Composite structural member

Abstract

The embodiment of the utility model discloses a composite structural member, which comprises a framework part made of a first metal material, a first metal material and a second metal material, the matrix part is made of at least one metal material, the matrix part is filled in the gap of the framework part, and each metal material in the at least one metal material is different from the first metal material. Due to the fact that the gaps of the framework part are filled with the base body part, a series of problems caused by the fact that a structural carrier and a functional carrier are designed respectively and then assembled and coupled are avoided, on the contrary, the gradient metal material with the two materials compounded and the components and the structure in a continuous gradient change mode is obtained, and the gradient metal material can be used for manufacturing the gradient metal material. Due to the fact that the composite structural part is of the integrated structure, the characteristics of two or more materials can be combined, the effect of functional combination or organic integration can be achieved, and the product efficiency and the application value are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of metal materials, in particular to a composite structural part. Background Art

[0002] In the industrial field, especially in high-tech fields such as the aerospace industry, there are many requirements for product structure and function, such as product structural strength, heat protection and thermal conductivity, circuit conduction, electromagnetic shielding, tissue fusion, etc. The above functions are often achieved through a certain structural feature of the product, such as the shell, joints and other components. The most basic product elements are the product structure carrier and the product function carrier.

[0003] Because industrial products need to have certain structural strength and specific structural functions, and are limited by design ideas and process methods, the traditional solution is to design the structural carrier and the functional carrier separately and then assemble and couple them. In many application scenarios, the products obtained in this way will cause problems such as structural volume redundancy, overweight, and poor functional realization. At the same time, for combined structures, due to process constraints, there are often secondary connections between several parts, resulting in poor structural reliability.

[0004] As the use environment of parts becomes more and more harsh and the requirements for material performance continue to increase, it is difficult for traditional single materials to meet the harsh conditions and operating conditions faced in modern technology. Therefore, it is necessary to introduce new theoretical methods and preparation technologies in the field of materials research to achieve the organic integration of typical product structure functions and improve product performance and application value. Utility Model Content

[0005] In order to solve the above technical problems, the embodiments of the present utility model hope to provide a composite structural part, which can avoid a series of problems caused by separately designing the structural carrier and the functional carrier and then assembling and coupling them.

[0006] The technical solution of the utility model is achieved in this way:

[0007] The present invention provides a composite structural member, the composite structural member comprising:

[0008] a skeleton portion of a first metal material, wherein the skeleton portion defines a void;

[0009] A matrix portion of at least one metallic material, the matrix portion filling the voids of the skeleton portion, wherein each metallic material of the at least one metallic material is different from the first metallic material.

[0010] The embodiment of the utility model provides a composite structural part. Since the base part is filled in the gap of the skeleton part, a series of problems caused by separately designing the structural carrier and the functional carrier and then assembling and coupling them are avoided. On the contrary, what is obtained is a gradient metal material in which the two materials are composited and the composition and structure show a continuous gradient change. Since the composite structural part is an integrated structure, it can not only combine the characteristics of two or more materials, but also achieve the effect of functional composite or organic integration, thereby improving the product performance and application value. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 is a schematic top view of a composite structural member according to an embodiment of the utility model;

[0012] Figure 2 is a three-dimensional schematic diagram of a skeleton portion of a composite structural member according to an embodiment of the utility model;

[0013] Figure 3 for Figure 2 A schematic top view of the skeleton portion shown in FIG.

[0014] Figure 4 is a three-dimensional schematic diagram of a skeleton portion of a composite structural member according to another embodiment of the utility model;

[0015] Figure 5 for Figure 4 A schematic top view of the skeleton portion shown in FIG.

[0016] Figure 6 is a schematic top view of a skeleton portion of a composite structural member according to another embodiment of the utility model;

[0017] Figure 7 is a schematic top view of a skeleton portion of a composite structural member according to another embodiment of the utility model;

[0018] Figure 8 is a three-dimensional schematic diagram of a partial unit of a skeleton portion of a composite structural member according to another embodiment of the utility model;

[0019] Fig. 9 is a three-dimensional schematic diagram of a partial unit of a skeleton portion of a composite structural member according to another embodiment of the utility model;

[0020] Fig.10 is a front view schematic diagram of a skeleton portion of a composite structural member according to another embodiment of the utility model;

[0021] Fig.11 It is a schematic diagram of a method for preparing a composite structural member according to an embodiment of the present utility model. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the accompanying drawings in the embodiments of the present invention.

