CN116287907A - Aluminum alloy for spaceflight and preparation method thereof - Google Patents
Aluminum alloy for spaceflight and preparation method thereof Download PDFInfo
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- CN116287907A CN116287907A CN202310314369.9A CN202310314369A CN116287907A CN 116287907 A CN116287907 A CN 116287907A CN 202310314369 A CN202310314369 A CN 202310314369A CN 116287907 A CN116287907 A CN 116287907A
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
Abstract
The invention provides an aluminum alloy for spaceflight and a preparation method thereof, wherein the aluminum alloy comprises the following components in percentage by mass: 2 to 2.6 percent of Cu, 1.9 to 2.6 percent of Mg, 5.7 to 6.7 percent of Zn, 0.05 to 0.12 percent of Fe, 0.04 to 0.09 percent of Mn, 0.05 to 0.11 percent of Sr, 0.06 to 0.16 percent of Si, less than or equal to 0.03 percent of Cr, less than or equal to 0.08 percent of Ti, 0.04 to 0.11 percent of Zr, 0.02 to 0.05 percent of Sc and the balance of Al, wherein the mass ratio of Fe/Mn is 0.9 to 1.4. The invention produces the novel aluminum alloy of the traditional aluminum-magnesium-zinc-copper-aluminum alloy with excellent overall performance through a reasonable process flow matched with the unique chemical component proportion, has excellent mechanical property, corrosion resistance and high temperature resistance, and can be applied to various fields of aerospace and the like.
Description
Technical Field
The invention belongs to the technical field of aluminum alloy materials, and particularly relates to an aluminum alloy for aerospace and a preparation method thereof.
Background
The aluminum alloy is an alloy based on aluminum and added with a certain amount of other alloying elements, and is one of light metal materials. The aluminum alloy has good casting performance and plastic processing performance, can be used as a structural material, and is widely applied to the fields of aerospace and aviation. The aluminum alloy for aerospace refers to an aluminum alloy which can be used in the aerospace field, and the aluminum alloy is one of main structural materials in the aerospace industry.
With the rapid development of aerospace industry, aluminum alloy with excellent comprehensive performance becomes a main structural material of an aircraft and a spacecraft, and the requirement on the aluminum alloy is higher and higher. The existing 7000 series aluminum alloy belongs to super-hard aluminum alloy, has good wear resistance and good weldability, but has poor corrosion resistance. Along with the improvement of the requirements of the aerospace industry on corrosion resistance, mechanical properties and the like of aluminum alloy, in order to meet the requirements of design and material selection of aerospace users, the comprehensive performance of the aluminum-magnesium-zinc-copper-aluminum alloy is further improved on the basis of the traditional aviation series to be a necessary requirement, so that the novel aluminum alloy for aerospace is developed, and the novel aluminum alloy for aerospace has important significance.
Disclosure of Invention
The invention aims to provide an aluminum alloy for spaceflight and a preparation method thereof, and the mechanical strength, high temperature resistance, corrosion resistance and the like of the aluminum alloy are improved by adding various elements, adjusting the content of components and optimizing the production process on the basis of the traditional aluminum alloy.
In order to achieve the aim, the invention provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: 2 to 2.6 percent of Cu, 1.9 to 2.6 percent of Mg, 5.7 to 6.7 percent of Zn, 0.05 to 0.12 percent of Fe, 0.04 to 0.09 percent of Mn, 0.05 to 0.11 percent of Sr, 0.06 to 0.16 percent of Si, less than or equal to 0.03 percent of Cr, less than or equal to 0.08 percent of Ti, 0.04 to 0.11 percent of Zr, 0.02 to 0.05 percent of Sc and the balance of Al, wherein the mass ratio of Fe/Mn is 0.9 to 1.4.
Further, the mass ratio of Fe/Mn is 1.0 to 1.1.
