Manufacturing method of light alloy structural part with complex structure

Abstract

The embodiment of the invention provides a manufacturing method of a light alloy structural part of a complex structure. The manufacturing method comprises the steps that the light alloy structure is divided according to a simple body and a complex structure part; a simple main body is manufactured by adopting a casting molding, pressure processing molding or stirring friction solid-phase additive molding technology; and preparing a complex structure part on the prepared simple main body by adopting an additive manufacturing technology. According to the method, the problem that the mechanical property, the structural complexity and the machining cost of a light alloy structural part of a complex structure are difficult to consider in the preparation process is remarkably solved.

Description

Technical Field

[0001] This application relates to the field of light alloy structural component processing and manufacturing technology, and in particular to a method for manufacturing a complex light alloy structural component. Background Technology

[0002] Lightweighting is one of the important development trends in aerospace equipment. Lightweight alloy materials have advantages such as low density, high specific strength, and good mechanical properties, and their application in the aerospace field is becoming increasingly widespread, achieving significant weight reduction. As the requirements for equipment weight reduction become increasingly stringent, the design of structural components is developing towards larger size, integration, and complexity, and the requirements for the mechanical properties, dimensional accuracy, and manufacturing efficiency of structural components are also becoming increasingly stringent.

[0003] Light alloy structural components experience different loads and effects in different parts during aerospace service, requiring a gradient of mechanical properties, but traditional forming methods all have inherent defects. Summary of the Invention

[0004] This application provides a method for manufacturing a lightweight alloy structural component with a complex structure.

[0005] This application provides a method for manufacturing a lightweight alloy structural component with a complex structure, including:

[0006] Light alloy structures are classified into simple main bodies and complex structural parts;

[0007] Simple main bodies are manufactured using casting, pressure forming, or friction stir solid-phase additive manufacturing technologies.

[0008] Complex structural parts are fabricated on a simple substrate that has already been prepared using additive manufacturing technology.

[0009] In one feasible implementation, the additive manufacturing technology includes fused wire additive manufacturing, powder additive manufacturing, and friction stir solid-state additive manufacturing.

[0010] In one feasible implementation, when a simple main body is manufactured using the aforementioned casting molding and a complex structural part is manufactured using fused wire additive manufacturing technology, the manufacturing steps include mold preparation, alloy melting, melt pouring, post-processing, mounting and positioning, 3D printing additive manufacturing, surface cleaning of structural parts, overall heat treatment, and workpiece finishing.

[0011] In one feasible implementation, the casting mold is any one of a sand mold, a ceramic mold, or a metal mold.

[0012] And / or, the melting temperature range for magnesium alloys is 700℃~850℃; the melting temperature range for aluminum alloys is 690℃~750℃; and the melting temperature range for titanium alloys is 1700℃~1800℃.

[0013] In one feasible implementation, the pouring speed of the magnesium alloy melt ranges from 35 mm / s to 60 mm / s;

[0014] And / or, the pouring speed of the molten aluminum alloy ranges from 5 mm / s to 20 mm / s.

[0015] In one feasible implementation, when a simple main body is manufactured using the pressure forming process and a complex structural part is manufactured using fused wire additive manufacturing or powder additive manufacturing, the manufacturing steps include blanking, billet preheating, forging or extrusion, post-processing, mounting and positioning, 3D printing, surface cleaning, overall heat treatment, and workpiece finishing.

[0016] In one feasible implementation, the preheating temperature range for magnesium alloy billets and aluminum alloy billets is 300℃~550℃, and the preheating time ranges from 4h to 30h.

[0017] The preheating temperature range for titanium alloy billets is 700℃~1000℃, and the preheating time range is 5h-30h.

[0018] In one feasible implementation, during 3D printing, the layer thickness ranges from 0.12 mm to 0.25 mm for fused filament additive manufacturing and from 5 μm to 50 μm for powder additive manufacturing.

[0019] In one feasible implementation, when a simple body is manufactured using the aforementioned friction stir solid-state additive manufacturing technology, and a complex structural part is manufactured using fused wire additive manufacturing technology or powder additive manufacturing technology, the manufacturing steps include friction stir solid-state additive manufacturing of the simple body, fused wire / powder additive manufacturing, post-processing, hot isostatic pressing, overall heat treatment, and finishing.

