CN115672988A - Aluminum/tantalum composite material for radiation shielding and preparation method thereof - Google Patents
Aluminum/tantalum composite material for radiation shielding and preparation method thereof Download PDFInfo
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Abstract
The application provides an aluminium/tantalum combined material for radiation shielding and a preparation method thereof, the combined material structure is a laminated structure and sequentially comprises a 2A12 aluminum alloy layer, A1 series aluminum alloy layer, a tantalum layer and A1 series aluminum alloy layer. The composite material is continuously compounded, and a supporting and connecting structure is not required to be additionally made, so that the protection part is compact in structure, and the weight of the protection structure is reduced. And a stable metallurgical bonding interface is prepared by adopting a rolling composite technology, so that the condition that the aluminum and tantalum composite interface is separated due to the aging of glue under the space thermal cycle is avoided.
Description
Technical Field
The technical field of nonferrous metal material processing, in particular to an aluminum/tantalum composite material for radiation shielding and a preparation method thereof.
Background
The aerospace technology is a national heavy instrument and is an important strategy for determining the future development of the country. Spacecraft are the core of aerospace technology. Because the satellite can encounter the radiation of various space charged particles, the space radiation resistance of the electronic device is an important factor influencing the development of medium and high orbit satellites and deep space exploration satellites in navigation, communication and the like. Currently, protection of electronic devices from the effects of total dose and displacement damage is primarily by passive shielding.
At present, 2A12 aluminum alloy is mainly adopted for shielding protection in the field, but the shielding protection efficiency is low, the protection effect can be improved only by increasing the thickness, the emission cost is increased due to the increase of the quality, and the radiation-resistant reinforcement requirements of middle and high orbit satellites and deep space exploration satellites in navigation, communication and the like in China are difficult to meet.
The development of the space environment electronic device protection structure technology based on the composite material can greatly save the satellite emission cost and the component use cost. Studies have shown that 30% less mass is occupied by the composite material than the elemental aluminum material at the same level of radiation dose protection. Composite materials must be used to realize low-quality, cost-effective and high-efficiency electronic device protection technologies. The energy loss mode of high-energy electrons in a substance mainly comprises ionization loss and radiation loss, shielding materials with different atomic numbers have different shielding effects on electrons according to a Bethe formula, the stopping power of target substances with unit area density on the electrons is approximately proportional to Z/A (Z is the atomic number, and A is relative atomic mass), meanwhile, the electrons are subjected to elastic scattering of atomic nuclei, deviate from the incident direction, equivalently, the shielding thickness is increased, and the elastic scattering is proportional to Z2/A. The low Z material has a higher Z/a value than the high Z material and therefore has a higher ionization energy loss for electrons, whereas the high Z material has a higher radiation energy loss for electrons due to scattering. Therefore, for the high-energy electron radiation protection, the high-Z material with a certain thickness, such as the metal aluminum-tantalum alloy, is arranged behind the low-Z material, so that the shielding effect of high-energy electrons can be greatly optimized.
However, the performance difference between the metal aluminum and the tantalum is significant, and particularly, the difference between the melting point and the hot working temperature range is large (the melting point of aluminum is 660 ℃, the melting point of tantalum is 2995 ℃, and the difference between the thermal expansion coefficients is about 4 times), so that great technical difficulties exist in the aspects of processing deformation and heat treatment. Meanwhile, due to the particularity of space application environment, the composite interface is cracked or layered due to the difference of thermal expansion coefficients of dissimilar metals caused by the alternating circulation of cold and heat.
At present, a series of research works are developed in the aspect of the preparation technology of the composite materials containing aluminum, tantalum and similar components in China. For example, a certain patent discloses a light high-strength Mg-Ta composite metal plate and a room-temperature rolling forming method thereof, wherein the Mg-Ta composite metal plate is prepared by adopting a room-temperature rolling process, low-temperature annealing treatment and high-temperature diffusion connection treatment are carried out in the middle of rolling passes, the heat treatment process is complicated, the edge cracks of the prepared composite plate are serious, and the composite material of the system is difficult to further process and form and has a certain distance from practical application because Mg has a close-packed hexagonal structure, the room-temperature plasticity is poor and the deformability is low. A certain patent discloses a preparation method of a shielding type magnesium-tantalum multilayer composite board, wherein after magnesium (magnesium alloy) and tantalum (tantalum alloy) are stacked and assembled, vacuumizing and sealing welding are needed in a sheath, and hot rolling forming is needed, so that the requirement on production equipment is high, and large-scale industrial production is not facilitated. A certain patent discloses a preparation method of a titanium/tantalum composite board and a product thereof, wherein inert atmosphere protection is performed in the heating and heat preservation processes, the production cost is high, the price of a titanium or titanium alloy material is high, the process performance is poor, further processing and welding are difficult, and the titanium/tantalum composite board is difficult to be applied in large scale in practice.
