm.

[0047] Homogenization treatment: The homogenization process for aluminum alloy ingots involves heating to 495℃ at a rate of 90℃ / h, holding for 18 hours, then rapidly heating to 505℃ and holding for 12 hours. After the holding time is completed, the ingots are removed from the furnace and air-cooled.

[0048] Hot rolling and annealing: The hot rolling heating temperature is 480℃, the heating time is 2h, the initial rolling temperature is 452℃, the final rolling temperature is 300℃, the thickness of the hot rolled plate is 2.6mm, and it is rolled in 12 passes, with a reduction of ≤40% per pass; the aluminum alloy hot rolled plate is annealed at a temperature of 350℃ and a holding time of 5h.

[0049] Composite rolling: The surfaces of the 2.6mm aluminum alloy plate and the 0.65mm thick Ta2.5W alloy plate were cleaned by using a wire brush and a flap wheel, respectively. After stacking the billets, they were rolled at room temperature with a reduction of 38.5% in one pass to a thickness of 2mm, of which the tantalum layer was 0.4mm thick, to obtain a layered composite material.

[0050] The layered composite material underwent solution treatment and aging treatment: nitrogen was used as a protective gas, and the temperature was raised to 200℃ at a rate of 8℃ / min and held for 30 min. The temperature was then increased to 500℃ at a rate of 12℃ / min and held at 500℃ for 1 hour and 50 min. The material was then immediately transferred to an aging furnace for aging treatment. The aging temperature range was 200℃, and the holding time was 15 hours. After aging, the material was air-cooled.

[0051] After solution treatment and aging, the aluminum-tantalum composite plate profile is shown in the figure. Figure 4 .

[0052] Example 2:

[0053] The composition of Al-3.5Cu-2Mg-Ni alloy ingot is as follows: Si content is 0.35%, Fe content is 0.42%, Cu content is 3.5%, Mn content is 0.01%, Mg content is 2.1%, Ni content is 1.0%, Zn content is 0.01%, and Ti content is 0.02%.

[0054] Ingot casting: Al-3.5Cu-2Mg-Ni alloy ingots are smelted and cast according to the designed composition ratio; the ingot thickness is 420mm.

[0055] Homogenization treatment: The homogenization process for cast aluminum alloy is to heat up to 493℃ at a rate of 80℃ / h, hold for 16h, then rapidly heat up to 510℃, hold for 12h, and then remove from the furnace and air cool.

[0056] Hot rolling and annealing: The hot rolling heating temperature is 470℃, the heating time is 2.5h, the initial rolling temperature is 445℃, the final rolling temperature is 280℃, the thickness of the hot-rolled plate is 0.28mm, and it is rolled in 14 passes, with a reduction of ≤40% per pass; the aluminum alloy hot-rolled plate is annealed at 380℃ for 4h.

[0057] Composite rolling: The surfaces of the 0.28mm aluminum alloy plate and the 0.75mm thick Ta2.5W alloy plate to be composited are cleaned with a wire brush, stacked and rolled at room temperature. The reduction in one pass is 39.8% to a thickness of 0.62mm, of which the tantalum layer is 0.46mm thick, to obtain a layered composite material.

[0058] The layered composite material underwent solution treatment and aging treatment: nitrogen was used as a protective gas, and the material was heated to 200℃ at a rate of 6℃ / min and held for 30 min. The temperature was then increased to 495℃ at a rate of 10℃ / min and held at 495℃ for 2 h. Immediately after removal, it was transferred to an aging furnace for aging treatment. Oxidation of the tantalum layer was prevented during heating. The aging temperature range was 210℃, and the holding time was 14 h. The material was then removed and air-cooled. Nitrogen was used as a protective gas during heating to prevent oxidation of the tantalum layer.

[0059] After solution treatment and aging, the aluminum-tantalum composite plate profile is shown in the figure. Figure 5 .

[0060] Example 3:

[0061] The composition of Al-3.5Cu-2Mg-Ni alloy ingot is as follows: Si content is 0.32%, Fe content is 0.46%, Cu content is 3.2%, Mn content is 0.01%, Mg content is 1.9%, Ni content is 1.0%, Zn content is 0.01%, and Ti content is 0.02%.

[0062] Ingot casting: Al-3.5Cu-2Mg-Ni alloy ingots are smelted and cast according to the designed composition ratio; the ingot thickness is 360mm.

[0063] Homogenization treatment: The homogenization process for cast aluminum alloy is to heat up to 498℃ at a rate of 100℃ / h, hold for 13.5h, then rapidly heat up to 500℃, hold for 12h, and then remove from the furnace and air cool.

