Preparation method of three-way high-strength plastic magnesium alloy structural part for spaceflight structure multi-way part

Abstract

The invention discloses a preparation method of a three-way high-strength plastic magnesium alloy structural part for a multi-way part of a spaceflight structure, which adopts two-stage solid solution heat treatment, so that a large number of lamellar LPSO phases are separated out from an alloy matrix, the forgeability in the alloy forging process is improved, and the strength of the alloy is improved. The alloy is not cracked during large-deformation forging, multi-direction free forging with few passes and single large deformation is adopted, and meanwhile the dependent variables in different directions are controlled, so that the three-direction high-strength and high-plasticity magnesium alloy square billet is prepared in a short process; and heat preservation before forging is reduced, and forging is conducted at a high temperature, so that rare earth elements in the alloy are kept in a supersaturated state all the time, precipitation of dynamic precipitated phases and secondary growth of crystal grains in the forging process are avoided, then a large number of fine second phases are precipitated in the aging process, and the comprehensive mechanical property of the alloy is enhanced.

Description

Technical Field

[0001] This invention relates to a method for preparing a three-dimensional high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components, belonging to the field of magnesium rare earth alloy material preparation technology. Background Technology

[0002] With the development of aerospace technology, the demand for lightweight structural materials in the aerospace field is becoming increasingly urgent. A certain type of multi-channel component is a typical component in the aerospace field, requiring magnesium alloy structural parts to meet the following mechanical properties in all three directions: tensile strength greater than 450 MPa, yield strength greater than 300 MPa, and elongation after fracture greater than 8%. However, currently widely used magnesium alloys such as AZ-series, ZK-series, and VW-series cannot meet the mechanical property requirements of multi-channel components. For example, application number 202310645241.0 developed a short-process method for preparing low-anisotropic magnesium alloys, in which the embodiment uses semi-continuous casting → homogenization heat treatment → ring rolling or die forging or rolling. However, the room temperature mechanical properties of the prepared low-anisotropic magnesium alloy structural parts are only 410 MPa to 360 MPa, which cannot meet the mechanical property requirements of multi-channel components. Application No. 201710179990.3 developed a method for preparing isotropic ultra-high strength heat-resistant magnesium alloy structural parts. The example adopted a semi-continuous casting → homogenization heat treatment → slow multi-pass forging → aging heat treatment. The room temperature elongation after fracture of the prepared magnesium alloy structural parts is only 4%~6%, which cannot meet the mechanical performance requirements of multi-pass parts. At the same time, its forging process includes 6~12 upsetting and drawing processes and intermediate tempering processes, and the forging process is too long.

[0003] Mg-Gd-Y-Zn alloys are a newly developed magnesium alloy system in recent years. They can not only improve strength through solid solution and precipitation strengthening with rare earth elements, but also possess a high-strength LPSO phase that coordinates deformation through bending and twisting, thereby increasing the alloy's strength and plasticity. This system holds promise for producing magnesium alloy structural components that meet requirements. However, current applications of Mg-Gd-Y-Zn alloys are mainly in magnesium alloy sheets, and it remains difficult to produce magnesium rare earth alloy forgings that meet requirements. The main reasons are as follows: First, the presence of the LPSO phase makes hot deformation of high rare earth magnesium alloys, which are already difficult to hot deform, even more challenging, and large deformation forgings are prone to cracking. Second, rare earth magnesium alloys are prone to developing textures during deformation, leading to significant differences in mechanical properties in different directions, resulting in some directional properties failing to meet standards. Third, current free multi-directional forging processes for magnesium alloys mostly involve six or more forging passes, including pre-forging holding and tempering during forging, resulting in excessively long forging processes and high costs. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a method for preparing a three-dimensional high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components, which has the advantages of short preparation process and low cost.

[0005] The technical solution of this invention is: A method for manufacturing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components, comprising: S1: Magnesium alloy ingots are prepared by semi-continuous casting. The magnesium alloy ingots after semi-continuous casting are cut into cylindrical ingots by sawing. S2: Perform a two-stage solution treatment on a cylindrical ingot to obtain a magnesium alloy solution ingot; S3: Magnesium alloy solution ingots are forged directly using a multi-directional forging method without cooling to obtain multi-directional forging billets; S4: Perform final forging and shaping on the multi-directional forging billet to obtain a magnesium rare earth alloy square billet; S5: Aging heat treatment is performed on magnesium rare earth alloy billets to obtain triaxial high-strength ductile magnesium rare earth alloy structural parts.