Disclosure of Invention
In order to solve the above-mentioned shortcomings in the art, the present application aims to provide an aluminum/tantalum composite material for radiation shielding and a method for preparing the same.
According to one aspect of the present application, there is provided a method of preparing an aluminum/tantalum composite for radiation shielding, comprising:
respectively polishing the surfaces of the 2A12 aluminum alloy plate, the tantalum plate and the 1-series aluminum alloy foil;
respectively placing the polished 1-series aluminum alloy foils on the upper side and the lower side of a tantalum plate to obtain an assembly blank;
performing cold rolling and stress relief annealing treatment on the assembly blank to obtain a composite component;
performing secondary assembly on the stress-relief annealed composite component and the 2A12 aluminum alloy plate;
and heating the secondary assembly, rolling, and air-cooling to room temperature to obtain the composite board.
According to some embodiments of the present application, the cold rolling temperature is 20-35 ℃ and the rolling speed is within 1m/min, and the deformation is controlled to be 20% -30% in one rolling.
According to some embodiments of the present application, the temperature of the stress relief annealing treatment is 240 ℃ to 260 ℃, and the holding time is 0.5 to 2 hours;
and taking out the blank quickly after the heat preservation time is finished, and performing secondary assembly after air cooling to room temperature.
According to some embodiments of the present application, the secondary assembly is heated at a temperature of 300 ℃ to 400 ℃ for a holding time of 20min to 60min.
According to some embodiments of the present application, the hot rolling is performed by a double-roll mill or a four-roll mill, the rolling speed is 5-20 m/min, and the reduction of the single-pass rolling is 30-50%.
According to another aspect of the present application, there is also provided an aluminum/tantalum composite for radiation shielding, which is a laminate structure composite;
the laminated structure comprises in sequence: 2A12 aluminum alloy layer, 1-series aluminum alloy layer, tantalum layer and 1-series aluminum alloy layer.
According to some embodiments of the present application, the 2a12 aluminum alloy layer has a thickness of 1.2 to 5.0mm;
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.
According to some embodiments of the present application, the tantalum layer is pure tantalum or a tantalum-tungsten alloy.
According to some embodiments of the present application, the tantalum-tungsten alloy is ta2.5w, ta7.5w, or Ta10W;
optionally, the total amount of unavoidable impurities in the pure tantalum or tantalum-tungsten alloy is less than 0.5%.
According to some embodiments of the present application, the 1-series aluminum alloy is brand 1050, 1060, or 1100.
Compared with the prior art, the application at least comprises the following beneficial effects:
according to an embodiment of the present application, an aluminum/tantalum composite material for radiation shielding is provided, which has a laminated structure and sequentially includes a 2a12 aluminum alloy layer, A1-series aluminum alloy layer, a tantalum layer, and A1-series aluminum alloy layer. Compared with the existing elemental metal material, the composite material has stable high-energy electron radiation resistance, low preparation cost, easy maintenance and better shielding effect than the elemental metal material, and can reduce the quality and cost of electronic devices.
Because the heating temperature of the plate blank exceeds 300 ℃ during hot rolling, an oxide layer formed by heating can generate adverse effect on interface combination in the rolling process, and the combination performance of the composite plate is greatly reduced. And the problem of edge cracks is easily caused due to the reduction of the plastic toughness and the increase of the brittleness of the material caused by the work hardening phenomenon of cold plastic deformation during cold rolling. Therefore, according to the composite material, the 1-series aluminum alloy is arranged on the two sides of the tantalum layer to serve as the protective layers, so that the tantalum layer can be prevented from being oxidized at the temperature of more than 250 ℃, and the problem of mechanical property reduction caused by cracks and the like in the rolling process of the tantalum layer can be solved.
The composite material is continuously compounded, and a supporting and connecting structure is not required to be additionally arranged, so that the protection part is compact in structure, and the weight of the protection structure is reduced; in addition, the stable metallurgical bonding interface is formed by adopting the rolling composite technology, so that the condition that the aluminum and tantalum composite interface is separated due to the aging of glue under the space thermal cycle is avoided.
