Metal wire rod for aerospace engineering and preparation method thereof

Abstract

The invention discloses a metal wire for aerospace engineering, and the metal wire comprises a core layer which is made of a high-purity metal material and is used for guaranteeing the basic conductivity or other specific physical properties of the metal wire; the middle reinforcing layer is arranged on the outer surface of the core layer, the middle reinforcing layer is an alloy layer produced and manufactured by containing various alloy elements, and high strength and good anti-fatigue performance are provided for the metal wire rod through a specific alloy proportion; the outer layer is arranged on the outer surface of the middle reinforcing layer. The preparation method of the metal wire rod for aerospace engineering is characterized by comprising the following steps of S1, core layer preparation, S2, middle reinforcing layer preparation, S3, outer layer preparation, S4, composite forming and S5, subsequent processing treatment.

Description

Technical Field

[0001] This invention belongs to the field of metal materials technology, specifically relating to a metal wire for aerospace engineering and its preparation method. Background Technology

[0002] In aerospace engineering, metal wires are widely used in many critical systems and components of spacecraft. For example, in the structural connection parts of spacecraft, metal wires are used to manufacture rivets, bolts and other connectors to ensure the stability of the structure. In the wiring system of electronic equipment, they serve as wires to bear the important task of power transmission and signal transmission. In the propulsion system, they are also used to manufacture some key sealing components and control elements. Given the extremely complex and harsh environment of aerospace engineering, such as high vacuum, strong radiation, large temperature changes (from the extremely cold temperature of space to the high temperature when re-entering the atmosphere), and the need to withstand huge mechanical stress, extremely stringent requirements are placed on the performance of metal wires used in aerospace engineering.

[0003] However, existing aerospace engineering metal wires have a single homogeneous structure, which makes it difficult to meet multiple performance requirements simultaneously when facing complex and ever-changing aerospace conditions. For example, in some applications that require high conductivity and high tensile strength, the strength of a single-structure metal wire is often insufficient if high-purity metal is selected to improve conductivity. If alloying elements are added to change the structure to enhance strength, the conductivity will be affected. Moreover, the internal structure of existing metal wires is not uniform and has microscopic defects such as pores and inclusions. This can lead to stress concentration under stress, reducing the fatigue life and tensile strength of the material. In aerospace, where reliability requirements are extremely high, this poses a great safety hazard. Therefore, there is an urgent need for aerospace engineering metal wire and its preparation method to solve the above problems. Summary of the Invention

[0004] In view of the problems raised in the background art above, the purpose of this invention is to provide a metal wire for aerospace engineering and a method for preparing the same.

[0005] To achieve the above-mentioned technical objectives, the technical solution adopted by the present invention is as follows:

[0006] A metal wire for aerospace engineering, comprising:

[0007] The core layer is made of high-purity metal material and is used to ensure the basic electrical conductivity or other specific physical properties of the metal wire.

[0008] An intermediate reinforcement layer is disposed on the outer surface of the core layer. The intermediate reinforcement layer is an alloy layer made of multiple alloying elements, which provides high strength and good fatigue resistance to the metal wire through a specific alloy ratio.

[0009] The outer layer is disposed on the outer surface of the intermediate reinforcing layer.

[0010] Furthermore, the high-purity metal in the core layer is one or a combination of high-purity copper, silver, and aluminum, with a purity of not less than 99.9%. This structural design results in extremely low resistance, ensuring efficient current transmission, reducing energy loss, effectively minimizing signal attenuation during transmission, and ensuring signal accuracy and stability.

[0011] Further specifying, the alloying elements of the intermediate reinforcing layer include, but are not limited to, chromium, titanium, magnesium, niobium, and zirconium, with the following mass percentages: chromium 0.5%–2%, titanium 0.1%–1%, magnesium 0.2%–1.5%, niobium 0.05%–0.8%, zirconium 0.05%–0.6%, and the remainder being the base metal. This structural design, through precise proportioning of alloying elements, can form a dispersed reinforcing phase within the base metal. For example, the intermetallic compound formed by chromium and the base metal can hinder dislocation movement, thereby significantly improving the strength of the metal wire. Simultaneously, these alloying elements can also improve the crystal structure of the metal, refine the grains, and enhance the material's fatigue resistance.