[0006] Further, in step S2, the heating method for the two-stage solution treatment is as follows: first, under a protective atmosphere, the temperature is raised from room temperature to 510℃~530℃ and held for 16h~20h; then, the temperature is cooled in a furnace to 470℃~490℃ and held for another 20h~30h.

[0007] Furthermore, under a protective atmosphere, the temperature is first raised from room temperature to 510℃~530℃, with a heating rate of 100℃ / h~150℃ / h.

[0008] Furthermore, in step S3, the magnesium alloy solution ingot is forged using a multi-directional forging process without cooling, specifically as follows: Before forging, heat the upper and lower dies of the hydraulic press to 450℃~480℃ and keep them at that temperature for 5h~10h. A hydraulic press with heat preservation completed the process of upsetting and drawing a magnesium alloy solution ingot in three passes. Each pass of upsetting and drawing includes one upsetting along the height direction and one upsetting followed by drawing.

[0009] Furthermore, the upsetting and drawing multi-directional forging method for each pass is as follows: The upsetting reduction along the height direction is 65%~80%, and the upsetting speed is 5mm / s~10mm / s; Then, the ingot is rotated 90 degrees and pressed down along the edges eight to twelve times to elongate it, so that the edges of the magnesium alloy solution ingot disappear. The amount of pressing down in a single elongation is 10% to 25% of the height of the magnesium alloy solution ingot, and the pressing speed is 10 mm / s to 20 mm / s.

[0010] Furthermore, during the three-pass upsetting and drawing multi-directional forging process, the upper and lower dies of the hydraulic press are temperature controlled and maintained at 450℃~480℃.

[0011] Further, in step S4, the multi-directional forging billet undergoes final forging and shaping, specifically as follows: With the height direction of the multi-directional forging billet as the Z direction, and any two radial directions perpendicular to the Z direction as the X and Z directions, press down along the Z direction, with a pressing amount of 50% to 70% of the height of the multi-directional forging billet in the Z direction; then repeat the following operation 4 to 8 times: Flip the forging billet and press it down along the X direction, with a reduction of 5-10% of the height of the multi-directional forging billet in the X direction; Flip the forging billet and press it down along the Y direction, with a pressing amount of 5 to 10% of the height of the multi-directional forging billet in the Y direction; After forging, the material is air-cooled to obtain a magnesium rare earth alloy billet.

[0012] Further, in step S5, the magnesium rare earth alloy billet is subjected to aging heat treatment, specifically: heated to 190℃~230℃ and held for 20h~100h.

[0013] Furthermore, in step S1, the height-to-diameter ratio of the cylindrical ingot is 2-3 to prevent the cylindrical ingot from bending during the forging process.

[0014] The advantages of this invention compared to the prior art are: (1) The present invention performs a two-stage solution heat treatment on the Mg-Gd-Y-Zn alloy containing LPSO before forging to precipitate a large amount of lamellar LPSO phase in the alloy, which significantly increases the forgeability of the alloy, so that the alloy does not crack under large deformation, and thus can be forged in multiple directions with large deformation.

[0015] (2) In this invention, the alloy is not cooled after bipolar solution heat treatment and is directly subjected to isothermal multi-directional forging at a higher temperature of 450~480℃. This reduces the heat preservation before forging in traditional processes to prevent grain growth before forging. At the same time, the alloy is always at a higher temperature, which reduces the dynamic precipitation of the alloy during the forging process. This makes rare earth elements such as Gd and Y in the alloy in a supersaturated state, which helps the alloy to precipitate a large number of fine precipitate phases during aging, thereby improving the strength of the alloy.