The application firstly provides a cold rolling and hot rolling mode to compound the aluminum and the tantalum together, and successfully prepares the aluminum-tantalum composite material with excellent interface bonding performance. The problems of poor plate shape, easy occurrence of cracks, processing hardening and the like of a cold-rolled plate which is independently compounded by cold rolling are avoided, and the problem of oxidation of the heating surface of the tantalum or tantalum-tungsten plate is solved; not only remains enough deformation generated in the cold rolling step and can improve the bonding effect of 2A12 and Ta, but also realizes that the diffusion distance of the composite interface elements after hot rolling is larger, and the interface has better metallurgical bonding compared with the interface of a pure cold-rolled plate.
Drawings
FIG. 1 is a flow chart of a composite material preparation process according to an exemplary embodiment of the present application.
Fig. 2 is a schematic structural view of an aluminum/tantalum composite material for radiation shielding according to an exemplary embodiment of the present application.
Fig. 3 is a scanning electron micrograph of an exemplary embodiment of the present application.
Fig. 4 is a graph of interfacial diffusion width for an exemplary embodiment of the present application.
FIG. 5 is a photograph of a sample of comparative example 1 of the present application.
FIG. 6 is a photograph of a sample of comparative example 2 of the present application.
FIG. 7 is a photograph of a sample of comparative example 4 of the present application.
Detailed Description
The technical solutions of the present application will be described clearly and completely in conjunction with the embodiments of the present application, and it is obvious that the described embodiments are some, but not all, of the embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It is specifically noted that similar alternatives and modifications will be apparent to those skilled in the art for the present application, which are deemed to be included herein. It will be apparent to the skilled artisan that modifications, variations or appropriate alterations and combinations of the methods and applications described herein may be made to implement and apply the techniques of the present application without departing from the content, spirit and scope of the application. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments.
The raw materials or auxiliary materials used, and the reagents or instruments used, the manufacturers of which are not indicated, are all conventional products which can be obtained commercially.
The present application is described in detail below.
[ aluminum/tantalum composite for radiation shielding ] according to the present application
The composite material is a composite material with a laminated structure and sequentially comprises a 2A12 aluminum alloy layer, A1 series aluminum alloy layer, a tantalum layer and A1 series aluminum alloy layer.
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.
Further, the tantalum layer is pure tantalum or tantalum-tungsten alloy, the tantalum-tungsten alloy is Ta2.5W, ta7.5W or Ta10W, and the total amount of inevitable impurities in the pure tantalum or the tantalum-tungsten alloy is less than 0.5%.
Further, the 1-series aluminum alloy is under the brand number 1050, 1060 or 1100.
[ METHOD FOR PRODUCING AN ALUMINIUM/TANTALUM COMPOSITE MATERIAL FOR RADIATION SHIELDING ] OF THE INVENTION
The preparation method of the aluminum-tantalum composite material for radiation shielding comprises the following steps:
(1) Polishing and degreasing the surfaces of the 2A12 aluminum alloy plate, the tantalum plate and the 1-series aluminum alloy foil to remove an oxide layer, oil stains or other dirt on the surfaces;
(2) Respectively stacking two 1-series aluminum alloy foils on the upper side and the lower side of a tantalum plate, and assembling into a blank;
(3) Rolling the blank assembled in the step (2) at room temperature to obtain a part of composite component;
(4) Performing stress relief annealing treatment on the composite component obtained in the step (3);
(5) Performing secondary assembly on the heat-treated composite component and the 2A12 aluminum alloy plate;
(6) And (4) rolling the blanks subjected to secondary assembly after heating, and air-cooling to room temperature to obtain the composite board product.
And (2) removing oxide layers or other dirt on the surfaces of the 2A12 aluminum alloy plate, the tantalum plate and the 1-series aluminum alloy foil in the step (1) by adopting a traditional mechanical polishing mode, wherein the oil removing mode is drying after cleaning with alcohol or acetone, the surface of the plate blank is bright after polishing and oil removing, cracks, slag inclusion, scratches, oil spots and the like which are visible to naked eyes do not exist, and scraps generated by polishing cannot be remained on the surface.
Furthermore, the single-side length and the single-side width of the upper and lower 1-series aluminum alloy foils in the step (2) are 4-5 mm larger than those of the tantalum plate, and 1-2 mm larger than those of the tantalum plate.