[0023] See also Figure 1 The present utility model embodiment provides a composite structural member 1, and the composite structural member 1 may include:

[0024] The skeleton part 10 of the first metal material, such as Figure 1 As schematically shown by black lines in FIG. 1 , the skeleton portion 10 defines a gap S, as shown in FIG. Figure 1 As shown in FIG. 1 , the skeleton portion 10 defines a grid-shaped gap. In addition, the skeleton portion 10 can be obtained, for example, by laser selective melting technology, which will be described in more detail below.

[0025] A base portion 20 of at least one metal material is filled in the gap S of the skeleton portion 10, such as in Figure 1 In the area filled with dots, more specifically, Figure 1 The figure exemplarily shows a base part 20 of two metal materials, where the two metal materials are represented by the different densities of the filled points, wherein each of the at least one metal material is different from the first metal material. In addition, the base part 20 can be obtained, for example, by laser stereo forming technology, which will be described in more detail below.

[0026] For the composite structural part 1 according to the embodiment of the utility model, since the base part 20 is filled in the gap S of the skeleton part 10, a series of problems caused by separately designing the structural carrier and the functional carrier and then assembling and coupling them are avoided. On the contrary, what is obtained is a gradient metal material in which two materials are composited and the composition and structure show a continuous gradient change. Specifically, the structural load-bearing and the possible sealing effect can be achieved by the skeleton part 10. In addition, the design goals of the structural load-bearing include but are not limited to strength, stiffness, vibration characteristics, etc., and functions such as thermal conductivity, thermal insulation, electrical conductivity, flame retardancy, and energy absorption can be achieved by the base part 20. Since the composite structural part 1 is an integrated structure, it can not only combine the characteristics of two or more materials, but also achieve the effect of functional composite or organic integration, thereby improving the product performance and application value. Such gradient metal materials are very suitable for application in high-tech fields such as the aerospace industry.

[0027] In some examples of the present invention, the skeleton portion 10 may be formed of a lattice-like frame, which will be described in detail below in conjunction with specific embodiments.

[0028] For the lattice frame, it can be composed of sheets, such as Figures 2 to 7 As shown in FIG. 1 , it can also be composed of a rod-shaped member, such as in FIG. Figure 8 and Fig. 9 As shown in .

[0029] First combine Figure 2 and Figure 3 The lattice-shaped frame composed of sheet materials is described. For workpieces in the mechanical field, some workpieces mainly bear pressure loads in the thickness direction. In this regard, in the preferred embodiment of the utility model, see Figure 2 and Figure 3 The skeleton portion 10 may include a hexagonal honeycomb structure 11 , and the channels 11P of the hexagonal honeycomb structure 11 are parallel to the thickness direction TD of the composite structural member 1 .

[0030] In this way, the requirement that the composite structural member 1 bears pressure load in the thickness direction can be met. More specifically, the boundary and wall thickness of the honeycomb structure 11 can be determined as needed. In addition, the base part 20 of the composite structural member 1 can be made of lightweight metal material in combination with the lightweight design principle.

[0031] In addition, it should be noted that Figure 2 and Figure 3 As shown in FIG. 1 , the skeleton part 10 includes not only the hexagonal honeycomb structure 11 but also the outer shell 14, that is, the skeleton part 10 can be composed of the outer shell 14 and the lattice frame inside the outer shell 14. In this way, the outer shell 14 can produce a sealing effect, which can facilitate the base part 20 of the composite structural member 1 to be obtained by casting, for example.

[0032] It should be noted that, although not shown in the drawings, it is understandable that Figure 2 and Figure 3 The skeleton portion 10 shown in FIG. 1 may not include the hexagonal honeycomb structure 11 , that is, the skeleton portion 10 may be constituted by the outer shell 14 .