[0016] (3) This invention differs from the traditional multi-pass, low-deformation multi-directional forging process combined with inter-pass heat preservation. Instead, it uses isothermal multi-directional forging with fewer passes and larger deformation, combined with multiple passes of drawing treatment. This reduces the number of forging passes and the heat preservation and tempering between passes, significantly lowering the cost. At the same time, the forging process is designed to ensure that the deformation of the alloy in each direction remains basically consistent. Furthermore, the multiple drawing treatments significantly reduce the texture generated in the alloy during forging, thereby enabling the short-process and low-cost preparation of triaxial high-strength and high-ductility magnesium rare earth alloy structural parts. Attached Figure Description

[0017] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 This is a microstructure diagram of the magnesium rare earth alloy after two-stage solid solution treatment in Embodiment 1 of the present invention. Figure 2 This is a microstructure diagram of the magnesium rare earth alloy after single-stage solid solution treatment in the comparative example of this invention. Figure 3 This is a flowchart illustrating the preparation method of a three-dimensional high-strength PVC-Mg alloy structural component in an embodiment of the present invention. Detailed Implementation

[0018] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0019] This invention proposes a method for preparing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components, such as... Figure 3 As shown, it includes: S1: Semi-continuous casting; Magnesium alloy ingots are prepared using a semi-continuous casting method, and cylindrical ingots are obtained by sawing the semi-continuously cast magnesium alloy ingots. To prevent bending of the ingots during forging and to ensure the reduction in the height direction, the height-to-diameter ratio of the ingots is controlled at 2~3.

[0020] S2: Two-stage solution heat treatment; The magnesium alloy ingot prepared in step S1 is subjected to a two-stage solution treatment. The heating regime is as follows: First, under a protective atmosphere, it is heated from room temperature to 510℃~530℃ at a heating rate of 100℃ / h~150℃ / h and held for 16h~24h; then, it is furnace cooled to 470℃~490℃ and held for 20~30h. The two-stage solution heat treatment designed in this invention differs from the traditional single-stage solution heat treatment. First, a higher temperature of 510℃~530℃ is used for holding, which allows the rare earth second phase on the alloy grain boundaries to fully dissolve, giving full play to the strengthening effect of rare earth on the alloy and retaining the blocky LPSO phase in the alloy. Then, a lower temperature of 470℃~490℃ is used for holding, which transforms the original blocky LPSO phase in the alloy into a large number of lamellar LPSO phases. Compared with the original blocky LPSO phase, the large number of lamellar LPSO phases in the alloy significantly increases the forgeability of the alloy, ensuring that the alloy will not crack under high strain forging.

[0021] S3: Upsetting and Drawing Multi-directional Forging; The magnesium alloy solution ingot after the double-stage solution heat treatment in step S2 is directly subjected to multi-directional forging without cooling. Before multi-directional forging, the upper and lower dies of the hydraulic press are heated to 450℃~480℃ and held for 5~10 hours, and the temperature of the upper and lower dies is controlled during the forging process. Then, the magnesium alloy solution ingot is subjected to three passes of upsetting and drawing multi-directional forging. Each pass of upsetting and drawing multi-directional forging includes one upsetting along the height direction and then drawing. The specific process is as follows: first, the upsetting amount along the height direction is 65%~80%, and the downsetting speed is 5mm / s~15mm / s. Then, it is rotated 90 degrees and drawn eight to twelve times along the edges, with a single downsetting amount of 10%~25% and a downsetting speed of 10mm / s~20mm / s. After a single upsetting and drawing process, the billet is a cylindrical ingot with a height-to-diameter ratio of 2 to 3. The above steps are then repeated twice.

[0022] Due to the two-stage solution heat treatment employed in step S2, this invention differs from the traditional process that combines low strain (30%~50%), high upsetting and drawing cycles (6~9 passes) with intermediate tempering and heat preservation. This step utilizes a one-step forming process with large deformation (65%~80%) and fewer upsetting and drawing cycles (3 passes), thereby producing triaxial high-strength and high-ductility magnesium rare earth alloy structural parts in a short and efficient manner. Furthermore, the direct forging without cooling after the two-stage solution treatment in step S2 keeps the alloy at a high temperature throughout the process, reducing the precipitation of dynamically precipitated phases during forging. This facilitates better precipitation of fine and dispersed second phases during the aging process, thus improving the alloy's mechanical properties.