Further, the rolling process in the step (3) is carried out at room temperature, the rolling speed is controlled within 1m/min, the rolling is carried out for one time, and the deformation is controlled to be 20-30%.
Since the deformation amount is large and the temperature is low in the cold rolling deformation process of step (3), large internal stress is generated. The internal stress not only can influence the strength and plasticity of the material, but also can cause the deformation of the material after subsequent processing due to the release of the internal stress. Therefore, stress relief annealing treatment is required for the composite component after the cold rolling.
Further, the temperature of the stress relief annealing treatment in the step (4) is 240-260 ℃, the heat preservation time is 0.5-2 h, the stress relief annealing treatment is quickly taken out after the heat preservation time is finished, and the stress relief annealing treatment is air-cooled to the room temperature.
Further, if the plate shape of the composite component obtained by room-temperature rolling in the step (3) has a bending phenomenon, straightening the composite component after stress relief annealing in the step (4) and discharging.
Further, in the step (5), the composite component after heat treatment is subjected to polishing degreasing treatment according to the relevant method in the step (1), so that the polished and degreased surface is bright, cracks, slag inclusions, scratches, oil spots and the like which are visible to naked eyes do not exist, and no scraps generated by polishing are left on the surface.
Further, in the step (6), the heating temperature of the plate blank is 300-400 ℃, and the heat preservation time is 20-60 min;
optionally, in the step (6), the heating temperature of the plate blank is 350 ℃, and the holding time is 60min.
If the heating temperature is too low, the deformation resistance is increased, and problems such as poor plate shape, cracks and the like can occur. If the temperature is too high, the crystal grains are too coarse, the product performance is affected, and if the temperature is too high, overburning, namely some low-melting-point eutectic crystals or crystal boundaries are melted, and the product is scrapped.
Further, the hot rolling in the step (6) adopts a double-roller mill or a four-roller mill, the rolling reduction of single-pass rolling is 30-50%, and the rolling speed is controlled at 5-20 m/min;
optionally, the single pass reduction is 40% and the rolling speed is 10m/min.
The present application will be described in detail with reference to specific examples.
The chemical compositions of the raw materials 2A12 aluminum alloy material and 1060 pure aluminum wrapping layer used in the embodiment of the application are in accordance with the regulations of the national standard GB/T3190-2020; the chemical composition of the pure tantalum is required to meet the specification in YS/T751-2011; the chemical composition of tantalum tungsten (Ta2.5W) should meet the specification in YS/T751-2011.
Example 1
Preparing raw materials:
preparing a composite material:
(1) And (3) polishing the surface of the raw material by using a steel wire brush to remove an oxide film on the surface of the material, wiping oil stains on the surface of the material by using acetone, drying, and cleaning up the residual scraps on the surface of the material by using compressed air.
(2) The two pieces of 1060 aluminum alloy foils after the above treatment are respectively stacked on the upper and lower sides of the pure tantalum plate, and assembled into a blank.
(3) And rolling the assembled blank at room temperature at the rolling speed of 1m/min and the rolling reduction of 20 percent in one step to obtain a part of aluminum/tantalum/aluminum composite component, wherein the tantalum is completely wrapped in the aluminum foil.
(4) And (3) performing stress relief annealing treatment on the cold-rolled composite component, wherein the heating temperature is 250 ℃, the heat preservation time is 1h, and after the heat preservation time is finished, the cold-rolled composite component is quickly taken out and placed in the air to be cooled to the room temperature.
(5) And (2) polishing the surface of the heat-treated composite component according to the method in the step (1), and then performing secondary assembly with a 2A12 aluminum alloy plate.
(6) Feeding the blanks of the secondary assembly into a heating furnace for heating, wherein the heating temperature is 350 ℃, the heat preservation time is 60min, and feeding the blanks into a rolling mill for rolling after the heating is finished; adopting a double-roller mill or a four-roller mill, rolling the steel plate at a rolling speed of 10m/min with the rolling reduction of 40% in single pass, and cooling the steel plate to room temperature after rolling.
And (3) performance testing: the prepared aluminum/tantalum composite board is subjected to mechanical property test, the average value of the interface shear strength is 76.0MPa, the average value of the tensile strength is 482.5MPa, and the strength requirement of the satellite device can be met.
Example 2
Preparing raw materials:
preparing a composite material:
(1) And (3) polishing the surface of the raw material by using a steel wire brush to remove an oxide film on the surface of the material, wiping oil stains on the surface of the material by using acetone, drying, and cleaning up the residual scraps on the surface of the material by using compressed air.
