Aluminum / tantalum composite material for radiation shielding and method for manufacturing the same

Abstract

The application provides an aluminum / tantalum composite material for radiation shielding and a preparation method thereof. The composite material has a laminated structure and sequentially comprises a 2A12 aluminum alloy layer, a 1-series aluminum alloy layer, a tantalum layer and a 1-series aluminum alloy layer. The composite material is continuously compounded, and no additional support connection structure is needed, so that the protective piece structure is compact, and the weight of the protective structure is reduced. The rolling compounding technology is adopted to form a stable metallurgical bonding interface, and the separation of the aluminum / tantalum composite interface caused by the aging of glue under space thermal cycling is avoided.

Description

Technical Field

[0001] In the field of non-ferrous metal materials processing technology, specifically, it relates to an aluminum / tantalum composite material for radiation shielding and its preparation method. Background Technology

[0002] Aerospace technology is a vital national asset and a major strategy that determines the future development of a country. Spacecraft are the core of aerospace technology. Because satellites are exposed to radiation from various charged particles in space, the radiation resistance of electronic devices is a crucial factor affecting the development of navigation, communication, and other medium- and high-orbit satellites, as well as deep space exploration satellites. Currently, protection against total dose and displacement damage effects on electronic devices mainly relies on passive shielding.

[0003] Currently, the shielding protection in this field mainly uses single-element 2A12 aluminum alloy, but its protection efficiency is low. The only way to improve the protection effect is to increase the thickness. However, the increased mass leads to higher launch costs, making it difficult to meet the radiation hardening requirements of my country's navigation, communication and other medium and high orbit satellites as well as deep space exploration satellites.

[0004] Developing composite material-based protective structures for electronic devices in space environments can significantly reduce satellite launch and component usage costs. Studies show that composite materials can reduce mass by 30% compared to elemental aluminum while achieving the same radiation dose protection level. To achieve low-mass, high-efficiency electronic device protection technology, composite materials are essential. High-energy electrons lose energy primarily through ionization and radiation. According to Bethe's law, shielding materials with different atomic numbers have varying shielding effects. The blocking ability of a target material per unit surface density is approximately proportional to Z / A (Z is the atomic number, A is the relative atomic mass). Simultaneously, electrons are subjected to elastic scattering from the atomic nucleus, deviating from the incident direction, which is equivalent to increasing the shielding thickness. Elastic scattering is proportional to Z² / A. Low-Z materials have a higher Z / A value than high-Z materials, resulting in greater ionization energy loss. High-Z materials, due to scattering, suffer greater radiation energy loss. Therefore, for high-energy electron radiation protection, placing a certain thickness of high-Z material, such as aluminum-tantalum alloy, behind low-Z material can significantly optimize the shielding effect.

[0005] However, aluminum and tantalum exhibit significant differences in properties, particularly in their melting points and hot working temperature ranges (aluminum melts at 660℃, while tantalum melts at 2995℃, with a difference in thermal expansion coefficients of approximately four times). This leads to considerable technical challenges in processing deformation and heat treatment. Furthermore, the unique environment of space applications, with its alternating hot and cold cycles, causes cracking or delamination at the composite interface due to the difference in thermal expansion coefficients between the dissimilar metals.

[0006] Currently, a series of research studies have been conducted in China on the preparation technology of aluminum-tantalum and similar composite materials. For example, a patent discloses a lightweight, high-strength Mg-Ta composite metal sheet and its room temperature rolling forming method. This method uses a room temperature rolling process to prepare the Mg-Ta composite metal sheet, with low-temperature annealing and high-temperature diffusion bonding treatments performed between rolling passes. The heat treatment process is complex, and the prepared composite sheet exhibits severe edge cracks. Furthermore, due to the close-packed hexagonal structure of Mg, its poor room temperature plasticity and low deformation capacity make further processing and forming of this composite material difficult, placing it some distance from practical application. Another patent discloses a method for preparing a shielded magnesium-tantalum multilayer composite plate. After stacking magnesium (magnesium alloy) and tantalum (tantalum alloy) into a blank, it requires vacuuming and sealing within a cladding before hot rolling. This places high demands on production equipment and is not conducive to large-scale industrial production. A patent discloses a method for preparing a titanium / tantalum composite plate and its product. The plate is protected by an inert atmosphere during both heating and heat preservation, resulting in high production costs. Furthermore, titanium or titanium alloy materials are expensive, have poor processing performance, and are difficult to further process and weld, making it difficult to apply on a large scale in practice. Summary of the Invention

[0007] To address the aforementioned deficiencies in this field, this application aims to provide an aluminum / tantalum composite material for radiation shielding and a method for preparing the same.