[0033] Secondly, combine Figure 4 and Figure 5 A lattice-shaped frame composed of sheet materials is described. For workpieces in the mechanical field, some workpieces need to withstand pressure loads in the length direction and the width direction in addition to the pressure load in the thickness direction. In addition, the workpieces are required to have a certain degree of flexibility in the length direction and the width direction. In this regard, in the preferred embodiment of the utility model, see Figure 4 and Figure 5 , the skeleton portion 10 may include:

[0034] A plurality of first sheets 12 , wherein the plurality of first sheets 12 are parallel to each other and to a thickness direction TD of the composite structural member 1 ;

[0035] a plurality of second sheets 13, wherein the plurality of second sheets 13 are parallel to each other and to the thickness direction TD of the composite structural member 1,

[0036] The first sheets 12 and the second sheets 13 are interwoven and perpendicular to each other, and

[0037] Among them, in the cross section perpendicular to the thickness direction TD of the composite structural member 1, such as in Figure 5 As shown in FIG. 1 , each of the plurality of first sheets 12 and the plurality of second sheets 13 is in a sinusoidal corrugated shape.

[0038] In this way, the composite structural member 1 can withstand pressure loads in the length and width directions in addition to the pressure loads in the thickness direction, and can also meet the requirement that the composite structural member 1 has certain flexibility in the length and width directions. More specifically, similarly, the common boundaries and thicknesses of the plurality of first sheets 12 and the plurality of second sheets 13 can be determined as needed. In addition, the plurality of first sheets 12 and the plurality of second sheets 13 can be evenly distributed or the spacing between each two adjacent sheets is equal. Finally, the base portion 20 of the composite structural member 1 can be made of lightweight metal materials in combination with the lightweight design principle.

[0039] Then combine Figure 8 Describes a lattice-like frame made of rod-like members. Figure 8 The skeleton part 10 may include a first frame 15, which is formed by connecting every two adjacent points in a BCC body-centered cubic lattice. It should be noted that: Figure 8 Only a single partial unit of the first frame 15 is shown in FIG. 1 , that is, the first frame 15 may be composed of an array of such single partial units.

[0040] Finally combined Fig. 9 Describes a lattice-like frame made of rod-like members. Fig. 9 The skeleton part 10 may include a second frame 16, which is formed by connecting every two adjacent points in the FCC dodecahedron face-centered cubic lattice. It should be noted that Fig. 9 Only a single partial unit of the second frame 16 is shown in FIG. 1 , that is, the second frame 16 may be composed of an array of such single partial units.

[0041] In some examples of the present invention, the lattice-like frame may be composed of rod-like members and sheets.

[0042] In some examples of the present invention, at least a portion of the skeleton portion 10 is hollow, such as in Figure 6 and Figure 7 As shown in FIG. 1 , there is a medium channel such as a coolant inside the composite structure 1. When the composite structure 1 is subjected to high temperature, the temperature can be reduced by the circulation of the medium. In this case, the base part 20 can be made of a material with high thermal conductivity to promote heat conduction. On the other hand, the hollow area of ​​the hollow skeleton part 10 itself can also serve as the above-mentioned gap S, and the base part 20 can be filled in the hollow area of ​​the skeleton part 10 itself. In this case, see Figure 6 and Figure 7 It is easy to understand that the obtained composite structural member 1 may include a relatively large hollow area.

[0043] The hollow skeleton part 10 can be obtained by a shelling process.

[0044] In some examples of the present invention, the at least one portion of the hollow part is open or closed. Specifically, when the at least one portion of the hollow part is open, it is convenient to inject powder into the hollow part for powder metallurgy, so that the base part 20 is filled into the gap S of the skeleton part 10, and when the at least one portion of the hollow part is closed, elastic properties can be provided.

[0045] The following will combine Fig.10 , such a skeleton part 10 is described: the skeleton part 10 is composed of a shell 14 and a lattice-like frame inside the shell 14, the lattice-like frame is composed of rod-like members and sheets, and at least a part of the skeleton part 10 is hollow.