[0012] Furthermore, the outer layer is made of a material that is nickel-plated, zinc-plated, or coated with a special anti-corrosion coating. This structural design effectively blocks external corrosion and protects the internal structure.

[0013] Furthermore, the outer surface is smoothed, with a surface roughness Ra not exceeding 0.1 μm. This structural design reduces frictional resistance during use and improves performance during high-frequency signal transmission.

[0014] Furthermore, the core layer, intermediate reinforcing layer, and outer layer are tightly connected as a whole through metallurgical bonding, and the thickness ratio of each layer is core layer thickness: intermediate reinforcing layer thickness: outer layer thickness = 3:4:3. This structural design enables strong interatomic bonding between the layers, preventing delamination during use, while adjusting the thickness ratio of each layer to achieve optimal performance balance.

[0015] A method for preparing metal wire for aerospace engineering, characterized by comprising the following steps:

[0016] S1: Core layer preparation. High-purity metal raw materials are selected, including one or more combinations of copper, silver, and aluminum, with a purity of not less than 99.9%. The selected high-purity metal raw materials are placed in a vacuum melting furnace for vacuum melting. The melting temperature is determined according to the type of metal: the melting temperature for high-purity copper is controlled at 1100–1200℃, for high-purity silver at 960–1000℃, and for high-purity aluminum at 660–700℃. During the melting process, the vacuum degree is maintained at 10⁻³ Pa to 10⁻³ Pa. -7 Pa is used to reduce the mixing of gases and impurities. After smelting, the molten metal is cast using a continuous casting process with the casting speed controlled at 0.5 to 2 m / min to obtain the core layer billet.

[0017] S2: Preparation of the intermediate reinforcement layer. Raw materials are selected according to the alloy element ratio of the intermediate reinforcement layer. The alloy elements include chromium, titanium, magnesium, niobium, zirconium, etc., with the following mass percentages: chromium 0.5%–2%, titanium 0.1%–1%, magnesium 0.2%–1.5%, niobium 0.05%–0.8%, zirconium 0.05%–0.6%, and the remainder being base metals. The selected raw materials are placed in a vacuum melting furnace for melting, with the melting temperature controlled at 1150–1250℃, while maintaining a vacuum degree of 10. -3 Pa~10 -7 Pa ensures that impurities are reduced during the melting process. After melting, casting is carried out using directional solidification process. The drawing speed of directional solidification is controlled at 5-20 mm / min to obtain the intermediate reinforcement layer billet. The intermediate reinforcement layer billet is rolled or drawn to make it into a tubular structure that can wrap the core layer. The inner diameter of the tube matches the outer diameter of the core layer billet.

[0018] S3: Outer layer preparation. Nickel-plated, zinc-plated, or special anti-corrosion coating materials are selected. When using a plating method, the outer surface of the intermediate reinforcing layer is first pretreated, including degreasing and rust removal. Then, electroplating or chemical plating is performed. The electroplating current density is controlled between 1 and 5 A / dm². 2 The plating time is 10–60 minutes to ensure uniform coating thickness.

[0019] S4: Composite forming involves inserting the core layer blank into the tubular blank of the intermediate reinforcing layer, ensuring concentricity. The assembled blank is then placed in a vacuum diffusion welding furnace for metallurgical bonding. The welding temperature is 0.6–0.8 times the metal melting point, the holding time is 1–4 hours, and the vacuum degree is not less than 10. -4 Pa, which enables the core layer and the intermediate reinforcement layer to form a strong metallurgical bond, and the outer layer is formed on the outer surface of the intermediate reinforcement layer by means of plating, etc.