[0008] According to one aspect of this application, this application provides a method for preparing an aluminum / tantalum composite material for radiation shielding, comprising:

[0009] The surfaces of 2A12 aluminum alloy plate, tantalum plate and 1 series aluminum alloy foil were polished respectively.

[0010] The polished 1-series aluminum alloy foil is placed on the upper and lower sides of the tantalum plate to obtain the assembly blank;

[0011] The assembled blank is subjected to cold rolling and stress-relieving annealing to obtain the composite component;

[0012] The composite components after stress-relieving annealing are then assembled with 2A12 aluminum alloy plates in a secondary process.

[0013] The secondary billet is heated and rolled, and then air-cooled to room temperature to obtain a composite plate.

[0014] According to some embodiments of this application, the cold rolling temperature is 20-35 degrees Celsius, the rolling speed is less than 1 m / min, the rolling is done in one pass, and the deformation is controlled to be 20%-30%.

[0015] According to some embodiments of this application, the temperature of the stress-relieving annealing treatment is 240℃~260℃, and the holding time is 0.5~2h;

[0016] After the heat preservation time is completed, the blanks should be removed quickly, air-cooled to room temperature, and then assembled again.

[0017] According to some embodiments of this application, the secondary billet heating temperature is 300℃~400℃, and the holding time is 20min~60min.

[0018] According to some embodiments of this application, the hot rolling is performed using a two-roll mill or a four-roll mill, with a rolling speed of 5 to 20 m / min and a reduction of 30 to 50% per pass.

[0019] According to another aspect of this application, an aluminum / tantalum composite material for radiation shielding is also provided, which is a laminated composite material.

[0020] The stacked structure comprises, in sequence: a 2A12 aluminum alloy layer, a 1-series aluminum alloy layer, a tantalum layer, and a 1-series aluminum alloy layer.

[0021] According to some embodiments of this application, the thickness of the 2A12 aluminum alloy layer is 1.2–5.0 mm;

[0022] The thickness of the tantalum layer is 0.3–1.2 mm;

[0023] The thickness of the 1-series aluminum alloy layer is 0.02 to 0.05 mm.

[0024] According to some embodiments of this application, the tantalum layer is pure tantalum or a tantalum-tungsten alloy.

[0025] According to some embodiments of this application, the tantalum-tungsten alloy is Ta2.5W, Ta7.5W, or Ta10W;

[0026] Optionally, the total unavoidable impurities in the pure tantalum or tantalum-tungsten alloy are less than 0.5%.

[0027] According to some embodiments of this application, the 1-series aluminum alloy is grade 1050, 1060, or 1100.

[0028] Compared with the prior art, this application has at least the following beneficial effects:

[0029] According to an embodiment of this application, an aluminum / tantalum composite material for radiation shielding is provided. Its structure is a laminated structure, sequentially comprising a 2A12 aluminum alloy layer, a 1-series aluminum alloy layer, a tantalum layer, and another 1-series aluminum alloy layer. Compared with current single-element metal materials, this composite material exhibits stable high-energy electron radiation protection performance, low manufacturing cost, ease of maintenance, and superior shielding effect compared to single-element metal materials, thereby reducing the weight and cost of electronic devices.

[0030] Because the slab heating temperature exceeds 300℃ during hot rolling, the oxide layer formed during heating will adversely affect the interfacial bonding during the rolling process, greatly reducing the bonding performance of the composite plate. Meanwhile, during cold rolling, the work hardening phenomenon of cold plastic deformation leads to a decrease in the material's plasticity and toughness, and an increase in brittleness, making it prone to edge cracking. Therefore, the composite material of this application has a 1-series aluminum alloy protective layer on both sides of the tantalum layer, which can prevent the tantalum layer from oxidizing at temperatures above 250℃ and avoid mechanical property degradation caused by cracking during the rolling process.

[0031] The composite material of this application is a continuous composite, which does not require additional support and connection structures, making the protective component structure compact and reducing the weight of the protective structure. Furthermore, this application uses rolling composite technology to prepare a stable metallurgical bonding interface, avoiding the separation of the aluminum and tantalum composite interface caused by the aging of the adhesive under space thermal cycling.