[0046] For workpieces in the mechanical field, some workpieces need to bear the functions of buffering, heat insulation and vibration reduction. In addition, the stiffness needs to be continuous and the outer layer needs to have a protective function. In this regard, in the preferred embodiment of the utility model, see Fig.10 , the skeleton portion 10 may include:

[0047] A first skin 17 and a second skin 18 respectively located at two sides of the composite structure 1 in the thickness direction TD, that is, the outer shell 14 of the skeleton part 10 mentioned above;

[0048] A hollow interlayer 19 located at the center of the composite structural member 1 in the thickness direction TD of the composite structural member 1, namely, the sheet material of the lattice-like frame mentioned above;

[0049] A first frame 15 or a second frame 16 between the first skin 17 and the hollow interlayer 19, wherein the first frame 15 is formed by connecting every two adjacent points in a BCC body-centered cubic lattice, and the second frame 16 is formed by connecting every two adjacent points in a FCC dodecahedron face-centered cubic lattice, i.e., the rod-shaped members of the above-mentioned lattice-shaped frame;

[0050] The first frame 15 or the second frame 16 between the second skin 18 and the hollow interlayer 19 .

[0051] For the composite structural member 1 including the skeleton part 10 according to the above embodiment, the hollow interlayer 19 can play the role of buffering, heat insulation and vibration reduction, the first skin 17 and the second skin 18 can provide continuous rigidity and external protection functions, and the first frame 15 or the second frame 16 can play the role of strengthening the rigidity of the first skin 17 and the second skin 18. In addition, the first frame 15 or the second frame 16 can be made of lightweight materials, and the base part 20 can be made of lightweight and high-strength materials to meet the requirements of lightweight and high-strength performance of the composite structural member 1.

[0052] See also Fig.11 Combined with Figure 1 The present utility model embodiment also provides a method for preparing a composite structural member 1, which may include:

[0053] S111: manufacturing a skeleton portion 10 of a first metal material by using a three-dimensional forming process, wherein the skeleton portion 10 defines a gap S;

[0054] S112: Filling the base portion 20 of at least one metal material into the void S of the skeleton portion 10 using a process suitable for forming in the void, wherein each metal material of the at least one metal material is different from the first metal material.

[0055] The three-dimensional forming process mentioned above may be, for example, a selective laser melting process, a selective electron beam melting process, and a 3D printing process.

[0056] The above-mentioned process suitable for forming in the gap may be, for example, a laser stereo forming process, a powder metallurgy process, a casting process, a die-casting process, and a hot isostatic pressing process.

[0057] For obtaining the skeleton part 10, it is advantageous to adopt the selective laser melting process, because for the composite structure 1, it is necessary to meet the requirements of repeated normal operation under extreme environments, and the design requirements of the material vary with the function, performance, and usage location. Selective laser melting has a high degree of freedom in structural design, and at the same time has the characteristics of short cycle and high precision. It can quickly design and iterate skeleton parts 10 of different shapes and sizes.

[0058] More specifically, manufacturing the skeleton part 10 of the first metal material by using the selective laser melting process may include:

[0059] The model of the preset skeleton part 10 is processed using three-dimensional model processing software;

[0060] Magics software was used to add support to the model to meet the conditions for selective laser melting;

[0061] A skeleton portion 10 is formed by using a selective laser melting device according to the model;

[0062] The formed frame portion 10 is subjected to post-processing.

[0063] More specifically, filling the base part 20 of the at least one metal material in the gap S of the skeleton part 10 by using a powder metallurgy process may include:

[0064] Filling the powder of the at least one metal material into the gap S of the skeleton part 10;

[0065] Pre-pressing the filled powder to compact the powder;

[0066] The compacted powder is sintered into the base portion 20 by hot pressing.

[0067] Or more specifically, using a powder metallurgy process to fill the base part 20 of the at least one metal material in the gap S of the skeleton part 10 may include:

[0068] Filling the powder of the at least one metal material into the gap S of the skeleton part 10;

[0069] The filled powder is vibrated and compacted;

[0070] The reserved powder filling port is vacuum welded to seal the powder inside the skeleton part 10;

[0071] The powder is sintered into the base portion 20 by hot isostatic pressing.