[0020] S5: Subsequent processing involves drawing the composite-formed metal wire to achieve the required diameter. During the drawing process, the drawing speed and deformation are controlled to ensure stable wire performance. The drawn metal wire is then annealed at a temperature of 300–500°C for 1–3 hours to eliminate processing stress.

[0021] The beneficial effects of this invention are as follows:

[0022] 1. This invention employs a unique core layer, intermediate reinforcement layer, and outer layer structure design. The high-purity metal of the core layer ensures basic electrical conductivity and other physical properties, the alloy design of the intermediate reinforcement layer provides high strength and fatigue resistance, and the functional outer layer enhances environmental adaptability and connection stability. Compared with traditional single-structure metal wires, this invention significantly improves electrical conductivity, mechanical properties, and environmental adaptability, and can better meet the complex needs of aerospace engineering.

[0023] 2. This invention employs processes such as vacuum melting and directional solidification, effectively reducing the ingress of gases and impurities into the metal wire, improving the purity and uniformity of the material, and ensuring the stability of the wire's performance. Vacuum diffusion welding achieves metallurgical bonding between the core layer, intermediate reinforcing layer, and outer layer, forming a strong interatomic bond between each layer. This prevents delamination during use, improves the overall strength and reliability of the metal wire, and guarantees the conductivity of the core layer, the high strength and fatigue resistance of the intermediate reinforcing layer, and the protective and auxiliary functions of the outer layer. This results in excellent comprehensive performance of the metal wire, meeting the stringent requirements of aerospace engineering. Attached Figure Description

[0024] The present invention can be further illustrated by the non-limiting embodiments given in the accompanying drawings;

[0025] Figure 1 This is a schematic diagram of the cross-sectional structure of a metal wire for aerospace engineering according to an embodiment of the present invention;

[0026] The symbols for the main components are explained below:

[0027] Core layer 1, intermediate reinforcement layer 2, outer layer 3. Detailed Implementation

[0028] To enable those skilled in the art to better understand the present invention, the technical solution of the present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0029] like Figure 1 As shown, an aerospace engineering metal wire of the present invention comprises:

[0030] Core layer 1 is made of high-purity metal material and is used to ensure the basic conductivity or other specific physical properties of the metal wire.

[0031] Intermediate reinforcement layer 2 is disposed on the outer surface of core layer 1. Intermediate reinforcement layer 2 is an alloy layer made of multiple alloying elements, which provides high strength and good fatigue resistance to metal wire through a specific alloy ratio.

[0032] Outer layer 3 is disposed on the outer surface of the intermediate reinforcing layer 2.

[0033] Preferably, the high-purity metal of the core layer 1 is one or a combination of high-purity copper, silver, and aluminum, with a purity of not less than 99.9%. This structural design gives it extremely low resistance, ensuring efficient current transmission, reducing energy loss, effectively reducing signal attenuation during transmission, and ensuring signal accuracy and stability.

[0034] Preferably, the alloying elements of the intermediate reinforcing layer 2 include, but are not limited to, chromium, titanium, magnesium, niobium, and zirconium, with the following mass percentages: chromium 0.5%–2%, titanium 0.1%–1%, magnesium 0.2%–1.5%, niobium 0.05%–0.8%, zirconium 0.05%–0.6%, and the remainder being the base metal. This structural design, through precise proportioning of alloying elements, enables the formation of dispersed reinforcing phases within the base metal. For example, the intermetallic compound formed by chromium and the base metal can hinder dislocation movement, thereby significantly improving the strength of the metal wire. Simultaneously, these alloying elements can also improve the crystal structure of the metal, refine the grains, and enhance the material's fatigue resistance.

[0035] Preferably, the outer layer 3 is made of a material that is nickel-plated, zinc-plated, or coated with a special anti-corrosion coating. This structural design can effectively block external corrosion and protect the internal structure.

[0036] Preferably, the outer layer 3 surface is smoothed, with a surface roughness Ra not exceeding 0.1 μm. This structural design reduces frictional resistance during use and improves its performance in high-frequency signal transmission.