[0064] Hot rolling annealing: hot rolling heating temperature 470℃, heating time 2h, initial rolling temperature 448℃, final rolling temperature 296℃, hot rolling plate thickness 5mm, a total of 10 passes, each pass reduction ≤40%; aluminum alloy hot rolling plate undergoes annealing treatment, annealing temperature 360℃, holding time 6h.

[0065] Composite rolling: The surfaces of the 5mm aluminum alloy plate and the 1.5mm thick Ta2.5W alloy plate to be composited are cleaned with a wire brush, stacked and rolled at room temperature. The reduction in one pass is 36.5% to a thickness of 4.13mm, of which the tantalum layer is 0.98mm thick, to obtain a layered composite material.

[0066] The layered composite material underwent solution treatment and aging treatment: nitrogen was used as a protective gas, and the material was heated to 210℃ at a rate of 9℃ / min and held for 25 min. The temperature was then increased to 505℃ at a rate of 15℃ / min and held at 505℃ for 2 h. After removal, it was immediately transferred to an aging furnace for aging treatment. Oxidation of the tantalum layer was prevented during heating. The aging temperature range was 190℃, and the holding time was 18 h. The material was then removed and air-cooled. Nitrogen was used as a protective gas during heating to prevent oxidation of the tantalum layer.

[0067] After solution treatment and aging, the aluminum-tantalum composite plate type is shown in 6.

[0068] Comparative Example 1: (Different aluminum alloy compositions result in poorer mechanical properties and lower radiation resistance)

[0069] Aluminum alloy composition: 1060 aluminum alloy is used, with the following chemical composition: Si 0.15%, Fe 0.18%, Cu 0.03%, Mn 0.02%, Mg 0.02%, Ni 0.01%, Zn 0.01%, Ti 0.01%, and Al 99.4%.

[0070] Ingot: The alloy ingot is smelted and cast according to the designed composition ratio; the ingot thickness is 480mm.

[0071] Homogenization process: The 1060 aluminum alloy ingot is homogenized by heating to 495℃ at a rate of 90℃ / h, holding for 18h, then rapidly heating to 505℃ and holding for 12h. After the holding time is completed, the ingot is removed from the furnace and air-cooled.

[0072] Hot rolling and annealing: The hot rolling temperature is 480℃, the heating time is 2h, the initial rolling temperature is 455℃, the final rolling temperature is 306℃, the thickness of the hot-rolled plate is 2.6mm, and it is rolled in 12 passes, with a reduction of ≤40% per pass. The 1060 aluminum alloy hot-rolled plate is annealed at 350℃ for 5h.

[0073] Composite rolling: The surfaces of the 2.6mm 1060 aluminum alloy plate and the 0.65mm thick Ta2.5W alloy plate to be composite were cleaned by using a wire brush. After stacking the billets, they were rolled at room temperature with a reduction of 38.5% in one pass to a thickness of 2mm, of which the tantalum layer was 0.4mm thick, to obtain a layered composite material.

[0074] The layered composite material underwent solution treatment and aging treatment: nitrogen was used as a protective gas, and the temperature was raised to 200℃ at a rate of 8℃ / min and held for 30 min. The temperature was then increased to 500℃ at a rate of 12℃ / min and held at 500℃ for 1 hour and 50 min. The material was then immediately transferred to an aging furnace for aging treatment. The aging temperature range was 200℃, and the holding time was 15 hours. After aging, the material was air-cooled.

[0075] After solution treatment and aging, the aluminum-tantalum composite plate profile is shown in the figure. Figure 7 .

[0076] Comparative Example 2: (The aluminum alloy composition is the same as in Example 1, but the solution treatment and aging process is different, resulting in poorer plate shape and slightly lower performance.)

[0077] The layered composite material underwent solution treatment and aging treatment: nitrogen was used as a protective gas, and the temperature was raised to 500℃ at a rate of 12℃ / min, held for 1 hour and 50 minutes, and then removed and water-cooled. The aging temperature was 200℃, the holding time was 15 hours, and then the material was removed and air-cooled.

[0078] After solution treatment and aging, the aluminum-tantalum composite plate profile is shown in the figure. Figure 8 (Left).

[0079] Comparative Example 3: (Same aluminum alloy composition, different solution treatment and aging times, resulting in lower performance)

[0080] The layered composite material underwent solution treatment and aging treatment: nitrogen was used as a protective gas, and the temperature was raised to 200℃ at a rate of 8℃ / min and held for 30 min. The temperature was then increased to 500℃ at a rate of 12℃ / min and held at 500℃ for 3 h. Immediately after removal, the material was transferred to an aging furnace for aging treatment. The aging temperature range was 200℃, and the holding time was 10 h. The material was then removed and air-cooled.