[0020] In one feasible implementation, when manufacturing a simple body using friction stir solid-state additive manufacturing technology, the stirring head rotation speed range is 300 r / min to 2500 r / min when the material is a magnesium alloy;

[0021] When the material is aluminum alloy, the stirring head speed range is 400 r / min to 2500 r / min;

[0022] When the material is titanium alloy, the stirring head speed range is 450 r / min to 2500 r / min.

[0023] This application provides a method for manufacturing a lightweight alloy structural component with a complex structure, including:

[0024] The lightweight alloy structure is divided into a simple main body and complex structural parts. Simple main bodies are manufactured using casting, pressure forming, or friction stir solid-state additive manufacturing techniques. Complex structural parts are then fabricated on the pre-fabricated simple main bodies using additive manufacturing technology. This method significantly improves upon the challenge of balancing mechanical properties, structural complexity, and processing costs in the fabrication of lightweight alloy structural components with complex structures. Attached Figure Description

[0025] The accompanying drawings, which are provided to further illustrate the invention and constitute a part of this invention, are illustrative embodiments of the invention and their descriptions are used to explain this application and do not constitute an undue limitation of the invention.

[0026] In the attached diagram:

[0027] Figure 1 This is a schematic flowchart illustrating a method for manufacturing a complex lightweight alloy structural component according to an embodiment of this application. Detailed Implementation

[0028] To enable those skilled in the art to better understand the technical solutions in this application, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of this application.

[0029] In the description of the embodiments of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0030] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0031] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0032] Lightweighting is one of the important development trends in aerospace equipment. Lightweight alloy materials have advantages such as low density, high specific strength, and good mechanical properties, and their application in the aerospace field is becoming increasingly widespread, achieving significant weight reduction. As the requirements for equipment weight reduction become increasingly stringent, the design of structural components is developing towards larger size, integration, and complexity, and the requirements for the mechanical properties, dimensional accuracy, and manufacturing efficiency of structural components are also becoming increasingly stringent.

[0033] Light alloy structural components experience different loads and effects in different parts during aerospace service, requiring a gradient of mechanical properties, but traditional forming methods all have inherent defects.

[0034] Common forming methods for light alloy structural components include casting, pressure processing, and additive manufacturing. Casting involves preparing alloy raw materials into a melt, which is then poured into a mold to obtain a structural component of the desired shape and size. Its advantages include no limitations on the shape and size of the structural component, especially its ability to form exceptionally complex and intricate features, compatibility with both mass-produced and research-developed products, and relatively low cost. However, the mechanical properties of the structural components are generally lower. Pressure processing involves shaping alloy billets into the desired structural components through forging, extrusion, rolling, and other deformation processes. Its advantages include excellent mechanical properties, but its disadvantages include a long manufacturing process, inability to form complex structures, and high cost. Additive manufacturing uses digital model files as a basis, employing software and CNC systems to melt and layer-by-layer deposit specialized alloy powders or wires to create the desired structural component. Its advantages include a short process flow, fast forming speed, and mechanical properties between those of castings and wrought parts. However, its disadvantages include lower surface quality, limited forming space, and high costs for wire and powder preparation, leading to an overall higher manufacturing cost. In recent years, friction stir solid-phase additive manufacturing has not only the advantages of traditional liquid phase additive manufacturing, but also the absence of a liquid phase in the solid-phase additive manufacturing process, resulting in high mechanical properties of the formed structural parts. However, the disadvantage is that the sides of the formed structural parts have overlapping waves, which require machining. Therefore, friction stir solid-phase additive manufacturing can only produce structural parts with simple shapes.

[0035] Figure 1This is a schematic flowchart illustrating a method for manufacturing a complex lightweight alloy structural component according to an embodiment of this application.

[0036] Reference Figure 1 As shown in the figure, this application provides a method for manufacturing a lightweight alloy structural component with a complex structure, including:

[0037] S100: Light alloy structures are classified into simple main bodies and complex structural parts.

[0038] S200: Simple main body manufactured using casting, pressure forming, or friction stir solid-state additive manufacturing technology.

[0039] S300: Complex structural parts are fabricated on a simple pre-fabricated substrate using additive manufacturing technology.

[0040] This method significantly improves the problem of balancing mechanical properties, structural complexity, and processing costs in the fabrication of complex lightweight alloy structural components.