The invention obviously improves the tensile strength by controlling the range of Fe/Mn mass ratio, and the inventor considers that the flaky beta phase in the aluminum alloy is converted into the Chinese character alpha phase under the condition, so that the mechanical property of the aluminum alloy can be improved. The invention utilizes the synergistic effect among the elements, and the corrosion resistance of the alloy is obviously improved under the condition of not reducing the mechanical property of the aluminum alloy.
Further, the composition comprises the following components in percentage by mass: 2.2 to 2.4 portions of Cu, 2.1 to 2.3 portions of Mg, 6.0 to 6.3 portions of Zn, 0.07 to 0.10 portion of Fe, 0.05 to 0.07 portion of Mn, 0.07 to 0.10 portion of Sr, 0.08 to 0.12 portion of Si, 0.01 to 0.03 portion of Cr, 0.06 to 0.08 portion of Ti, 0.06 to 0.08 portion of Zr, 0.03 to 0.04 portion of Sc and the balance of Al.
The invention can improve the strength and heat resistance of the aluminum alloy by adding Si and Ti elements, reasonably control the contents of Mg, si, cu and other elements, and ensure that the alloy achieves an optimal balance between the strength and the forming performance. According to the invention, the Sc element is added to play roles in grain refinement, recrystallization inhibition, solid solution strengthening and the like, so that the mechanical property, damage tolerance and corrosion resistance of the aluminum alloy are obviously improved. The content of Zr and Sc elements in the alloy is regulated and controlled, so that the supercooling degree of components during the solidification of the aluminum alloy is improved, the solidification nucleation rate is improved, the morphology of crystal grains is refined, and the effect of inhibiting hot cracks can be achieved.
The second aspect of the invention provides a preparation method of the aluminum alloy for aerospace, which comprises the following steps:
(1) Melting the aluminum alloy composition of claim 1 into a melt, casting the melt to form an aluminum alloy ingot;
(2) The cast ingot is sequentially subjected to three-stage homogenization annealing treatment, hot rolling treatment, solution treatment and aging heat treatment to obtain the aluminum alloy.
Further, the three-stage homogenizing annealing treatment specifically comprises the following steps: the aluminum alloy after casting is heated to 370-400 ℃ from room temperature for 10-13 h, then heated to 500-530 ℃ for 15-18 h, then heated to 550-570 ℃ for 20-25 h, and then cooled to room temperature.
Further, the three-stage homogenizing annealing specifically comprises: the aluminum alloy after casting is heated from room temperature to 370-400 ℃ for 10-13 h at the heating rate of 10-15 ℃/h, then heated to 500-530 ℃ at the heating rate of 20-25 ℃/h for 15-18 h, heated to 550-570 ℃ at the heating rate of 30-35 ℃/h for 20-25 h, and then cooled to room temperature at the cooling rate of 30-40 ℃/h.
Further, the temperature of the solution treatment is 500-550 ℃, the time is 10-15 min, and the solution treatment is quenched to room temperature by using water.
Further, the aging heat treatment specifically comprises: heating the sample quenched to room temperature in a heating furnace to 100-120 ℃, preserving heat for 35-45 min, then heating to 200-220 ℃ and preserving heat for 35-45 min; quenching with water to room temperature; continuously transferring the sample into an aging furnace for pre-aging within 10-20 min, wherein the pre-aging temperature is 90-130 ℃, and the pre-aging heat preservation time is 10-15 h.
Further, heating the sample water quenched to room temperature to 100-120 ℃ in a heating furnace at a heating rate of 10-15 ℃/s, preserving heat for 35-45 min, heating to 200-220 ℃ at a heating rate of 20-30 ℃/s, and preserving heat for 35-45 min; quenching with water to room temperature; transferring the sample into an aging furnace for pre-aging within 10-20 min, wherein the pre-aging temperature is 90-130 ℃, and the pre-aging heat preservation time is 10-15 h.