[0032] This application is the first to propose a cold-rolling + hot-rolling method to composite aluminum and tantalum materials, successfully preparing an aluminum-tantalum composite material with excellent interfacial bonding performance. This method avoids the problems of poor sheet shape, easy cracking, and work hardening associated with cold-rolled sheets alone, while also solving the problem of surface oxidation of tantalum or tantalum-tungsten sheets during heating. It retains sufficient deformation during the cold rolling step to improve the bonding effect between 2Al2 and Ta, while achieving a greater diffusion distance of elements at the composite interface after hot rolling, resulting in better metallurgical bonding at the interface compared to purely cold-rolled sheets. Attached Figure Description

[0033] Figure 1 This is a flowchart illustrating the composite material preparation process of an example embodiment of this application.

[0034] Figure 2 This is a schematic diagram of an aluminum / tantalum composite material structure for radiation shielding, as shown in an example embodiment of this application.

[0035] Figure 3 These are scanning electron microscope images of an example embodiment of this application.

[0036] Figure 4 This is a diagram showing the interface diffusion width in an example embodiment of this application.

[0037] Figure 5 This is a sample photograph of Comparative Example 1 of this application.

[0038] Figure 6 This is a photograph of a sample from Comparative Example 2 of this application.

[0039] Figure 7 This is a photograph of the sample for Comparative Example 4 of this application. Detailed Implementation

[0040] 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.

[0041] 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.

[0042] 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.

[0043] The following is a detailed description of this application.

[0044] [The aluminum / tantalum composite material for radiation shielding in this application]

[0045] The composite material of this application is a laminated composite material, which sequentially includes a 2A12 aluminum alloy layer, a 1-series aluminum alloy layer, a tantalum layer, and a 1-series aluminum alloy layer.

[0046] The thickness of the 2A12 aluminum alloy layer is 1.2–5.0 mm.

[0047] The thickness of the tantalum layer is 0.3–1.2 mm;

[0048] The thickness of the 1-series aluminum alloy layer is 0.02 to 0.05 mm.

[0049] Furthermore, the tantalum layer is pure tantalum or a tantalum-tungsten alloy, wherein the tantalum-tungsten alloy is Ta2.5W, Ta7.5W, or Ta10W, and the total unavoidable impurities in the pure tantalum or tantalum-tungsten alloy are less than 0.5%.

[0050] Furthermore, the 1-series aluminum alloy is grade 1050, 1060, or 1100.

[0051] [Preparation method of aluminum / tantalum composite material for radiation shielding according to this application]

[0052] The method for preparing the radiation shielding aluminum-tantalum composite material of this application includes the following steps:

[0053] (1) Polish and degrease the surface of 2A12 aluminum alloy plate, tantalum plate and 1 series aluminum alloy foil to remove the oxide layer, oil or other dirt from the surface;

[0054] (2) Place two 1-series aluminum alloy foils on the top and bottom sides of the tantalum plate respectively to assemble them into a blank;

[0055] (3) The billet assembled in step (2) is rolled at room temperature to obtain a composite component;

[0056] (4) The composite components obtained in step (3) are subjected to stress-relieving annealing.

[0057] (5) The heat-treated composite components are then assembled with 2A12 aluminum alloy plate in a second process.

[0058] (6) After heating, the billet of the secondary assembly is rolled and air-cooled to room temperature to obtain the composite plate product.

[0059] In step (1), the oxide layer or other contaminants on the surface of 2A12 aluminum alloy plate, tantalum plate and 1 series aluminum alloy foil are removed by traditional mechanical grinding. The degreasing method is to clean with alcohol or acetone and then dry. After grinding and degreasing, the surface of the plate is bright and free of visible cracks, slag inclusions, scratches, oil spots, etc., and no grinding debris shall remain on the surface.

[0060] Furthermore, in step (2), the length of the two 1-series aluminum alloy foils on one side is 4-5 mm longer than that of the tantalum plate, and the width of the two sides is 1-2 mm longer than that of the tantalum plate.

[0061] Furthermore, the rolling process in step (3) is carried out at room temperature, the rolling speed is controlled within 1m / min, and the deformation is controlled to be 20% to 30% in one rolling pass.