[0041] In some examples, simple main bodies are manufactured using casting, while complex structural parts are manufactured using fused wire additive manufacturing technology. Specific steps include mold preparation, alloy melting, melt pouring, post-processing, mounting and positioning, 3D printing additive manufacturing, surface cleaning of structural parts, overall heat treatment, and workpiece finishing.

[0042] In these examples, the mold can be any of a sand mold, a ceramic mold, or a metal mold. The melting temperature range for magnesium alloys is 700℃ to 850℃; for aluminum alloys, it is 690℃ to 750℃; and for titanium alloys, it is 1700℃ to 1800℃. When pouring the melt into the mold, the pouring speed for magnesium alloy melt is 35 mm / s to 60 mm / s; and / or, the pouring speed for aluminum alloy melt is 5 mm / s to 20 mm / s.

[0043] In the post-processing stage, the surface dimensional accuracy of the cast part needs to reach ±(2~0.1) mm, and the surface roughness needs to be less than or equal to 6.3 μm. The completed simple main body is then clamped and positioned on a 3D printing platform for 3D filament additive manufacturing. During the 3D filament additive manufacturing process, the layer thickness ranges from 0.12 mm to 0.25 mm, and the printing speed ranges from 200 mm / s to 380 mm / s.

[0044] After 3D printing additive manufacturing is completed, the surface of the structural parts needs to be cleaned, followed by overall heat treatment. Magnesium alloy and aluminum alloy parts require solution treatment at 350℃ to 550℃, followed by 5-30 hours of air cooling, air cooling, or furnace cooling, and finally 5-30 hours of air cooling or air cooling at 100℃ to 250℃. Titanium alloy parts require annealing at 500℃ to 1000℃, followed by 5-30 hours of air cooling, air cooling, or furnace cooling.

[0045] In some examples, the pressure forming process is used to manufacture simple bodies, while fused wire additive manufacturing or powder additive manufacturing is used to manufacture complex structural parts. The manufacturing steps include blanking, billet preheating, forging or extrusion, post-processing, mounting and positioning, 3D printing, surface cleaning, overall heat treatment and workpiece finishing.

[0046] In these examples, magnesium alloy billets and aluminum alloy billets need to be preheated at 300℃~550℃ for 4h-30h, and titanium alloy billets need to be preheated at 700℃~1000℃ for 5h-30h. Pressure processing dies need to be preheated at 200℃~300℃.

[0047] Magnesium alloy and aluminum alloy billets need to be forged within a temperature range of 350℃ to 540℃, with a forging speed of 0.5mm / s to 20mm / s, and a total deformation range of 40% to 60%. Titanium alloy billets need to be forged within a temperature range of 700℃ to 1000℃, with a forging speed of 5mm / s to 30mm / s, and a total deformation range of 40% to 60%.

[0048] Magnesium alloy and aluminum alloy billets need to be extruded within a temperature range of 300℃ to 500℃, with an extrusion speed of 10m / min to 50m / min. Titanium alloy billets need to be forged within a temperature range of 900℃ to 950℃, with a forging speed of 1m / min to 1.5m / min.

[0049] When post-processing simple forged or extruded parts, the surface quality needs to be machined to a dimensional accuracy of ±(2~0.1) mm and a surface roughness ≤6.3 μm. In 3D printing filament additive manufacturing, the layer thickness ranges from 0.12 mm to 0.25 mm, and the printing speed ranges from 200 mm / s to 380 mm / s. In 3D printing powder additive manufacturing, the layer thickness ranges from 5 μm to 50 μm, and the printing speed ranges from 1000 mm / s to 2500 mm / s.

[0050] After 3D printing additive manufacturing is completed, the surface of the structural parts needs to be cleaned, followed by overall heat treatment. Magnesium alloy and aluminum alloy parts require solution treatment at 350℃ to 550℃, followed by 5-30 hours of air cooling, air cooling, or furnace cooling, and finally 5-30 hours of air cooling or air cooling at 100℃ to 250℃. Titanium alloy parts require annealing at 500℃ to 1000℃, followed by 5-30 hours of air cooling, air cooling, or furnace cooling.

[0051] In other examples, the friction stir solid-state additive manufacturing technology is used to manufacture simple bodies, while fused wire additive manufacturing technology or powder additive manufacturing technology is used to manufacture complex structural parts. The manufacturing steps include friction stir solid-state additive manufacturing of simple bodies, fused wire / powder additive manufacturing, post-processing, hot isostatic pressing, overall heat treatment, and finishing.