[0023] S4: Final forging and shaping; The multi-directional forging billet after step S3 is subjected to final forging and shaping. The specific process of final forging and shaping is as follows: Taking the height direction of the cylindrical ingot as the Z direction and any two perpendicular radial directions as the X and Z directions, first press down 50%~70% along the Z direction of the forging billet after the billet is opened, then flip the forging billet and press down along the X direction first, with a single pressing amount of 5%~10%, then flip the forging billet and press down along the Y direction, with a single pressing amount of 5%~10%, then repeat the above steps, pressing down 4~8 times in the X and Y directions. After forging, air cooling is performed to finally produce a magnesium alloy square billet.

[0024] S5: Aging heat treatment; The magnesium alloy forging billet shaped in step S4 is subjected to aging treatment at 190℃~230℃ for 20h~100h to obtain a triaxial high-strength ductile magnesium rare earth alloy structural component.

[0025] Experimental results show that the triaxial high-strength PVC rare earth alloy structural components prepared by this invention can stably achieve at least the following triaxial mechanical properties at room temperature: tensile strength greater than 450 MPa, yield strength greater than 300 MPa, and elongation after fracture greater than 8%, and can be used for the preparation of multi-channel components for aerospace structures.

[0026] The present invention will be further illustrated by two embodiments and a comparative example: Example 1 A method for manufacturing a magnesium alloy aerospace structural multi-channel component, wherein the selected magnesium alloy has the following mass percentages: Gd: 9.2%, Y: 3.8%, Zn: 1.5%, Zr: 0.38%. Impurities include Fe, Si, Cu, Ni, etc., with the total impurity content not exceeding 0.1%, and the remainder being magnesium.

[0027] Specifically, the following steps are included: S1. Semi-continuous casting; Magnesium alloy ingots are prepared by semi-continuous casting. The semi-continuously cast magnesium alloy ingots are then machined, inspected for flaws, and cut into cylindrical ingots with a diameter of 200 mm and a length of 500 mm.

[0028] S2. Two-stage solution heat treatment; the magnesium alloy ingot prepared in step S1 is subjected to a two-stage solution treatment. The heating regime is as follows: first, under a protective atmosphere, it is heated from room temperature to 520℃ at a heating rate of 150℃ / h and held at that temperature for 20h; then, it is furnace cooled to 480℃ and held at 480℃ for 20h. The microstructure is as follows. Figure 1 As shown, the alloy contains a large number of lamellar LPSO phases.

[0029] S3. Upsetting and Drawing Multi-directional Forging: The magnesium alloy solution ingot after the double-stage solution heat treatment in step S2 is directly subjected to multi-directional forging without cooling. Before multi-directional forging, the upper and lower dies of the hydraulic press are heated to 480℃ and held for 8 hours, and the temperature of the upper and lower dies is controlled during the forging process. Subsequently, the magnesium alloy solution ingot undergoes three passes of upsetting and drawing multi-directional forging. Each pass of upsetting and drawing multi-directional forging includes one upsetting along the height direction and then drawing after upsetting. The specific process is as follows: first, the upsetting along the height direction has a reduction of 80%, and the downsetting speed is 6 mm / s. Then, it is rotated 90 degrees and downset 12 times along the edge, with a single downsetting reduction of 10%~25% and a downsetting speed of 15 mm / s. After a single upsetting and drawing, the height-to-diameter ratio of the billet is 2.5. The above steps are then repeated twice.

[0030] S4. Final forging and shaping; The multi-directional forging billet after step S3 is subjected to final forging and shaping. The specific process of final forging and shaping is as follows: Taking the height direction of the cylindrical forging billet as the Z direction and any two perpendicular radial directions as the X and Z directions, first press down 60% along the Z direction of the forging billet after the billet is opened, then flip the forging billet and press down along the X direction first, with a single pressing amount of about 9%, then flip the forging billet and press down along the Y direction, with a single pressing amount of about 9%, then repeat the above steps, pressing down 5 times in the X and Y directions. After forging, air cooling is performed to finally produce a 350mm×200mm×200mm magnesium alloy square billet.