In the invention, dendrite segregation and grain boundary segregation exist in the aluminum alloy ingot, and unbalanced phases of Zn, mg and Cu and phases generated by Fe and Mn are distributed in a continuous net shape along the grain boundary. The inventor eliminates dendrite structure by optimizing preparation method, and the unbalanced phase on grain boundary is basically completely dissolved back into matrix, and ingot defect is eliminated. Through a series of treatment steps of the preparation method, fine and uniform precipitation and coarsening of grain boundaries exist in crystals after aging heat treatment, and the obtained aluminum alloy has high strength and good corrosion resistance.
The invention further provides an application of the aluminum alloy in preparing space structure devices.
Compared with the prior art, the invention has the advantages that: the novel aluminum alloy with excellent overall performance of the traditional aluminum-magnesium-zinc-copper-aluminum alloy is produced through unique chemical component proportion and reasonable process flow, has excellent mechanical property, corrosion resistance and high temperature resistance, and can be applied to various fields of aerospace and the like.
Detailed Description
In order to fully disclose the technical contents of the present invention, the following description is made in detail with reference to the preferred embodiments. It should be emphasized that the technical solutions disclosed in the present invention are only the best embodiments of the present invention, but not all, and that the technical solutions that are obvious to those skilled in the art in combination with the present invention and the prior art still fall within the protection scope of the present invention.
Example 1
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu 2.4,Mg 2.2,Zn6.1,Fe 0.07,Mn 0.07,Sr 0.09,Si 0.09,Cr 0.02,Ti 0.07,Zr 0.07,Sc 0.04,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following specific steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) The aluminum alloy after casting is heated from room temperature to 380 ℃ for 12 hours at the heating rate of 12 ℃/h, then heated to 520 ℃ for 16 hours at the heating rate of 23 ℃/h, then heated to 560 ℃ for 23 hours at the heating rate of 32 ℃/h, and then cooled to room temperature along with the furnace at the cooling rate of 35 ℃/h. The method comprises the steps of hot rolling treatment and solution treatment, wherein the temperature of the solution treatment is 530 ℃, the time is 12min, and the solution treatment is quenched to room temperature by using water. Heating the sample quenched to room temperature in a heating furnace to 110 ℃ at a heating rate of 13 ℃/s, preserving heat for 40min, and then heating to 210 ℃ at a heating rate of 25 ℃/s, preserving heat for 40min; quenching with water to room temperature; and transferring the sample into an aging furnace for pre-aging within 15min, wherein the pre-aging temperature is 120 ℃, and the pre-aging heat preservation time is 13h, so that the aluminum alloy is obtained.
Example 2
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu2,Mg 1.9,Zn 5.7,Fe 0.05,Mn 0.04,Sr 0.05,Si 0.06,Cr 0.01,Ti 0.01,Zr 0.04,Sc 0.02,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following specific steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) The aluminum alloy after casting is heated from room temperature to 380 ℃ for 12 hours at the heating rate of 12 ℃/h, then heated to 520 ℃ for 16 hours at the heating rate of 23 ℃/h, then heated to 560 ℃ for 23 hours at the heating rate of 32 ℃/h, and then cooled to room temperature along with the furnace at the cooling rate of 35 ℃/h. The method comprises the steps of hot rolling treatment and solution treatment, wherein the temperature of the solution treatment is 530 ℃, the time is 12min, and the solution treatment is quenched to room temperature by using water. Heating the sample quenched to room temperature in a heating furnace to 110 ℃ at a heating rate of 13 ℃/s, preserving heat for 40min, and then heating to 210 ℃ at a heating rate of 20 ℃/s, preserving heat for 40min; quenching with water to room temperature; and transferring the sample into an aging furnace for pre-aging within 15min, wherein the pre-aging temperature is 120 ℃, and the pre-aging heat preservation time is 13h, so that the aluminum alloy is obtained.