[0052] When manufacturing simple main bodies using friction stir solid-state additive manufacturing technology, magnesium alloy billets and aluminum alloy billets need to be preheated at a temperature range of 350℃-550℃ for 5h-30h. Titanium alloy billets need to be preheated at a temperature range of 700℃~1000℃ for 5h-30h.

[0053] When manufacturing simple bodies using friction stir solid-state additive manufacturing technology, the stirring head rotation speed ranges from 300 r / min to 2500 r / min and the welding travel speed ranges from 30 mm / min to 240 mm / min when the material is magnesium alloy; the stirring head rotation speed ranges from 400 r / min to 2500 r / min and the welding travel speed ranges from 30 mm / min to 600 mm / min when the material is aluminum alloy; and the stirring head rotation speed ranges from 450 r / min to 2500 r / min and the welding travel speed ranges from 50 mm / min to 1000 mm / min when the material is titanium alloy.

[0054] In 3D printing filament additive manufacturing, the printed layer thickness ranges from 0.12mm to 0.25mm, and the printing speed ranges from 200mm / s to 380mm / s. In 3D printing powder additive manufacturing, the printed layer thickness ranges from 5μm to 50μm, and the printing speed ranges from 1000mm / s to 2500mm / s.

[0055] After the 3D printing process, the parts undergo hot isostatic pressing (HIP). For magnesium alloy and aluminum alloy parts, the process is carried out for 5-30 hours at a pressure range of 100-180 MPa and a temperature range of 400-500℃. For titanium alloy parts, the process is carried out for 5-30 hours at a pressure range of 120-200 MPa and a temperature range of 900-980℃.

[0056] Finally, the components undergo overall heat treatment. Magnesium alloy and aluminum alloy components require solution treatment within the range of 350℃ to 550℃, followed by 5 hours to 30 hours of air cooling, air cooling, or furnace cooling, and finally 5 hours to 30 hours of air cooling or air cooling within the range of 100℃ to 250℃. Titanium alloy components require annealing within the range of 500℃ to 1000℃, followed by 5 hours to 30 hours of air cooling, air cooling, or furnace cooling.

[0057] To better illustrate the solutions provided in the embodiments of this application, two specific embodiments will be provided.

[0058] Example 1

[0059] Magnesium alloy structural components are manufactured using casting and fused wire additive manufacturing technologies.

[0060] Step 1: Divide the structure. Divide the components into "simple main body" and "complex structural parts".

[0061] Step Two: Sand Casting. Cast the "simple main body," using resin sand for both molding and core making.

[0062] Step 3: Melting. Pure magnesium, pure zinc, Mg-Nd master alloy, and Mn-Al master alloy are melted between 700℃ and 800℃, and then subjected to composite treatments such as stirring and refining before being allowed to stand for casting.

[0063] Step 4: Anti-gravity casting. Control the operating cabinet to introduce compressed air into the crucible, creating a pressure difference with the mold. The pressure increase rate is set to 1 kPa / s, the holding pressure fluctuation is ±0.3 kPa, and the maximum pressure difference is 100 kPa.

[0064] Step 5: Post-casting treatment. After pouring, wait 1.5 hours before removing the mold, cutting off the gating and riser parts of the casting, machining the machined surfaces of the casting, performing benchmark calibration at the connection between simple main body and complex structural parts, and pre-treating the mating surfaces to ensure that the surface roughness is less than 6.3μm.

[0065] Step Six: Mounting and Positioning. Secure the cast simple main body to the printing platform using bolts / adhesives or other methods.

[0066] Step 7: Fused Wire Additive Manufacturing. Start fused wire additive manufacturing at the connection point between the simple main body and the complex structural parts. Use ZM6G ​​filament, set the printing layer thickness to 0.2mm, and the printing speed to 350mm / s.

[0067] Step 8: Inspection and Testing. The castings undergo dimensional inspection and internal quality testing using X-rays and fluorescence.

[0068] Step 9: Surface cleaning. Remove burrs and oxide scale from the surface of the components.