[0031] S5. Aging heat treatment; The magnesium alloy forging billet shaped in step S4 was subjected to aging treatment at 200℃ for 48 hours. The mechanical properties of the prepared triaxial high-strength ductile magnesium rare earth alloy structural parts are shown in Table 1. Table 1 Mechanical Properties of Example 1

[0032] Example 2 A method for manufacturing a magnesium alloy aerospace structural multi-channel component, wherein the selected magnesium alloy has the following mass percentages: Gd: 9.5%, Y: 4.3%, Zn: 1.5%, Zr: 0.38%. Impurities include Fe, Si, Cu, Ni, etc., with the total impurity content not exceeding 0.1%, and the remainder being magnesium.

[0033] Specifically, the following steps are included: S1. Semi-continuous casting; Magnesium alloy ingots are prepared by semi-continuous casting. The magnesium alloy ingots produced by semi-continuous casting are then machined, inspected for flaws, and cut into cylindrical ingots with a diameter of 250 mm and a length of 700 mm.

[0034] S2. Two-stage solution heat treatment; The magnesium alloy ingot prepared in step S1 is subjected to two-stage solution treatment. The heating regime is as follows: First, under a protective atmosphere, it is heated from room temperature to 520℃ at a heating rate of 150℃ / h and held for 24h; then, it is furnace cooled to 480℃ and held at 480℃ for 30h.

[0035] S3. Upsetting and Drawing Multi-directional Forging: The magnesium alloy solution ingot after the double-stage solution heat treatment in step S2 is directly subjected to multi-directional forging without cooling. Before multi-directional forging, the upper and lower dies of the hydraulic press are heated to 480℃ and held for 8 hours, and the temperature of the upper and lower dies is controlled during the forging process. Subsequently, the magnesium alloy solution ingot undergoes three passes of upsetting and drawing multi-directional forging. Each pass of upsetting and drawing multi-directional forging includes one upsetting along the height direction and then drawing after upsetting. The specific process is as follows: first, the upsetting along the height direction has a reduction of 80%, and the downsetting speed is 8mm / s. Then, it is rotated 90 degrees and downset 12 times along the edge, with a single downsetting reduction of 10%~25% and a downsetting speed of 20mm / s. After a single upsetting and drawing, the height-to-diameter ratio of the billet is 2.8. The above steps are then repeated twice.

[0036] S4. Final forging and shaping; The multi-directional forging billet after step S3 is subjected to final forging and shaping. The specific process of final forging and shaping is as follows: Taking the height direction of the cylindrical forging billet as the Z direction and any two perpendicular radial directions as the X and Z directions, first press down 70% along the Z direction of the forging billet after the billet is opened, then flip the forging billet and press down along the X direction first, with a single pressing amount of about 10%, then flip the forging billet and press down along the Y direction, with a single pressing amount of about 7%, then repeat the above steps, pressing down 6 times in the X and Y directions. After forging, air cooling is performed to finally produce a 400mm×300mm×250mm magnesium alloy square billet.

[0037] S5. Aging heat treatment; The magnesium alloy forging billet shaped in step S4 was subjected to aging treatment at 225℃ for 24 hours. The mechanical properties of the prepared triaxial high-strength ductile magnesium rare earth alloy structural parts are shown in Table 2. Table 2 Mechanical Properties of Example 2

[0038] Comparative Example 1 A method for manufacturing a magnesium alloy aerospace structural multi-channel component, wherein the selected magnesium alloy has the following mass percentages: Gd: 9.2%, Y: 3.8%, Zn: 1.5%, Zr: 0.38%. Impurities include Fe, Si, Cu, Ni, etc., with the total impurity content not exceeding 0.1%, and the remainder being magnesium.

[0039] Specifically, the following steps are included: S1. Semi-continuous casting; Magnesium alloy ingots are prepared by semi-continuous casting. The semi-continuously cast magnesium alloy ingots are then machined, inspected for flaws, and cut into cylindrical ingots with a diameter of 200 mm and a length of 500 mm.

[0040] S2. Two-stage solution heat treatment; the magnesium alloy ingot prepared in step S1 is subjected to a two-stage solution treatment. The heating regime is as follows: first, under a protective atmosphere, it is heated from room temperature to 520℃ at a heating rate of 150℃ / h, and held at that temperature for 20h before being removed and air-cooled. The microstructure is as follows. Figure 2 As shown, there is almost no lamellar LPSO phase in the alloy.