Example 3
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu 2.4,Mg 2.2,Zn6.1,Fe 0.05,Mn 0.09,Sr 0.09,Si 0.09,Cr 0.02,Ti 0.07,Zr 0.07,Sc 0.04,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following specific steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) The aluminum alloy after casting is heated from room temperature to 380 ℃ for 12 hours at the heating rate of 12 ℃/h, then heated to 520 ℃ for 16 hours at the heating rate of 23 ℃/h, then heated to 560 ℃ for 23 hours at the heating rate of 32 ℃/h, and then cooled to room temperature along with the furnace at the cooling rate of 35 ℃/h. The method comprises the steps of hot rolling treatment and solution treatment, wherein the temperature of the solution treatment is 530 ℃, the time is 12min, and the solution treatment is quenched to room temperature by using water. Heating the sample quenched to room temperature in a heating furnace to 110 ℃ at a heating rate of 13 ℃/s, preserving heat for 40min, and then heating to 210 ℃ at a heating rate of 20 ℃/s, preserving heat for 40min; quenching with water to room temperature; and transferring the sample into an aging furnace for pre-aging within 15min, wherein the pre-aging temperature is 120 ℃, and the pre-aging heat preservation time is 13h, so that the aluminum alloy is obtained.
Example 4
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu 2.4,Mg 2.2,Zn6.1,Fe 0.07,Mn 0.07,Sr 0.09,Si 0.09,Cr 0.02,Ti 0.07,Zr 0.07,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following specific steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) The aluminum alloy after casting is heated from room temperature to 380 ℃ for 12 hours at the heating rate of 12 ℃/h, then heated to 520 ℃ for 16 hours at the heating rate of 23 ℃/h, then heated to 560 ℃ for 23 hours at the heating rate of 32 ℃/h, and then cooled to room temperature along with the furnace at the cooling rate of 35 ℃/h. The method comprises the steps of hot rolling treatment and solution treatment, wherein the temperature of the solution treatment is 530 ℃, the time is 12min, and the solution treatment is quenched to room temperature by using water. Heating the sample quenched to room temperature in a heating furnace to 110 ℃ at a heating rate of 13 ℃/s, preserving heat for 40min, and then heating to 210 ℃ at a heating rate of 20 ℃/s, preserving heat for 40min; quenching with water to room temperature; and transferring the sample into an aging furnace for pre-aging within 15min, wherein the pre-aging temperature is 120 ℃, and the pre-aging heat preservation time is 13h, so that the aluminum alloy is obtained.
Example 5
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu 2.4,Mg 2.2,Zn6.1,Fe 0.07,Mn 0.07,Sr 0.09,Si 0.09,Cr 0.02,Ti 0.07,Zr 0.2,Sc 0.01,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following specific steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) The aluminum alloy after casting is heated from room temperature to 380 ℃ for 12 hours at the heating rate of 12 ℃/h, then heated to 520 ℃ for 16 hours at the heating rate of 23 ℃/h, then heated to 560 ℃ for 23 hours at the heating rate of 32 ℃/h, and then cooled to room temperature along with the furnace at the cooling rate of 35 ℃/h. The method comprises the steps of hot rolling treatment and solution treatment, wherein the temperature of the solution treatment is 530 ℃, the time is 12min, and the solution treatment is quenched to room temperature by using water. Heating the sample quenched to room temperature in a heating furnace to 110 ℃ at a heating rate of 13 ℃/s, preserving heat for 40min, and then heating to 210 ℃ at a heating rate of 20 ℃/s, preserving heat for 40min; quenching with water to room temperature; and transferring the sample into an aging furnace for pre-aging within 15min, wherein the pre-aging temperature is 120 ℃, and the pre-aging heat preservation time is 13h, so that the aluminum alloy is obtained.