[0072] In a preferred embodiment of the present invention, the melting point of the skeleton portion 10 may be higher than the melting point of the base portion 20 .

[0073] Thus, it is possible to avoid damage to the skeleton portion 10 due to high temperature during the process of obtaining the base portion 20 filled in the gap S of the skeleton portion 10.

[0074] In a preferred embodiment of the present invention, the density of the skeleton portion 10 may be higher than the density of the base portion 20 .

[0075] In a specific example, to obtain a Figure 2 and Figure 3 Taking the composite structure 1 of the skeleton part 10 shown in the figure as an example, the skeleton part 10 can be made of TC4 titanium alloy material, and the base part 20 of the composite structure 1 can be made of AlSi10Mg aluminum alloy material, and the TiC4 / AlSi10Mg gradient metal material is prepared by selective laser melting technology combined with powder metallurgy. The prepared TiC4 / AlSi10Mg gradient metal material has the characteristics of low density and good thermal conductivity of aluminum alloy, and high strength and excellent performance of titanium alloy. The specific method is as follows:

[0076] First, the model of the preset skeleton part 10 is processed by three-dimensional model processing software, and Magics software is used to support the model to meet the conditions of selective laser melting. Secondly, the skeleton part 10 is formed by selective laser melting equipment, and the skeleton part 10 is post-processed after forming. Finally, AlSi10Mg powder is filled in the obtained titanium alloy skeleton part 10, and after filling, it is pre-pressed in a suitable mold to compact the powder. The pre-pressing can be carried out at a pressure of 5MPa to 10MPa for 5min to 10min, and finally the compacted powder is sintered into the matrix part 20 by hot pressing sintering, thereby preparing a composite structural part 1 of TiC4 / AlSi10Mg gradient metal material.

[0077] The surface roughness of the titanium alloy parts is controlled by adjusting the selective laser melting process parameters, so that the AlSi10Mg powder and the titanium alloy parts are more easily combined, and the hot pressing process parameters are adjusted to ensure the bonding quality of TiC4 and AlSi10Mg. The hot pressing sintering process parameters include sintering atmosphere, sintering pressure, sintering temperature, sintering time, etc. During hot pressing sintering, the sintering atmosphere can be Ar gas or vacuum environment, the sintering pressure is 30MPa to 60MPa, the sintering temperature is 600℃ to 900℃, and the sintering time is 3min to 120min.

[0078] The prepared TiC4 / AlSi10Mg gradient metal material was heat treated, and the bonding quality and organization of the prepared TiC4 / AlSi10Mg gradient metal material were evaluated by metallographic microscope and scanning electron microscope. In particular, the organization of the TiC4 / AlSi10Mg bonding point was analyzed to characterize the evolution law of the material precipitation phase, and the hardness, room temperature and high temperature tensile properties of the well-bonded TiC4 / AlSi10Mg gradient metal material were evaluated to obtain the corresponding relationship between the organization and the performance.

[0079] In another specific example, to obtain a Figure 6Taking the composite structure 1 of the skeleton part 10 shown in the figure as an example, the skeleton part 10 can be made of In 718 high temperature alloy material, and the base part 20 of the composite structure 1 can be made of TC4 titanium alloy material, and the In 718 / TC4 gradient metal material is prepared by selective laser melting technology combined with powder metallurgy. The prepared In 718 / TC4 gradient metal material has the characteristics of low density of titanium alloy and high strength and excellent high temperature performance of high temperature alloy. The specific method is as follows:

[0080] First, the model of the preset skeleton part 10 is processed by three-dimensional model processing software, and the model is supported by Magics software to meet the conditions of selective laser melting. Secondly, the skeleton part 10 is formed by selective laser melting equipment, and the skeleton part 10 is post-processed after forming. Finally, TC4 powder is filled in the obtained In 718 high-temperature alloy skeleton part 10, and the powder is vibrated after filling. Then, the reserved powder filling port is vacuum welded to seal the powder inside the skeleton part 10, and finally the powder is sintered by hot isostatic pressing to prepare In 718 / TC4 gradient metal material. The process parameters of hot isostatic pressing include sintering atmosphere, sintering pressure, sintering temperature, sintering time, etc. When hot isostatic pressing is performed, the sintering atmosphere is Ar gas or vacuum atmosphere, the sintering pressure is 100MPa to 200MPa, the sintering temperature is 900℃ to 1100℃, and the sintering time is 60min to 180min.