[0037] Preferably, the core layer 1, the intermediate reinforcing layer 2, and the outer layer 3 are tightly connected to form a whole through metallurgical bonding, and the thickness ratio of each layer is core layer thickness: intermediate reinforcing layer thickness: outer layer thickness = 3:4:3. This structural design enables strong interatomic bonding between the layers, preventing delamination during use, and allows for adjustment of the thickness ratio of each layer to achieve optimal performance balance.

[0038] A method for preparing metal wire for aerospace engineering, characterized by comprising the following steps:

[0039] S1: Core layer preparation. High-purity metal raw materials are selected, including one or more combinations of copper, silver, and aluminum, with a purity of not less than 99.9%. The selected high-purity metal raw materials are placed in a vacuum melting furnace for vacuum melting. The melting temperature is determined according to the type of metal: the melting temperature for high-purity copper is controlled at 1100–1200℃, for high-purity silver at 960–1000℃, and for high-purity aluminum at 660–700℃. During the melting process, the vacuum level is maintained at 10... -3 Pa~10 -7 Pa is used to reduce the mixing of gases and impurities. After smelting, the molten metal is cast using a continuous casting process with the casting speed controlled at 0.5 to 2 m / min to obtain the core layer billet.

[0040] S2: Preparation of the intermediate reinforcement layer. Raw materials are selected according to the alloy element ratio of the intermediate reinforcement layer. The alloy elements include chromium, titanium, magnesium, niobium, zirconium, etc., with the following mass percentages: chromium 0.5%–2%, titanium 0.1%–1%, magnesium 0.2%–1.5%, niobium 0.05%–0.8%, zirconium 0.05%–0.6%, and the remainder being base metals. The selected raw materials are placed in a vacuum melting furnace for melting, with the melting temperature controlled at 1150–1250℃, while maintaining a vacuum degree of 10. -3 Pa~10 -7 Pa ensures that impurities are reduced during the melting process. After melting, casting is carried out using directional solidification process. The drawing speed of directional solidification is controlled at 5-20 mm / min to obtain the intermediate reinforcement layer billet. The intermediate reinforcement layer billet is rolled or drawn to make it into a tubular structure that can wrap the core layer. The inner diameter of the tube matches the outer diameter of the core layer billet.

[0041] S3: Outer layer preparation. Nickel-plated, zinc-plated, or special anti-corrosion coating materials are selected. When using a plating method, the outer surface of the intermediate reinforcing layer is first pretreated, including degreasing and rust removal. Then, electroplating or chemical plating is performed. The electroplating current density is controlled between 1 and 5 A / dm². 2 The plating time is 10–60 minutes to ensure uniform coating thickness.

[0042] S4: Composite forming involves inserting the core layer blank into the tubular blank of the intermediate reinforcing layer, ensuring concentricity. The assembled blank is then placed in a vacuum diffusion welding furnace for metallurgical bonding. The welding temperature is 0.6–0.8 times the metal melting point, the holding time is 1–4 hours, and the vacuum degree is not less than 10. -4 Pa, which enables the core layer and the intermediate reinforcement layer to form a strong metallurgical bond, and the outer layer is formed on the outer surface of the intermediate reinforcement layer by means of plating, etc.

[0043] S5: Subsequent processing involves drawing the composite-formed metal wire to achieve the required diameter. During the drawing process, the drawing speed and deformation are controlled to ensure stable wire performance. The drawn metal wire is then annealed at a temperature of 300–500°C for 1–3 hours to eliminate processing stress.

[0044] Example 1

[0045] Core preparation: High-purity copper with a purity of 99.95% is selected as raw material and placed in a vacuum melting furnace. It is melted at a vacuum degree of 10-3 Pa and a temperature of 1150℃. After melting, a continuous casting process is adopted to obtain a core blank with a diameter of 5mm at a casting speed of 1m / min.