Example 6
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu 2.4,Mg 2.2,Zn6.1,Fe 0.07,Mn 0.07,Si 0.09,Cr 0.02,Zr 0.07,Sc 0.04,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following specific steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) The aluminum alloy after casting is heated from room temperature to 380 ℃ for 12 hours at the heating rate of 12 ℃/h, then heated to 520 ℃ for 16 hours at the heating rate of 23 ℃/h, then heated to 560 ℃ for 23 hours at the heating rate of 32 ℃/h, and then cooled to room temperature along with the furnace at the cooling rate of 35 ℃/h. The method comprises the steps of hot rolling treatment and solution treatment, wherein the temperature of the solution treatment is 530 ℃, the time is 12min, and the solution treatment is quenched to room temperature by using water. Heating the sample quenched to room temperature in a heating furnace to 110 ℃ at a heating rate of 13 ℃/s, preserving heat for 40min, and then heating to 210 ℃ at a heating rate of 20 ℃/s, preserving heat for 40min; quenching with water to room temperature; and transferring the sample into an aging furnace for pre-aging within 15min, wherein the pre-aging temperature is 120 ℃, and the pre-aging heat preservation time is 13h, so that the aluminum alloy is obtained.
Example 7
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu 3,Mg 2.3,Zn 5.5,Fe 0.04,Mn 0.06,Sr 0.06,Si 0.08,Cr 0.03,Ti 0.07,Zr 0.08,Sc 0.06,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following specific steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) The aluminum alloy after casting is heated from room temperature to 380 ℃ for 12 hours at the heating rate of 12 ℃/h, then heated to 520 ℃ for 16 hours at the heating rate of 23 ℃/h, then heated to 560 ℃ for 23 hours at the heating rate of 32 ℃/h, and then cooled to room temperature along with the furnace at the cooling rate of 35 ℃/h. The method comprises the steps of hot rolling treatment and solution treatment, wherein the temperature of the solution treatment is 530 ℃, the time is 12min, and the solution treatment is quenched to room temperature by using water. Heating the sample quenched to room temperature in a heating furnace to 110 ℃ at a heating rate of 13 ℃/s, preserving heat for 40min, and then heating to 210 ℃ at a heating rate of 20 ℃/s, preserving heat for 40min; quenching with water to room temperature; and transferring the sample into an aging furnace for pre-aging within 15min, wherein the pre-aging temperature is 120 ℃, and the pre-aging heat preservation time is 13h, so that the aluminum alloy is obtained.
Example 8
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu 2.4,Mg 2.2,Zn6.1,Fe 0.07,Mn 0.07,Sr 0.09,Si 0.09,Cr 0.02,Ti 0.07,Zr 0.07,Sc 0.04,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following specific steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) And (3) heating the aluminum alloy after casting to 560 ℃ at a heating rate of 32 ℃/h, preserving heat for 40h, and then cooling to room temperature along with a furnace at a cooling rate of 35 ℃/h. The method comprises the steps of hot rolling treatment and solution treatment, wherein the temperature of the solution treatment is 530 ℃, the time is 12min, and the solution treatment is quenched to room temperature by using water. Heating the sample quenched to room temperature in a heating furnace to 110 ℃ at a heating rate of 13 ℃/s, preserving heat for 40min, and then heating to 210 ℃ at a heating rate of 20 ℃/s, preserving heat for 40min; quenching with water to room temperature; and transferring the sample into an aging furnace for pre-aging within 15min, wherein the pre-aging temperature is 120 ℃, and the pre-aging heat preservation time is 13h, so that the aluminum alloy is obtained.
Example 9
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu 2.4,Mg 2.2,Zn6.1,Fe 0.07,Mn 0.07,Sr 0.09,Si 0.09,Cr 0.02,Ti 0.07,Zr 0.07,Sc 0.04,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following specific steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) The aluminum alloy after casting is heated from room temperature to 380 ℃ for 12 hours at the heating rate of 12 ℃/h, then heated to 520 ℃ for 16 hours at the heating rate of 23 ℃/h, then heated to 560 ℃ for 23 hours at the heating rate of 32 ℃/h, and then cooled to room temperature along with the furnace at the cooling rate of 35 ℃/h. The method comprises the steps of hot rolling treatment and solution treatment, wherein the temperature of the solution treatment is 400 ℃, the time is 15min, and the solution treatment is quenched to room temperature by using water. Heating the sample quenched to room temperature in a heating furnace to 110 ℃ at a heating rate of 13 ℃/s, preserving heat for 40min, and then heating to 210 ℃ at a heating rate of 20 ℃/s, preserving heat for 40min; quenching with water to room temperature; and transferring the sample into an aging furnace for pre-aging within 15min, wherein the pre-aging temperature is 120 ℃, and the pre-aging heat preservation time is 13h, so that the aluminum alloy is obtained.