[0081] The surface roughness of In 718 high-temperature alloy parts is controlled by adjusting the selective laser melting process parameters, making it easier to combine TC4 powder and In 718 high-temperature alloy parts. At the same time, the hot isostatic pressing process parameters are adjusted to ensure the bonding quality of TC4 and In718.

[0082] The prepared In 718 / TC4 gradient metal material was heat treated, and the bonding quality and organization of the prepared In 718 / TC4 gradient metal material were evaluated by metallographic microscope and scanning electron microscope. In particular, the organization of the In 718 / TC4 joint was analyzed to characterize the evolution law of the material precipitation phase, and the hardness, room temperature and high temperature tensile properties of the well-bonded In 718 / TC4 gradient metal material were evaluated to obtain the corresponding relationship between organization and performance.

[0083] In another specific example, to obtain a Figure 4 and Figure 5Taking the composite structure 1 of the skeleton part 10 shown in the figure as an example, the skeleton part 10 can be made of 316L stainless steel material, and the base part 20 of the composite structure 1 can be made of TC4 titanium alloy material, and the 316L / TC4 gradient metal material is prepared by selective laser melting technology combined with powder metallurgy. The prepared 316L / TC4 gradient metal material has the characteristics of good heat resistance and corrosion resistance of stainless steel, and also has the characteristics of light density and excellent performance of titanium alloy. The specific method is as follows:

[0084] First, the model of the preset skeleton part 10 is processed by three-dimensional model processing software, and Magics software is used to support the model to meet the conditions of selective laser melting. Secondly, the skeleton part 10 is formed by selective laser melting equipment, and the skeleton part 10 is post-processed after forming. Finally, TC4 metal powder is used as raw material, and the 316L part prepared by selective laser melting technology is remanufactured by laser stereo forming technology to prepare 316L / TC4 gradient metal material.

[0085] The surface roughness of 316L stainless steel parts is controlled by adjusting the selective laser melting process parameters, making it easier for TC4 powder to combine with the stainless steel parts. At the same time, the SLF process parameters are adjusted to ensure the bonding quality of 316L and TC4.

[0086] The prepared 316L / TC4 gradient metal material was heat treated, and the bonding quality and organization of the prepared 316L / TC4 gradient metal material were evaluated by metallographic microscope and scanning electron microscope. In particular, the organization of the 316L / TC4 joint was analyzed to characterize the evolution law of the material precipitation phase, and the hardness, room temperature and high temperature tensile properties of the well-bonded 316L / TC4 gradient metal material were evaluated to obtain the corresponding relationship between organization and performance.

[0087] In another specific example, to obtain a Figure 7 Taking the composite structure 1 of the skeleton part 10 shown in the figure as an example, the skeleton part 10 can be made of tungsten metal material, and the base part 20 of the composite structure 1 can be made of copper alloy material, and the W / Cu gradient metal material is prepared by selective laser melting technology combined with powder metallurgy. The prepared W / Cu gradient metal material has the characteristics of high melting point and high hardness, and also has the characteristics of excellent thermal and electrical conductivity of copper alloy. The specific method is as follows:

[0088] First, the model of the preset skeleton part 10 is processed using 3D model processing software, and the model is supported using Magics software to meet the conditions of selective laser melting. Secondly, the skeleton part 10 is formed using a selective laser melting device, and the skeleton part 10 is post-processed after the forming is completed. Finally, the copper alloy metal liquid is cast into the pure tungsten part obtained by the selective laser melting technology to prepare a W / Cu gradient metal material.

[0089] The surface roughness of pure tungsten parts is controlled by adjusting the selective laser melting process parameters, making it easier for the copper alloy molten metal to combine with the pure tungsten parts. At the same time, the casting process parameters are adjusted to ensure the bonding quality of the pure tungsten parts and the copper alloy.