[0046] Preparation of intermediate reinforcing layer: Raw materials were selected according to the mass percentages of 1% chromium, 0.5% titanium, 0.8% magnesium, 0.4% niobium, 0.3% zirconium, and the remainder copper. The raw materials were placed in a vacuum melting furnace and melted at a vacuum degree of 10-3 Pa and a temperature of 1200℃. A directional solidification process was adopted, and a billet was cast at a drawing speed of 10 mm / min. The billet was then rolled into a tubular structure with an inner diameter of 5 mm and an outer diameter of 8 mm.

[0047] Outer layer preparation: Since this metal wire is mainly used for conductive wiring, the outer layer needs to have improved corrosion resistance. Therefore, nickel plating is used. First, the outer surface of the intermediate reinforcing layer is degreased and derusted, and then nickel is electroplated at a current density of 3A / dm. 2 The plating time is 30 minutes, resulting in a nickel plating layer of uniform thickness;

[0048] Composite molding: The core layer blank is inserted into the intermediate reinforcing layer tubular blank and placed in a vacuum diffusion welding furnace at a temperature of 800℃, a holding time of 2 hours, and a vacuum degree of 10. -4 Welding is performed under Pa conditions to bond the core layer and the intermediate reinforcement layer;

[0049] Subsequent processing: The composite wire is drawn to a diameter of 2mm, then annealed at 400℃ for 2 hours, and finally polished to achieve a surface roughness Ra of 0.08μm, thus obtaining a metal wire for wiring in aerospace electronic equipment.

[0050] Example 2

[0051] Core layer preparation: High-purity aluminum with a purity of 99.9% was selected as raw material and vacuum melted at a vacuum degree of 10-3 Pa and a temperature of 680℃. A continuous casting process was adopted to obtain a core layer blank with a diameter of 6 mm at a speed of 0.8 m / min.

[0052] Preparation of intermediate reinforcing layer: Raw materials were selected according to the mass percentages of 1.5% chromium, 0.8% titanium, 1.2% magnesium, 0.6% niobium, 0.5% zirconium, and the remainder being aluminum. The raw materials were melted under vacuum of 10⁻³ Pa and temperature of 750℃, and cast into billets by directional solidification and drawing speed of 15 mm / min. The billets were then rolled into tubular structures with an inner diameter of 6 mm and an outer diameter of 10 mm.

[0053] Outer layer fabrication: To improve the stability of the connection with the wing structure, an active material containing titanium was selected for the outer layer. Titanium was electroplated onto the outer surface of the intermediate reinforcement layer using a current density of 2 A / dm². 2 The plating time is 40 minutes;

[0054] Composite molding: The core layer is inserted into the intermediate reinforcing layer, and then subjected to vacuum diffusion welding in a vacuum diffusion welding furnace at a temperature of 550℃, a holding time of 3 hours, and a vacuum degree of 10. -4 Welding under Pa conditions;

[0055] Subsequent processing: drawn to a diameter of 3 mm, annealed at 350°C for 3 hours, and polished to Ra0.09 μm to obtain metal wire for spacecraft structural connections.

[0056] The above embodiments are merely illustrative of the principles and effects of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in the present invention should still be covered by the claims of the present invention.

Claims

1. A metal wire for aerospace engineering, characterized in that: include: Core layer (1), wherein the core layer (1) is made of high-purity metal material and is used to ensure the basic conductivity or other specific physical properties of the metal wire; Intermediate reinforcement layer (2) is disposed on the outer surface of core layer (1). The intermediate reinforcement layer (2) is an alloy layer made of multiple alloying elements, which provides high strength and good fatigue resistance to metal wire through a specific alloy ratio. The outer layer (3) is disposed on the outer surface of the intermediate reinforcing layer (2).

2. The aerospace engineering metal wire according to claim 1, characterized in that: The high-purity metal of the core layer (1) is one or a combination of high-purity copper, silver and aluminum, with a purity of not less than 99.9%.