Example 10
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu 2.4,Mg 2.2,Zn6.1,Fe 0.07,Mn 0.07,Sr 0.09,Si 0.09,Cr 0.02,Ti 0.07,Zr 0.07,Sc 0.04,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following specific steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) The aluminum alloy after casting is heated from room temperature to 380 ℃ for 12 hours at the heating rate of 12 ℃/h, then heated to 520 ℃ for 16 hours at the heating rate of 23 ℃/h, then heated to 560 ℃ for 23 hours at the heating rate of 32 ℃/h, and then cooled to room temperature along with the furnace at the cooling rate of 35 ℃/h. The method comprises the steps of hot rolling treatment and solution treatment, wherein the temperature of the solution treatment is 530 ℃, the time is 12min, and the solution treatment is quenched to room temperature by using water. And transferring the sample which is quenched to room temperature in 15min into an aging furnace for pre-aging, wherein the pre-aging temperature is 120 ℃, and the pre-aging heat preservation time is 13h, so that the aluminum alloy is obtained.
Example 11
The embodiment provides an aluminum alloy for spaceflight, which comprises the following components in percentage by mass: cu 2.4,Mg 2.2,Zn6.1,Fe 0.07,Mn 0.07,Sr 0.09,Si 0.09,Cr 0.02,Ti 0.07,Zr 0.07,Sc 0.04,Al balance.
The preparation method of the aluminum alloy for aerospace comprises the following steps:
(1) Smelting the aluminum alloy components into a melt, and casting the melt to form an aluminum alloy cast ingot;
(2) The ingot is sequentially subjected to homogenizing annealing treatment, hot rolling treatment, solid solution treatment and aging heat treatment to obtain the aluminum alloy.
The homogenizing annealing condition is that the temperature of the aluminum alloy after casting rises from room temperature to 490 ℃ at the heating rate of 35 ℃/h, and the heat preservation is continued for 25h. The temperature of the solution treatment is 520 ℃ and the time is 12min. The aging heat treatment specifically comprises the following steps: the sample was transferred to an aging oven for pre-aging at 110℃for 13h in 15 min. The solution treatment is followed by quenching to room temperature using water.
Performance testing
The aluminum alloy prepared in the example is subjected to mechanical property stretching, fracture toughness, peeling corrosion resistance test and high temperature resistance test according to GBT-228.1-2010 and GB/T22639-2022, and the results are shown in Table 1.
TABLE 1 Performance test results
As is clear from examples 1 to 7, the aluminum alloy obtained by the specific chemical composition ratio of the present invention is more excellent in the comprehensive properties. As is clear from examples 1 and 8 to 11 of the invention, the strength, high temperature resistance and good corrosion resistance of the obtained aluminum alloy are high by three-stage homogenization annealing treatment, hot rolling treatment and solution treatment, then by stage heat preservation, immediately quenching, and fully dissolving the alloy to form supersaturated solid solution, so that fine and uniform precipitation exists in crystals during aging heat treatment, and grain boundaries are coarsened. The specific chemical composition and the preparation process of the aluminum alloy provided by the invention play a role in synergy, so that the corrosion resistance of the aluminum alloy is improved, the obtained aluminum alloy plate is high in strength and good in high temperature resistance, and the aluminum alloy with more excellent overall performance is obtained.
While the invention has been described in detail in connection with specific preferred embodiments thereof, it is not to be construed as limited thereto, but rather as a result of a simple deduction or substitution by a person having ordinary skill in the art to which the invention pertains without departing from the scope of the invention defined by the appended claims.