(2) And respectively stacking the two processed 1050 aluminum alloy foils on the upper side and the lower side of the tantalum-tungsten plate, and assembling into a blank.
(3) And rolling the assembled blank at room temperature at the rolling speed of 0.8m/min and the rolling reduction of 25%, rolling for one time to obtain an aluminum/tantalum/aluminum composite component, wherein the tantalum is completely wrapped in the aluminum foil.
(4) And (3) performing stress relief annealing treatment on the cold-rolled composite component, wherein the heating temperature is 255 ℃, the heat preservation time is 1.2h, and after the heat preservation time is finished, the cold-rolled composite component is quickly taken out and placed in the air to be cooled to the room temperature.
(5) And (2) polishing the surface of the heat-treated composite component according to the method in the step (1), and then performing secondary assembly with a 2A12 aluminum alloy plate.
(6) And (3) conveying the blanks of the secondary assembly into a heating furnace for heating, wherein the heating temperature is 360 ℃, the heat preservation time is 60min, conveying the blanks into a rolling mill for rolling after the heating is finished, adopting a double-roller rolling mill or a four-roller rolling mill, rolling the blanks in a single-pass rolling way at the rolling speed of 12m/min, and cooling the blanks in air to room temperature after the rolling.
And (3) performance testing: the prepared aluminum/tantalum composite board is subjected to mechanical property test, the average value of the interface shear strength is 77.1MPa, the average value of the tensile strength is 491.3MPa, and the strength requirement of the star device can be met.
Comparative example 1
(1) Respectively carrying out acid-base treatment on the 2A12 aluminum alloy, the 1050 alloy and the tantalum layer material to remove surface oil stains and the like;
(2) Stacking the three layers of materials according to the sequence of 2A12 aluminum alloy, 1050 alloy and tantalum, and fixing by spot welding;
(3) Rolling and compounding the spot-welded material through a cold rolling mill, wherein the rolling deformation is 45%; rolling temperature: room temperature; rolling speed: 1m/min;
(4) And (3) annealing and heat treating the compounded material at 500 ℃, preserving heat for 50h, and then flattening and trimming.
The composite material prepared by the method is not protected by the tantalum layer, serious oxidation occurs in the annealing heat treatment process at 500 ℃, and a large amount of white oxide particles are formed on the surface of tantalum after 50 hours, so that the interface of the composite plate is separated, and please refer to the attached figure 5.
Comparative example 2
Raw material preparation (same as example 1):
preparing a composite material:
(1) And (3) polishing the surface of the raw material by using a steel wire brush to remove an oxide film on the surface of the material, wiping oil stains on the surface of the material by using acetone, drying, and cleaning up the residual scraps on the surface of the material by using compressed air.
(2) And (3) sequentially assembling the processed raw materials into a blank according to the sequence of the 2A12 aluminum alloy layer, the 1060 aluminum alloy foil, the tantalum layer and the 1060 aluminum alloy foil.
(3) And rolling the assembled blank at room temperature at the rolling speed of 1m/min and the rolling reduction of 20 percent in one step to obtain a part of aluminum/tantalum/aluminum composite component, wherein the tantalum is completely wrapped in the aluminum foil.
(4) And (3) performing stress relief annealing treatment on the cold-rolled composite component, wherein the heating temperature is 250 ℃, the heat preservation time is 1h, and after the heat preservation time is finished, the cold-rolled composite component is quickly taken out and placed in the air to be cooled to the room temperature.
The composite material prepared by the method has large-area cracks on the edge, and has serious influence on the service performance of the product, see the attached figure 6.
Comparative example 3
Raw material preparation (same as example 2):
preparing a composite material:
(1) And (3) polishing the surface of the raw material by using a steel wire brush to remove an oxide film on the surface of the material, wiping oil stains on the surface of the material by using acetone, drying, and cleaning up the residual scraps on the surface of the material by using compressed air.
(2) And (3) sequentially assembling the treated raw materials into a blank according to the sequence of the 2A12 aluminum alloy layer, the 1050 aluminum alloy foil, the Ta2.5W tantalum-tungsten plate and the 1050 aluminum alloy foil.