3. The aerospace engineering metal wire according to claim 2, characterized in that: The alloying elements of the intermediate reinforcing layer (2) include, but are not limited to, chromium, titanium, magnesium, niobium, zirconium, etc., and the mass percentage of each alloying element is: chromium 0.5% to 2%, titanium 0.1% to 1%, magnesium 0.2% to 1.5%, niobium 0.05% to 0.8%, zirconium 0.05% to 0.6%, and the remainder is base metal.

4. The aerospace engineering metal wire according to claim 3, characterized in that: The outer layer (3) is made of nickel-plated, zinc-plated or coated with a special anti-corrosion coating.

5. The aerospace engineering metal wire according to claim 4, characterized in that: The outer layer (3) surface is smoothed, and the surface roughness Ra does not exceed 0.1 μm.

6. The aerospace engineering metal wire according to claim 5, characterized in that: The core layer (1), the intermediate reinforcing layer (2) and the outer layer (3) are tightly connected to form a whole by metallurgical bonding, and the thickness ratio of each layer is core layer thickness: intermediate reinforcing layer thickness: outer layer thickness = 3:4:

3.

7. A method for preparing aerospace engineering metal wire according to any one of claims 1 to 6, characterized in that: Includes the following steps: S1: Core layer preparation. High-purity metal raw materials are selected, including one or more combinations of copper, silver, and aluminum, with a purity of not less than 99.9%. The selected high-purity metal raw materials are placed in a vacuum melting furnace for vacuum melting. The melting temperature is determined according to the type of metal: the melting temperature for high-purity copper is controlled at 1100–1200℃, for high-purity silver at 960–1000℃, and for high-purity aluminum at 660–700℃. During the melting process, the vacuum level is maintained at 10... -3 Pa~10 -7 Pa is used to reduce the mixing of gases and impurities. After smelting, the molten metal is cast using a continuous casting process with the casting speed controlled at 0.5 to 2 m / min to obtain the core layer billet. S2: Preparation of the intermediate reinforcement layer. Raw materials are selected according to the alloy element ratio of the intermediate reinforcement layer. The alloy elements include chromium, titanium, magnesium, niobium, zirconium, etc., with the following mass percentages: chromium 0.5%–2%, titanium 0.1%–1%, magnesium 0.2%–1.5%, niobium 0.05%–0.8%, zirconium 0.05%–0.6%, and the remainder being base metals. The selected raw materials are placed in a vacuum melting furnace for melting, with the melting temperature controlled at 1150–1250℃, while maintaining a vacuum degree of 10. -3 Pa~10 -7 Pa ensures that impurities are reduced during the melting process. After melting, casting is carried out using directional solidification process. The drawing speed of directional solidification is controlled at 5-20 mm / min to obtain the intermediate reinforcement layer billet. The intermediate reinforcement layer billet is rolled or drawn to make it into a tubular structure that can wrap the core layer. The inner diameter of the tube matches the outer diameter of the core layer billet. S3: Outer layer preparation. Nickel-plated, zinc-plated, or special anti-corrosion coating materials are selected. When using a plating method, the outer surface of the intermediate reinforcing layer is first pretreated, including degreasing and rust removal. Then, electroplating or chemical plating is performed. The electroplating current density is controlled between 1 and 5 A / dm². 2 The plating time is 10–60 minutes to ensure uniform coating thickness. S4: Composite forming involves inserting the core layer blank into the tubular blank of the intermediate reinforcing layer, ensuring concentricity. The assembled blank is then placed in a vacuum diffusion welding furnace for metallurgical bonding. The welding temperature is 0.6–0.8 times the metal melting point, the holding time is 1–4 hours, and the vacuum degree is not less than 10. -4 Pa, which enables the core layer and the intermediate reinforcement layer to form a strong metallurgical bond, and the outer layer is formed on the outer surface of the intermediate reinforcement layer by means of plating, etc. S5: Subsequent processing involves drawing the composite-formed metal wire to achieve the required diameter. During the drawing process, the drawing speed and deformation are controlled to ensure stable wire performance. The drawn metal wire is then annealed at a temperature of 300–500°C for 1–3 hours to eliminate processing stress.

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