[0062] During the cold rolling deformation process in step (3), the deformation is large and the temperature is low, resulting in significant internal stress. This internal stress not only affects the material's strength and plasticity but also leads to material deformation after subsequent processing due to stress release. Therefore, the composite component after cold rolling needs to undergo stress-relieving annealing.

[0063] Furthermore, in step (4), the temperature of the stress-relieving annealing treatment is 240℃~260℃, the holding time is 0.5~2h, and after the holding time is completed, it is quickly taken out and air-cooled to room temperature.

[0064] Furthermore, if the composite component plate obtained by room temperature rolling in step (3) exhibits bending, the composite component will be straightened after stress-relieving annealing in step (4).

[0065] Furthermore, in step (5), the heat-treated composite components are polished and degreased according to the relevant method in step (1) to ensure that the surface is bright after polishing and degreasing, without visible cracks, inclusions, scratches, oil spots, etc., and that no debris generated during polishing remains on the surface.

[0066] Furthermore, in step (6), the slab heating temperature is 300℃~400℃, and the holding time is 20min~60min;

[0067] Optionally, in step (6), the slab heating temperature is 350°C and the holding time is 60 min.

[0068] If the heating temperature is too low, the deformation resistance will increase, leading to problems such as poor plate shape and cracks. If the temperature is too high, it will cause excessively coarse grains, affecting product performance. In severe cases, it can lead to overheating, where some low-melting-point eutectics or grain boundaries melt, rendering the product unusable.

[0069] Furthermore, the hot rolling in step (6) is carried out using a two-roll mill or a four-roll mill, with a reduction of 30-50% per pass and a rolling speed controlled at 5-20 m / min.

[0070] Optionally, the single-pass reduction is 40%, and the rolling speed is 10 m / min.

[0071] The present application will now be described in detail with reference to specific embodiments.

[0072] The chemical composition of the 2A12 aluminum alloy material and the 1060 pure aluminum cladding used in the embodiments of this application shall comply with the provisions of the national standard GB / T3190-2020; the chemical composition of pure tantalum shall comply with the provisions of YS / T751-2011; and the chemical composition of tantalum-tungsten (Ta2.5W) shall comply with the provisions of YS / T751-2011.

[0073] Example 1

[0074] Raw material preparation:

[0075]

[0076] Composite material preparation:

[0077] (1) Grind the surface of the above raw materials with a wire brush to remove the oxide film on the surface of the material, wipe the oil stains on the surface of the material with acetone and dry it, and clean the remaining debris on the surface of the material with compressed air.

[0078] (2) The two 1060 aluminum alloy foils after the above treatment are stacked on the upper and lower sides of the pure tantalum plate and assembled into a blank.

[0079] (3) The assembled billet is rolled at room temperature at a rolling speed of 1 m / min and a rolling reduction of 20% in one pass. After rolling, an aluminum / tantalum / aluminum composite component is obtained, and the tantalum is completely wrapped inside the aluminum foil.

[0080] (4) The cold-rolled composite component is subjected to stress-relieving annealing treatment. The heating temperature is 250℃ and the holding time is 1h. After the holding time is completed, it is quickly taken out and placed in the air to cool to room temperature.

[0081] (5) After polishing the surface of the heat-treated composite component according to the method in step (1), it is then assembled with the 2A12 aluminum alloy plate for a second time.

[0082] (6) The billet of the above-mentioned secondary billet assembly is sent to the heating furnace for heating at a temperature of 350°C and a holding time of 60 minutes. After heating, it is sent to the rolling mill for rolling. A two-roll or four-roll rolling mill is used, the reduction of a single pass is 40%, the rolling speed is 10 m / min, and after rolling, it is air-cooled to room temperature.

[0083] Performance testing: The mechanical properties of the prepared aluminum / tantalum composite plate were tested. The average interfacial shear strength was 76.0 MPa and the average tensile strength was 482.5 MPa, which meets the strength requirements of space-based devices.

[0084] Example 2

[0085] Raw material preparation:

[0086]

[0087] Composite material preparation:

[0088] (1) Grind the surface of the above raw materials with a wire brush to remove the oxide film on the surface of the material, wipe the oil stains on the surface of the material with acetone and dry it, and clean the remaining debris on the surface of the material with compressed air.

[0089] (2) The two 1050 aluminum alloy foils after the above treatment are stacked on the upper and lower sides of the tantalum tungsten plate and assembled into a blank.