[0081] After solution treatment and aging, the aluminum-tantalum composite plate profile is shown in the figure. Figure 8 (right).

[0082] Comparative Example 4: (The aluminum alloy composition is the same as in Example 1, but the homogenization process is different)

[0083] The composition of the Al-3.5Cu-2Mg-Ni alloy ingot is as follows: Si content 0.4%, Fe content 0.52%, Cu content 3.7%, Mn content 0.01%, Mg content 2.4%, Ni content 1.1%, Zn content 0.01%, and Ti content 0.02%. (The composition is the same as in Example 1)

[0084] Ingot casting: An Al-3.5Cu-2Mg-Ni alloy ingot was melted and cast according to the designed composition ratio; the ingot thickness was 480 mm. (Ingot specifications are the same as in Example 1)

[0085] Homogenization treatment: The homogenization process for aluminum alloy ingots involves heating to 490℃ at a rate of 90℃ / h, holding for 18h, then rapidly heating to 498℃ and holding for 12h. After the holding time is completed, the ingots are removed from the furnace and air-cooled.

[0086] Hot rolling and annealing: The hot rolling heating temperature is 480℃, the heating time is 2h, the initial rolling temperature is 452℃, the final rolling temperature is 300℃, the thickness of the hot rolled plate is 2.6mm, and it is rolled in 12 passes, with a reduction of ≤40% per pass; the aluminum alloy hot rolled plate is annealed at a temperature of 350℃ and a holding time of 5h.

[0087] Composite rolling: The surfaces of the 2.6mm aluminum alloy plate and the 0.65mm thick Ta2.5W alloy plate were cleaned by using a wire brush and a flap wheel, respectively. After stacking the billets, they were rolled at room temperature with a reduction of 38.5% in one pass to a thickness of 2mm, of which the tantalum layer was 0.4mm thick, to obtain a layered composite material.

[0088] The layered composite material underwent solution treatment and aging treatment: nitrogen was used as a protective gas, and the temperature was raised to 200℃ at a rate of 8℃ / min and held for 30 min. The temperature was then increased to 500℃ at a rate of 12℃ / min and held at 500℃ for 1 hour and 50 min. The material was then immediately transferred to an aging furnace for aging treatment. The aging temperature range was 200℃, and the holding time was 15 hours. After aging, the material was air-cooled.

[0089] Experimental Example

[0090] 1. Test the mechanical properties and shielding effectiveness of the composite materials in the above embodiments and comparative examples.

[0091] The shielding effectiveness test utilizes a 90Sr-90Y electron radiation source device to test the shielding effectiveness of aluminum / tantalum composite materials of different specifications under irradiation with a continuous electron spectrum (0.5-5 MEV) in a high-orbit quasi-Earth orbit, as well as the shielding effectiveness of elemental aluminum material of the same mass (i.e., equivalent aluminum thickness). Equivalent aluminum thickness = Al layer thickness in the composite material + TaW layer thickness × TaW layer density ÷ Al layer density. For example, in Example 1, the composite material consists of 1.6 mm of aluminum + 0.4 mm of tantalum, and the equivalent aluminum thickness is 1.6 + 0.4 × 16.68 ÷ 2.7 = 4 mm.

[0092] The test results are shown in Tables 1 and 2.

[0093] Table 1

[0094]

[0095]

[0096] Table 2

[0097]

[0098] 2. Test the effect of the homogenization process in the preparation process of this application, such as... Figure 9 , Figure 10 .

[0099] Figure 9 The SEM microstructures of Al-3.5Cu-2Mg-Ni alloy after different homogenization heat treatments are shown, where (a) is in the as-cast state; (b) at 480℃ / 24h; (c) at 490℃ / 24h; (d) at 495℃ / 24h; and (e) at 505℃ / 24h. Figure 10 The SEM microstructures of Al-3.5Cu-2Mg-Ni aluminum alloys after different double-stage homogenization heat treatments are shown, where (a) 495℃ / 12h+505℃ / 12h; (b) 495℃ / 18h+505℃ / 12h.

[0100] according to Figure 9 It is evident that extending the time of a single homogenization treatment still cannot completely eliminate the non-equilibrium phases in the ingot; according to Figure 10 It can be seen that a two-stage homogenization treatment with a heat preservation time of ≥1.5h for every 40mm thickness can result in a cleaner and more uniform tissue morphology.