Claims (10)
1. The aluminum alloy for spaceflight is characterized by comprising the following components in percentage by mass: 2 to 2.6 percent of Cu, 1.9 to 2.6 percent of Mg, 5.7 to 6.7 percent of Zn, 0.05 to 0.12 percent of Fe, 0.04 to 0.09 percent of Mn, 0.05 to 0.11 percent of Sr, 0.06 to 0.16 percent of Si, less than or equal to 0.03 percent of Cr, less than or equal to 0.08 percent of Ti, 0.04 to 0.11 percent of Zr, 0.02 to 0.05 percent of Sc and the balance of Al, wherein the mass ratio of Fe/Mn is 0.9 to 1.4.
2. The aluminum alloy for aerospace according to claim 1, wherein the mass ratio of Fe/Mn is 1.0 to 1.1.
3. The aluminum alloy for aerospace according to claim 2, which comprises the following components in percentage by mass: 2.2 to 2.4 percent of Cu, 2.1 to 2.3 percent of Mg, 6.0 to 6.3 percent of Zn, 0.07 to 0.10 percent of Fe, 0.05 to 0.07 percent of Mn, 0.07 to 0.10 percent of Sr, 0.08 to 0.12 percent of Si, 0.01 to 0.03 percent of Cr, 0.06 to 0.08 percent of Ti, 0.06 to 0.08 percent of Zr, 0.03 to 0.04 percent of Sc and the balance of Al.
4. The method for preparing the aluminum alloy for aerospace according to claim 1, comprising the following steps:
(1) Melting the aluminum alloy composition of claim 1 into a melt, casting the melt to form an aluminum alloy ingot;
(2) The cast ingot is sequentially subjected to three-stage homogenization annealing treatment, hot rolling treatment, solution treatment and aging heat treatment to obtain the aluminum alloy.
5. The method for preparing an aluminum alloy for aerospace according to claim 4, wherein the three-stage homogenizing annealing treatment is specifically: the aluminum alloy after casting is heated to 370-400 ℃ from room temperature for 10-13 h, then heated to 500-530 ℃ for 15-18 h, then heated to 550-570 ℃ for 20-25 h, and then cooled to room temperature.
6. The method for producing an aluminum alloy for aerospace according to claim 5, wherein the three-stage homogenizing annealing is specifically: the aluminum alloy after casting is heated from room temperature to 370-400 ℃ for 10-13 h at the heating rate of 10-15 ℃/h, then heated to 500-530 ℃ at the heating rate of 20-25 ℃/h for 15-18 h, heated to 550-570 ℃ at the heating rate of 30-35 ℃/h for 20-25 h, and then cooled to room temperature at the cooling rate of 30-40 ℃/h.
7. The method for producing an aluminum alloy for aerospace according to claim 4, wherein the temperature of the solution treatment is 500 to 550 ℃ for 10 to 15 minutes, and the solution treatment is followed by quenching with water to room temperature.
8. The method for producing an aluminum alloy for aerospace according to claim 7, wherein the aging heat treatment is specifically: heating the sample quenched to room temperature in a heating furnace to 100-120 ℃, preserving heat for 35-45 min, then heating to 200-220 ℃ and preserving heat for 35-45 min; quenching with water to room temperature; continuously transferring the sample into an aging furnace for pre-aging within 10-20 min, wherein the pre-aging temperature is 90-130 ℃, and the pre-aging heat preservation time is 10-15 h.
9. The method for producing an aluminum alloy for aerospace according to claim 8, wherein a sample water-quenched to room temperature is heated to 100 to 120 ℃ in a heating furnace at a heating rate of 10 to 15 ℃/s, kept for 35 to 45 minutes, and then heated to 200 to 220 ℃ at a heating rate of 20 to 30 ℃/s, and kept for 35 to 45 minutes; quenching with water to room temperature; transferring the sample into an aging furnace for pre-aging within 10-20 min, wherein the pre-aging temperature is 90-130 ℃, and the pre-aging heat preservation time is 10-15 h.
10. Use of an aluminium alloy according to any one of claims 1 to 9 for the preparation of a device of aerospace construction.
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