[0041] S3. Upsetting and drawing multi-directional forging: The magnesium alloy solution-treated ingot from step S2 is forged directly without cooling. Before forging, the upper and lower dies of the hydraulic press are heated to 480℃ and held for 8 hours, and the temperature of the upper and lower dies is controlled during the forging process. After a single pass of 80% reduction, the sample cracked severely and could not be forged further.

[0042] The embodiments described above are merely preferred embodiments of the present invention. Ordinary variations and substitutions made by those skilled in the art within the scope of the technical solution of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for preparing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components, characterized in that, include: S1: Magnesium alloy ingots are prepared by semi-continuous casting. The magnesium alloy ingots after semi-continuous casting are cut into cylindrical ingots by sawing. S2: Perform a two-stage solution treatment on a cylindrical ingot to obtain a magnesium alloy solution ingot; S3: Magnesium alloy solution ingots are forged directly using a multi-directional forging method without cooling to obtain multi-directional forging billets; S4: Perform final forging and shaping on the multi-directional forging billet to obtain a magnesium rare earth alloy square billet; S5: Aging heat treatment is performed on magnesium rare earth alloy billets to obtain triaxial high-strength ductile magnesium rare earth alloy structural parts.

2. The method for preparing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components according to claim 1, characterized in that, In step S2, the heating method for the two-stage solution treatment is as follows: first, under a protective atmosphere, the temperature is raised from room temperature to 510℃~530℃ and held for 16h~20h; then, the temperature is cooled in the furnace to 470℃~490℃ and held for another 20h~30h.

3. The method for preparing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components according to claim 2, characterized in that, First, under a protective atmosphere, heat from room temperature to 510℃~530℃, with a heating rate of 100℃ / h~150℃ / h.

4. The method for preparing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components according to claim 1, characterized in that, In step S3, the magnesium alloy solution ingot is forged using a multi-directional forging process without cooling, specifically as follows: Before forging, heat the upper and lower dies of the hydraulic press to 450℃~480℃ and keep them at that temperature for 5h~10h. A hydraulic press with heat preservation completed the process of upsetting and drawing a magnesium alloy solution ingot in three passes. Each pass of upsetting and drawing includes one upsetting along the height direction and one upsetting followed by drawing.

5. The method for preparing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components according to claim 4, characterized in that, The upsetting and drawing multi-directional forging method for each pass is as follows: The upsetting reduction along the height direction is 65% to 80%, and the upsetting speed is 5 mm / s to 10 mm / s. Then, it is flipped 90 degrees and pressed down along the edges eight to twelve times to elongate it, so that the edges of the magnesium alloy solution ingot disappear. The amount of pressing down in a single elongation is 10% to 25% of the height of the magnesium alloy solution ingot, and the pressing speed is 10 mm / s to 20 mm / s.

6. The method for preparing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components according to claim 4, characterized in that, During the three-pass upsetting and drawing multi-directional forging process, the upper and lower dies of the hydraulic press are temperature controlled and maintained at 450℃~480℃.

7. The method for preparing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components according to claim 1, characterized in that, In step S4, the multi-directional forging billet undergoes final forging and shaping, specifically as follows: Using the height direction of the multi-directional forging billet as the Z-direction and any two radial directions perpendicular to the Z-direction as the X and Z-directions, press down along the Z-direction, with a pressing amount of 50% to 70% of the height of the multi-directional forging billet in the Z-direction; then repeat the following operation 4 to 8 times: Flip the forging billet and press it down in the X direction. The pressing amount is 5 to 10% of the height of the multi-directional forging billet in the X direction. Flip the forging billet and press it down along the Y direction. The pressing amount is 5 to 10% of the height of the multi-directional forging billet in the Y direction. After forging, the material is air-cooled to obtain a magnesium rare earth alloy billet.

8. The method for preparing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components according to claim 1, characterized in that, In step S5, the magnesium rare earth alloy billet is subjected to aging heat treatment, specifically: heated to 190℃~230℃ and held for 20h~100h.

9. A method for preparing a triaxial high-strength PVC-Mg alloy structural component for aerospace structural multi-channel components according to claim 1, characterized in that, In step S1, the height-to-diameter ratio of the cylindrical ingot is 2 to 3 to prevent the cylindrical ingot from bending during the forging process.

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