[0090] (3) The assembled billet is rolled at room temperature at a rolling speed of 0.8 m / min and a rolling reduction of 25% in one pass. After rolling, an aluminum / tantalum / aluminum composite component is obtained, and the tantalum is completely wrapped inside the aluminum foil.

[0091] (4) The above-mentioned cold-rolled composite components are subjected to stress-relieving annealing treatment. The heating temperature is 255℃ and the holding time is 1.2h. After the holding time is completed, they are quickly taken out and placed in the air to cool to room temperature.

[0092] (5) After polishing the surface of the heat-treated composite component according to the method in step (1), it is then assembled with the 2A12 aluminum alloy plate for a second time.

[0093] (6) The billet of the above-mentioned secondary billet is sent to the heating furnace for heating at a temperature of 360°C and a holding time of 60 minutes. After heating, it is sent to the rolling mill for rolling. A two-roll or four-roll rolling mill is used. The reduction of a single pass is 50%, and the rolling speed is 12 m / min. After rolling, it is air-cooled to room temperature.

[0094] Performance testing: The mechanical properties of the prepared aluminum / tantalum composite plate were tested. The average interfacial shear strength was 77.1 MPa and the average tensile strength was 491.3 MPa, which meet the strength requirements of space-based devices.

[0095] Comparative Example 1

[0096] A 2A12 / intermediate layer / Ta three-layer composite material of the prior art

[0097] (1) The 2A12 aluminum alloy, 1050 alloy and tantalum layer material are subjected to acid and alkali treatment to remove surface oil and other contaminants.

[0098] (2) Stack the three layers of materials together in the order of 2A12 aluminum alloy, 1050 alloy, and tantalum, and spot weld them together;

[0099] (3) The spot-welded materials are rolled and compounded by a cold rolling mill with a rolling deformation of 45%; rolling temperature: room temperature; rolling speed: 1m / min;

[0100] (4) The composite material is subjected to annealing heat treatment at 500℃ and kept at that temperature for 50 hours, and then leveled and trimmed.

[0101] The composite material prepared by this method underwent severe oxidation during the annealing heat treatment at 500℃ because the tantalum layer was not protected. After 50 hours, a large number of white oxide particles formed on the tantalum surface, leading to separation at the composite plate interface. (See attached image.) Figure 5 .

[0102] Comparative Example 2

[0103] Raw material preparation (same as in Example 1):

[0104]

[0105] Composite material preparation:

[0106] (1) Grind the surface of the above raw materials with a wire brush to remove the oxide film on the surface of the material, wipe the oil stains on the surface of the material with acetone and dry it, and clean the remaining debris on the surface of the material with compressed air.

[0107] (2) The raw materials after the above treatment are assembled into a blank in the order of 2A12 aluminum alloy layer, 1060 aluminum alloy foil, tantalum layer and 1060 aluminum alloy foil.

[0108] (3) The assembled billet is rolled at room temperature at a rolling speed of 1 m / min and a rolling reduction of 20% in one pass. After rolling, an aluminum / tantalum / aluminum composite component is obtained, and the tantalum is completely wrapped inside the aluminum foil.

[0109] (4) The cold-rolled composite component is subjected to stress-relieving annealing treatment. The heating temperature is 250℃ and the holding time is 1h. After the holding time is completed, it is quickly taken out and placed in the air to cool to room temperature.

[0110] The composite material prepared by this method exhibited large-area cracks at its edges, severely impacting the product's performance. (See attached image.) Figure 6 .

[0111] Comparative Example 3

[0112] Raw material preparation (same as in Example 2):

[0113]

[0114] Composite material preparation:

[0115] (1) Grind the surface of the above raw materials with a wire brush to remove the oxide film on the surface of the material, wipe the oil stains on the surface of the material with acetone and dry it, and clean the remaining debris on the surface of the material with compressed air.

[0116] (2) The raw materials after the above treatment are assembled into a blank in the order of 2A12 aluminum alloy layer, 1050 aluminum alloy foil, tantalum tungsten plate Ta2.5W and 1050 aluminum alloy foil.

[0117] (3) The above billet is sent to the heating furnace for heating at a temperature of 360°C and a holding time of 60 minutes. After heating, it is sent to the rolling mill for rolling. A two-roll or four-roll mill is used. The reduction of a single pass is 50%, and the rolling speed is 12 m / min. After rolling, it is air-cooled to room temperature.