[0090] The prepared W / Cu gradient metal material was heat treated, and the bonding quality and organization of the prepared W / Cu gradient metal material were evaluated by metallographic microscope and scanning electron microscope. In particular, the organization of the W / Cu bonding point was analyzed to characterize the evolution law of the material precipitation phase, and the hardness, room temperature and high temperature tensile properties of the well-bonded W / Cu gradient metal material were evaluated to obtain the corresponding relationship between the organization and performance.

[0091] In another specific example, to obtain a Fig.10 Taking the composite structure 1 of the skeleton part 10 shown in the figure as an example, the skeleton part 10 can be made of GH3536 high temperature alloy material, and the base part 20 of the composite structure 1 can be made of AlSi10Mg aluminum alloy material, and the GH3536 / AlSi10Mg gradient metal material is prepared by selective laser melting technology combined with casting technology. The prepared GH3536 / AlSi10Mg gradient metal material has the characteristics of low density and good thermal conductivity of aluminum alloy, and high strength and excellent performance of high temperature alloy. The specific method is as follows:

[0092] First, the model of the preset skeleton part 10 is processed by three-dimensional model processing software, and the model is supported by Magics software to meet the conditions of selective laser melting. Secondly, the skeleton part 10 is formed by selective laser melting equipment, and the skeleton part 10 is post-processed after forming. Finally, the molten metal of AlSi10Mg aluminum alloy is cast into the GH3536 part obtained by selective laser melting technology to prepare GH3536 / AlSi10Mg gradient metal material.

[0093] The surface roughness of GH3536 parts is controlled by adjusting the selective laser melting process parameters, making it easier for the AlSi10Mg aluminum alloy liquid to combine with the GH3536 parts. At the same time, the casting process parameters are adjusted to ensure the bonding quality of pure GH3536 parts and AlSi10Mg aluminum alloy.

[0094] The prepared GH3536 / AlSi10Mg gradient metal material was heat treated, and the bonding quality and organization of the prepared GH3536 / AlSi10Mg gradient metal material were evaluated by metallographic microscope and scanning electron microscope. In particular, the organization of the GH3536 / AlSi10Mg bonding site was analyzed to characterize the evolution law of the material precipitation phase, and the hardness, room temperature and high temperature tensile properties of the well-bonded GH3536 / AlSi10Mg gradient metal material were evaluated to obtain the corresponding relationship between organization and performance.

[0095] It should be noted that the technical solutions described in the embodiments of the present utility model can be combined arbitrarily without conflict.

[0096] The above is only a specific implementation of the utility model, but the protection scope of the utility model is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed by the utility model, which should be included in the protection scope of the utility model. Therefore, the protection scope of the utility model should be based on the protection scope of the claims.

Claims

1. A composite structural part, characterized in that: The composite structural member comprises: a skeleton portion of a first metal material, wherein the skeleton portion defines a void; A matrix portion of at least one metallic material, the matrix portion filling the voids of the skeleton portion, wherein each metallic material of the at least one metallic material is different from the first metallic material.

2. The composite structural member according to claim 1, characterized in that: The skeleton portion is formed by an outer shell.

3. The composite structural member according to claim 1, characterized in that: The skeleton part is composed of a lattice-like frame.

4. The composite structural member according to claim 1, characterized in that: The skeleton part is composed of an outer shell and a lattice-shaped frame inside the outer shell.

5. The composite structural member according to claim 3 or 4, characterized in that: The lattice-like frame is composed of rod-like members.

6. The composite structural member according to claim 3 or 4, characterized in that: The lattice-like frame is composed of sheet materials.

7. The composite structural member according to claim 3 or 4, characterized in that: The lattice-like frame is composed of rod-like members and sheets.

8. The composite structural member according to any one of claims 1 to 4, characterized in that: At least a portion of the skeleton portion is hollow.

9. The composite structural member according to claim 8, characterized in that: The at least one portion of the hollow space is open or closed.

10. The composite structural member according to claim 1, characterized in that: The melting point of the skeleton portion is higher than the melting point of the base portion.

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