(3) And (2) heating the blank in a heating furnace at 360 ℃, keeping the temperature for 60min, rolling in a rolling mill after heating, rolling in a double-roller rolling mill or a four-roller rolling mill at the rolling speed of 12m/min with the rolling reduction of 50% in single-pass rolling, and cooling in air to room temperature after rolling.
The composite material prepared by the method has no cold rolling step, and the direct hot rolling results in that the 1-series alloy does not protect the tantalum layer, and the oxidation of the tantalum layer cannot be avoided, so the composite material has the same problem as that of the comparative example 1.
Comparative example 4
Raw material preparation (same as example 1):
preparing a composite material:
(1) And polishing the surface of the raw material by using a steel wire brush to remove an oxidation film on the surface of the material, wiping oil stains on the surface of the material by using acetone, drying, and cleaning the residual scraps on the surface of the material by using compressed air.
(2) And (3) respectively stacking the two treated 1060 aluminum alloy foils on the upper side and the lower side of the pure tantalum plate, and assembling into a blank.
(3) And rolling the assembled blank at room temperature at the rolling speed of 1m/min and the rolling reduction of 20 percent in one step to obtain an aluminum/tantalum/aluminum composite component, wherein the tantalum is completely wrapped in the aluminum foil.
(4) And (2) polishing the surfaces of the composite components according to the method in the step (1), and then performing secondary assembly with a 2A12 aluminum alloy plate.
(5) The blanks of the secondary assembly are sent to a heating furnace for heating, the heating temperature is 350 ℃, the heat preservation time is 60min, and the blanks are sent to a rolling mill for rolling after the heating is finished; adopting a double-roller mill or a four-roller mill, rolling the steel plate at a rolling speed of 10m/min with the rolling reduction of 40% in single pass, and cooling the steel plate to room temperature after rolling.
The composite material prepared by the method is not subjected to stress relief heat treatment, the plate shape is greatly bent after hot rolling, a straightening process is required to be added, and the production cost is increased, see the attached figure 7.
The above description of the embodiments is only intended to help understand the method of the present application and its core ideas. It should be noted that, for those skilled in the art, it is possible to make several improvements and modifications to the present application without departing from the principle of the present application, and such improvements and modifications also fall within the scope of the claims of the present application.
Claims (10)
1. A method for preparing an aluminum/tantalum composite material for radiation shielding is characterized by comprising the following steps:
polishing the surfaces of the 2A12 aluminum alloy plate, the tantalum plate and the 1-series aluminum alloy foil respectively;
respectively placing the polished 1-series aluminum alloy foils on the upper side and the lower side of a tantalum plate to obtain an assembly blank;
performing cold rolling and stress relief annealing treatment on the assembled blank to obtain a composite component;
performing secondary assembly on the stress-relief annealed composite component and the 2A12 aluminum alloy plate;
and heating the secondary assembly, carrying out hot rolling, and carrying out air cooling to room temperature to obtain the composite plate.
2. The method according to claim 1, wherein the cold rolling temperature is 20-35 ℃, the rolling speed is within 1m/min, one-pass rolling is carried out, and the deformation is controlled to be 20-30%.
3. The preparation method according to claim 1, wherein the stress relief annealing treatment temperature is 240-260 ℃, and the holding time is 0.5-2 h;
and taking out quickly after the heat preservation time is finished, and cooling to room temperature in air.
4. The preparation method according to claim 3, wherein the heating temperature of the secondary assembly is 300-400 ℃, and the holding time is 20-60 min.
5. The production method according to claim 1, wherein the hot rolling is performed by a double-roll mill or a four-roll mill, the rolling speed is 5 to 20m/min, and the reduction of the single-pass rolling is 30 to 50%.
6. An aluminum/tantalum composite material for radiation shielding is characterized by being a composite material with a laminated structure;
the laminated structure comprises in sequence: 2A12 aluminum alloy layer, 1-series aluminum alloy layer, tantalum layer and 1-series aluminum alloy layer.
7. The composite material of claim 6, wherein the 2a12 aluminum alloy layer has a thickness of 1.2 to 5.0mm;
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.
8. The composite material of claim 7, wherein the tantalum layer is pure tantalum or a tantalum tungsten alloy.
9. The composite material of claim 8, wherein the tantalum-tungsten alloy is Ta2.5W, ta7.5W, or Ta10W;
preferably, the total amount of unavoidable impurities in the pure tantalum or tantalum-tungsten alloy is less than 0.5%.
10. The composite of claim 7, wherein the 1-series aluminum alloy is brand 1050, 1060, or 1100.
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