[0069] Step 10: Heat treatment. The castings are subjected to solution aging treatment in sequence. The solution temperature is 500℃ and the solution time is 15h. After solution treatment, the castings are air-cooled and then aged at room temperature for 220℃ for 25h. After aging, the castings are air-cooled to room temperature.

[0070] Step 11: Finishing. The ZM6G ​​magnesium alloy components are finished to meet the requirements for dimensional accuracy and surface finish.

[0071] Example 2

[0072] Aluminum alloy structural components are manufactured using pressure forming and powder additive manufacturing technologies.

[0073] Step 1: Divide the structure. Divide the components into "simple main body" and "complex structural parts".

[0074] Step 2: Preheating. Preheat the ZL114A aluminum alloy ingot at 350℃ for 4 hours, and preheat the mold at 250℃ for 4 hours.

[0075] Step 3: Forging the simple main body. The ZL114A aluminum alloy ingot is forged at 535℃±5℃, with a forging speed of 20mm / s and a total forging deformation of 40%. After forging, it is air-cooled.

[0076] Step 4: Post-forging processing. For the connection between a simple main body and a complex structural part, a benchmark calibration is performed, and the mating surfaces are pre-treated to ensure a surface roughness of less than 6.3 μm.

[0077] Step 5: Mounting and Positioning. Secure the cast simple main body to the printing platform using bolts / adhesives or other methods.

[0078] Step Six: Powder Additive Manufacturing. Begin powder additive manufacturing at the junction of the simple main body and the complex structural parts, setting the printing layer thickness to 40μm and the printing speed to 1800mm / s.

[0079] Step 7: Surface Cleaning. Clean burrs, oxide scale, etc. from the surface of the components.

[0080] Step 8: Inspection and Testing. Dimensional inspection of the components and internal quality testing using X-rays and fluorescence.

[0081] Step Nine: Heat Treatment. The components are subjected to solution aging treatment in sequence. The solution temperature is 500℃ and the solution time is 8 hours. After solution treatment, the components are air-cooled and then subjected to aging treatment after cooling to room temperature. The aging temperature is 160℃ and the time is 10 hours. After aging, the components are air-cooled to room temperature.

[0082] Step 10: Finishing. The ZL114A aluminum alloy components are finished to meet the requirements for dimensional accuracy and surface finish.

[0083] Example 3

[0084] Friction Stir Solid-State Additive Manufacturing and Powder Additive Manufacturing of Titanium Alloy Structural Components

[0085] Step 1: Divide the structure. Divide the components into simple main parts and complex structural parts.

[0086] Step 2: Raw material preparation. The TC4 titanium alloy rod is first held at 750℃ under a vacuum of 1.5×10-3Pa for 2 hours, then filled with 0.5% hydrogen and held for 3 hours before being slowly cooled to room temperature. Then it is heated to 950℃ and held for 30 minutes before being water-cooled. Finally, the grains are refined by equal diameter angular extrusion to obtain the additive raw material rod.

[0087] Step 3: Friction Stir Solid-State Additive Manufacturing. A simple main body is prepared using friction stir solid-state additive manufacturing. The stirring head rotation speed is set to 1200 r / min, the forward speed to 800 mm / min, the downward pressure to 200 kN, and the indentation depth to 0.5 mm.

[0088] Step 4: Powder Additive Manufacturing. Powder additive manufacturing begins at the junction of the simple main body and the complex structural parts, with a printing layer thickness of 30μm and a printing speed of 1200mm / s.

[0089] Step 5: Post-processing. Remove burrs, oxide scale, etc. from the surface of the components.

[0090] Step Six: Inspection and Testing. The components are inspected for dimensions and internal quality is tested using X-rays and fluorescence.

[0091] Step 7: Hot Isostatic Pressing. The hot isostatic pressing equipment is heated to 920℃ at a heating rate of 15℃ / min and the pressure is 120MPa. After holding at this temperature for 2.5h, it is cooled with the furnace.

[0092] Step 8: Heat treatment. After hot isostatic pressing, the component is placed in a vacuum heat treatment furnace for annealing at 750℃ for 5 hours. After annealing, it is air-cooled to room temperature.

[0093] Step Nine: Finishing. The TC4 titanium alloy components are finished to meet the requirements for dimensional accuracy and surface finish.