[0101] The microstructure of the aluminum alloy in Example 1 after different homogenization heat treatments can be compared. It can be seen that after homogenization treatment at 495℃ / 18h + 505℃ / 12h, the coarse S(Al2CuMg) phase, AlCuFeMn phase and θ(Al2Cu) phase on the grain boundaries are basically completely dissolved in the matrix. The non-equilibrium crystalline phases on the grain boundaries are continuously reduced to almost completely eliminated, the compositional segregation is gradually eliminated, and the microstructure becomes more uniform.

[0102] The above experimental examples show that the addition of certain amounts of Cu, Mg, and Ni to the Al-3.5Cu-2Mg-Ni alloy of this application not only improves the radiation shielding ability of the alloy, but also forms precipitates such as Al2Cu and Al2CuMg during the aging process, increasing the mechanical properties of the composite material (Examples 1-3 and Comparative Example 1); the heat treatment system of this application, by adding a 200℃ heat treatment stage before solution treatment, can effectively prevent the deformation of the composite plate during the solution treatment process, eliminating the need for straightening after heat treatment (Example 1 and Comparative Example 2); heat treatment within the solution and aging temperature and time range of this application can effectively improve the mechanical properties of the composite plate (Example 1 and Comparative Example 3); the homogenization heat treatment system of this application can eliminate the microsegregation generated during the casting process, which is beneficial to the uniform distribution of precipitates during subsequent aging, making the properties more uniform.

[0103] The above description of the embodiments is only for the purpose of helping to understand the method and core ideas of this application. It should be noted that, for those skilled in the art, several improvements and modifications can be made to this application without departing from the principles of this application, and these improvements and modifications also fall within the protection scope of the claims of this application.

Claims

1. A method for producing an anti-radiation metal layered composite material, characterized by, The application relates to an Al-3.5Cu-2Mg-Ni alloy ingot, a radiation-resistant metal layered composite material and a preparation method thereof. The Al-3.5Cu-2Mg-Ni alloy ingot is subjected to homogenization treatment, hot rolling and annealing. The Al-3.5Cu-2Mg-Ni alloy ingot after the annealing is subjected to composite rolling with a tantalum-tungsten alloy plate to obtain the radiation-resistant metal layered composite material. The Al-3.5Cu-2Mg-Ni alloy ingot comprises the following components in percentage by weight: Si: <=0.5%, Fe: 0.2-0.6%, Cu: 3-3.8%, Mn: <=0.05%, Mg: 1.8-2.4%, Ni: 0.8-1.2%, Zn: <=0.3%, Ti: <=0.5%, other elements: <=0.05% in single content and <=0.15% in total content, and the rest is aluminum. The homogenization treatment comprises the following steps: heating at a speed of 80-100 DEG C / h to 492-498 DEG C, keeping the temperature for >=1.5 h per 40 mm of the thickness of the alloy ingot, rapidly heating to 500-510 DEG C after the keeping, keeping the temperature for 10-15 h, and air cooling after the keeping. The hot rolling temperature is 470 DEG C + / - 10 DEG C, the heating time is >=1.5 h, the opening rolling temperature is 440 DEG C + / - 20 DEG C, the final rolling temperature is >=270 DEG C, and the reduction per pass is <=40%. The reduction per pass of the composite rolling is 35-40%. The annealing temperature is 350-380 DEG C, and the keeping time is 3-6 h.

2. The production method according to claim 1, characterized by, The application further relates to a radiation-resistant metal layered composite material.

3. The production method according to claim 1 or 2, characterized by, The radiation-resistant metal layered composite material is subjected to solid solution treatment and aging treatment. The solid solution treatment comprises the following steps: heating to 190-210 DEG C at a speed of 5-10 DEG C / min under a nitrogen protective atmosphere, keeping the temperature for 25-35 min, then heating to 495-505 DEG C at a speed of 10-15 DEG C / min, and keeping the temperature for 1.5-2 h.

4. The preparation method according to claim 3, characterized in that, The aging treatment comprises the following steps: immediately performing the aging treatment on the radiation-resistant metal layered composite material after the solid solution treatment under a nitrogen protective atmosphere.

5. The preparation method according to claim 4, characterized in that, The aging treatment is performed at a temperature of 180-250 DEG C for >=12 h.

6. The preparation method according to claim 5, characterized in that, The application relates to an Al-3.5Cu-2Mg-Ni alloy ingot, a radiation-resistant metal layered composite material and a preparation method thereof.

7. The radiation-shielding metal layered composite prepared by the production method according to any one of claims 1 to 6, characterized by The radiation-resistant metal layered composite material has a tensile strength of >=500 MPa, a yield strength of >=380 MPa and a shear strength of >=100 MPa. ​

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