[0118] The composite material prepared by this method, due to the absence of a cold rolling step and direct hot rolling, results in the 1-series alloy failing to protect the tantalum layer and thus failing to prevent oxidation of the tantalum layer, leading to the same problem as Comparative Example 1.

[0119] Comparative Example 4

[0120] Raw material preparation (same as in Example 1):

[0121]

[0122] Composite material preparation:

[0123] (1) Grind the surface of the above raw materials with a wire brush to remove the oxide film on the surface of the material, wipe the oil stains on the surface of the material with acetone and dry it, and clean the remaining debris on the surface of the material with compressed air.

[0124] (2) The two 1060 aluminum alloy foils after the above treatment are stacked on the upper and lower sides of the pure tantalum plate and assembled into a blank.

[0125] (3) The assembled billet is rolled at room temperature at a rolling speed of 1 m / min and a rolling reduction of 20% in one pass. After rolling, an aluminum / tantalum / aluminum composite component is obtained, and the tantalum is completely wrapped inside the aluminum foil.

[0126] (4) After polishing the surface of the above composite components according to the method in step (1), they are assembled with 2A12 aluminum alloy plate for a second time.

[0127] (5) The billet of the above-mentioned secondary billet is sent to the heating furnace for heating at a temperature of 350°C and a holding time of 60 minutes. After heating, it is sent to the rolling mill for rolling. A two-roll or four-roll rolling mill is used, the reduction of a single pass is 40%, the rolling speed is 10 m / min, and after rolling, it is air-cooled to room temperature.

[0128] The composite material prepared by this method, due to the lack of stress-relieving heat treatment, exhibits significant bending after hot rolling, requiring an additional straightening process, which increases production costs. Please see the appendix. Figure 7 .

[0129] 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 aluminum / tantalum composite material for radiation shielding, characterized by, The application relates to a 2A12 aluminum alloy composite plate and a preparation method thereof. The surfaces of 2A12 aluminum alloy plates, tantalum plates and 1-series aluminum alloy foils are respectively polished; The polished 1-series aluminum alloy foils are respectively arranged on the upper and lower sides of the tantalum plates to obtain an assembled blank; The assembled blank is subjected to cold rolling and stress relief annealing treatment to obtain a composite component; The composite component after the stress relief annealing treatment is subjected to secondary assembly with the 2A12 aluminum alloy plate; The secondary assembly is heated and subjected to hot rolling, and then air-cooled to room temperature to obtain a composite plate; The cold rolling temperature is 20-35 DEG C, the rolling speed is less than 1 m / min, one-pass rolling is adopted, and the deformation amount is controlled to be 20%-30%.

2. The production method according to claim 1, characterized by, The stress relief annealing treatment temperature is 240 DEG C-260 DEG C, and the holding time is 0.5-2 h; The holding time is completed, and then the composite component is rapidly taken out and air-cooled to room temperature.

3. The production method according to claim 2, characterized by, The heating temperature of the secondary assembly is 300 DEG C-400 DEG C, and the holding time is 20 min-60 min.

4. The method of claim 1, wherein, The hot rolling adopts a double-roller rolling mill or a four-roller rolling mill, the rolling speed is 5-20 m / min, and the single-pass rolling reduction is 30-50%.

5. An aluminum / tantalum composite material for radiation shielding produced by the production method according to any one of claims 1 to 4, characterized in that, The application relates to a laminated structure composite material. The laminated structure comprises a 2A12 aluminum alloy layer, a 1-series aluminum alloy layer, a tantalum layer and a 1-series aluminum alloy layer in sequence.

6. The composite material of claim 5, wherein, The thickness of the 2A12 aluminum alloy layer is 1.2-5.0 mm; The thickness of the tantalum layer is 0.3-1.2 mm; The thickness of the 1-series aluminum alloy layer is 0.02-0.05 mm.

7. The composite material of claim 6, wherein, The tantalum layer is pure tantalum or a tantalum-tungsten alloy.

8. The composite material of claim 7, wherein, The tantalum-tungsten alloy is Ta2.5W, Ta7.5W or Ta10W.

9. The composite material of claim 7, wherein, The total amount of inevitable impurities in the pure tantalum or the tantalum-tungsten alloy is less than 0.5%.

10. The composite material of claim 6, wherein, The 1-series aluminum alloy is 1050, 1060 or 1100.

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