[0094] The magnesium alloy structural parts, aluminum alloy structural parts, and titanium alloy structural parts prepared in the above embodiments were subjected to bulk sampling tests to determine their room temperature mechanical properties. The specific results are as follows:

[0095]

[0096] The above comparison shows that the performance of the light alloy structural parts prepared by the method of this application is significantly better than that of the light alloy structural parts cast by the traditional anti-gravity casting technology.

[0097] It is readily understood that, based on the several embodiments provided in this application, those skilled in the art can combine, split, or reorganize the embodiments of this application to obtain other embodiments, none of which exceed the protection scope of this application.

[0098] The above detailed embodiments further illustrate the purpose, technical solution, and beneficial effects of the embodiments of this application. It should be understood that the above are merely specific embodiments of the embodiments of this application and are not intended to limit the protection scope of the embodiments of this application. Any modifications, equivalent substitutions, improvements, etc., made on the basis of the technical solutions of the embodiments of this application should be included within the protection scope of the embodiments of this application.

Claims

1. A method of manufacturing a light alloy structural member of complex configuration, characterized by, The application relates to a method for manufacturing a light alloy structure. The light alloy structure is divided into a simple body and a complex structure part; The simple body is manufactured by casting forming, pressure processing forming or friction stir solid-phase additive forming technology; The complex structure part is manufactured on the prepared simple body by additive manufacturing technology.

2. The method of manufacturing a light alloy structural member according to claim 1, characterized by The additive manufacturing technology includes fused filament additive manufacturing technology, powder additive manufacturing technology and friction stir solid-phase additive manufacturing.

3. The method of manufacturing a complex-structured light alloy structural member according to claim 1, characterized by, When the simple body is manufactured by the casting forming and the complex structure part is manufactured by the fused filament additive manufacturing technology, the manufacturing steps include casting preparation, alloy smelting, melt pouring, post-processing, clamping positioning, 3D printing additive manufacturing, structure surface cleaning, overall heat treatment and workpiece finishing.

4. The method of manufacturing a complex-structured light alloy structural member according to claim 3, characterized by, The casting forming is any one of sand casting, ceramic casting or metal casting; The smelting temperature range of the magnesium alloy material is 700-850 DEG C; the smelting temperature range of the aluminum alloy material is 690-750 DEG C; and the smelting temperature range of the titanium alloy material is 1700-1800 DEG C.

5. The method of manufacturing a complex-structured light alloy structural member according to claim 3, characterized by, The pouring speed range of the magnesium alloy melt is 35-60 mm / s; The pouring speed range of the aluminum alloy melt is 5-20 mm / s.

6. The method of manufacturing a complex-structured light alloy structural member according to claim 1, characterized by, When the simple body is manufactured by the pressure processing forming and the complex structure part is manufactured by the fused filament additive manufacturing technology or the powder additive manufacturing technology, the manufacturing steps include blanking, blank preheating, forging or extrusion, post-processing, clamping positioning, 3D printing, surface cleaning, overall heat treatment and workpiece finishing steps.

7. The method of manufacturing a complex-structured light alloy structural member according to claim 6, characterized by The preheating temperature range of the magnesium alloy blank and the aluminum alloy blank is 300-550 DEG C, and the preheating time range is 4-30 h; The preheating temperature range of the titanium alloy blank is 700-1000 DEG C, and the preheating time range is 5-30 h.

8. The method of manufacturing a complex-structured light alloy structural member according to claim 6, characterized by, When 3D printing, the fused filament additive manufacturing layer thickness range is 0.12-0.25 mm; and the powder additive manufacturing layer thickness range is 5-50 um.

9. The method of manufacturing a complex-structured light alloy structural member according to claim 1, characterized by, When the simple body is manufactured by the friction stir solid-phase additive forming technology and the complex structure part is manufactured by the fused filament additive manufacturing technology or the powder additive manufacturing technology, the manufacturing steps include friction stir solid-phase additive manufacturing of the simple body, fused filament / powder additive manufacturing, post-processing, hot isostatic pressing, overall heat treatment and finishing.

10. The method of manufacturing a complex-structured light alloy structural member according to claim 9, wherein When the simple body is manufactured by the friction stir solid-phase additive forming technology, the stirring head rotating speed range is 300-2500 r / min when the material is a magnesium alloy; The stirring head rotating speed range is 400-2500 r / min when the material is an aluminum alloy; The stirring head rotating speed range is 450-2500 r / min when the material is a titanium alloy.

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