KR20240013741A - Aluminum alloy, aluminum alloy wire, and method for manufacturing aluminum alloy wire - Google Patents

Abstract

The aluminum alloy contains 0.6 mass% to 1.5 mass% of silicon, 0.5 mass% to 1.3 mass% of magnesium, 0.1 mass% to 1.2 mass% of copper, and 0.2 mass% to 1.15 mass% of manganese. It has a composition with the remainder containing aluminum and inevitable impurities, and the average value of the orientation degree of the 111 faces obtained by X-ray diffraction of the entire cross section in a state in which solution treatment and aging treatment is performed is 50% or more, and the average value of the orientation of the 111 faces is 50% or more. The dispersion of the degree of orientation is less than 45%.

Description

Aluminum alloy, aluminum alloy wire, and method for manufacturing aluminum alloy wire

The present disclosure relates to aluminum alloy, aluminum alloy wire, and methods for manufacturing aluminum alloy wire.

This application claims priority based on Patent Application No. 2021-089504 of the Japanese application dated May 27, 2021, and uses all of the contents described in the Japanese application.

Patent Document 1 discloses an aluminum alloy wire containing high tensile strength after solution treatment and aging treatment as a wire containing an aluminum alloy containing silicon and magnesium. The aluminum alloy wire can be used as a raw material for aluminum alloy members. The aluminum alloy member is manufactured by subjecting the aluminum alloy wire to predetermined plastic processing and then subjecting it to solution treatment and aging treatment.

Patent Document 1: Japanese Patent Publication No. 2015-124409

The aluminum alloy of the present disclosure contains 0.6 mass% or more and 1.5 mass% or less of silicon, 0.5 mass% or more and 1.3 mass% or less of magnesium, 0.1 mass% or more and 1.2 mass% or less of copper, and 0.2 mass% or more and 1.15 mass% or less of manganese. and the balance includes aluminum and unavoidable impurities. In a state in which solution treatment and aging treatment are performed, the average value of the orientation degree of the 111 planes obtained by X-ray diffraction of the entire cross section is 50% or more, and the dispersion of the orientation degree of the 111 planes is 45% or less.

The aluminum alloy wire of the present disclosure includes the aluminum alloy of the present disclosure.

The method for manufacturing an aluminum alloy wire of the present disclosure includes 0.6 mass% to 1.5 mass% of silicon, 0.5 mass% to 1.3 mass% of magnesium, 0.1 mass% to 1.2 mass% of copper, and 0.2 mass% to 1.15 mass% of manganese. A process of manufacturing a workpiece by subjecting a cast material of an aluminum alloy having a composition containing not more than % by mass, the balance of which includes aluminum and inevitable impurities, to plastic working, and subjecting the workpiece to a first cold drawing process, thereby first drawing the workpiece. A process for producing ash, a process for producing a softened material by subjecting the first wire material to a softening treatment, and a process for producing a second wire material by subjecting the softened material to a second cold drawing process. . The degree of processing in the second wire drawing process is 20% or more and is greater than the degree of processing in the first wire drawing process.

1 is a perspective view showing an example of an aluminum alloy wire according to an embodiment.
Figure 2 is a diagram showing an example of the distribution of the degree of orientation in 111 planes across the cross section of the aluminum alloy wire of sample No. 3 of Test Example 1.
FIG. 3 is a diagram showing an example of the distribution of the degree of orientation of 111 planes for the aluminum alloy wire of sample No. 3 of Test Example 1 using contour lines.
Figure 4 is a diagram showing an example of the distribution of the degree of orientation in 111 planes across the cross section of the aluminum alloy wire of sample No. 1 of Test Example 1.
FIG. 5 is a diagram showing an example of the distribution of the degree of orientation of 111 planes for the aluminum alloy wire of Sample No. 1 of Test Example 1 using contour lines.
Figure 6 is a diagram explaining a method of measuring the distribution of orientation of 111 planes over the entire cross section of a sample.

[Problems that this disclosure seeks to solve]

As described above, further improvement in strength is desired for aluminum alloy members used after solution treatment and aging treatment. Additionally, there is a demand for an aluminum alloy that can form such a high-strength aluminum alloy member.

Therefore, one of the purposes of the present disclosure is to provide an aluminum alloy with high strength in a state in which solution treatment and aging treatment have been performed. Another purpose of the present disclosure is to provide an aluminum alloy wire containing the above-described aluminum alloy. Another purpose of the present disclosure is to provide a manufacturing method of an aluminum alloy wire capable of manufacturing the above-described aluminum alloy wire.

[Effect of this disclosure]

The aluminum alloy of the present disclosure and the aluminum alloy wire of the present disclosure have high strength when solution heat treatment and aging treatment have been performed. The method for manufacturing the aluminum alloy wire of the present disclosure can produce the aluminum alloy wire of the present disclosure.

[Description of Embodiments of the Present Disclosure]

First, embodiments of the present disclosure will be described and described.

(1) The aluminum alloy according to one aspect of the present disclosure contains 0.6 mass% or more and 1.5 mass% or less of silicon, 0.5 mass% or more and 1.3 mass% or less of magnesium, 0.1 mass% or more and 1.2 mass% or less of copper, and 0.2 mass% or more of manganese. It has a composition containing not less than 1.15% by mass and not more than 1.15% by mass, with the balance containing aluminum and unavoidable impurities. In this aluminum alloy, the average value of the orientation degree of 111 planes obtained by X-ray diffraction of the entire cross section in a state in which solution treatment and aging treatment have been performed is 50% or more, and the dispersion of the orientation degree of the 111 planes is 45% or less.

The 111 facet in the present disclosure refers to the crystal face indicated by (111) in crystallography. The degree of orientation of the 111 plane in the present disclosure is obtained by using the normalized values of the following three diffraction intensities obtained by X-ray diffraction over the entire cross section. The degree of orientation of the 111 plane in the present disclosure is the ratio of the normalized value of the diffraction intensity of the 111 plane to the sum of the three standardized values. The three diffraction intensities are the diffraction intensity of the 111 plane, the diffraction intensity of the 200 plane, and the diffraction intensity of the 220 plane. The 200 and 220 planes refer to crystal planes indicated as (200) and (220) in crystallography. The average value of the orientation of 111 planes in the present disclosure is the average value of the above-mentioned ratios at each measurement point over the entire cross section. The dispersion of the degree of orientation of 111 planes in the present disclosure is a value obtained from the above average value. The method of measuring the average value and dispersion of the degree of orientation of 111 planes in the present disclosure will be described later. The measurement method described later makes the entire cross section the object of measurement for The degree of orientation can be appropriately evaluated.

In the present disclosure, the cross section of the aluminum alloy is, for example, the cross section below. When the aluminum alloy has a somewhat long shape such as a line, pipe, plate, etc., the cross section is a cross section cut on a plane perpendicular to the longitudinal direction of the aluminum alloy.

In the present disclosure, the conditions of solution treatment and aging treatment are as follows.

(Conditions of solution treatment)

The heating temperature is a temperature selected from the range of 530°C or more and 580°C or less. The heating time is a time selected from the range of 15 minutes to 120 minutes.

(Conditions for prescription treatment)

The heating temperature is a temperature selected from the range of 150°C or more and 180°C or less. The heating time is a time selected from the range of 4 hours or more and 100 hours or less.

The aluminum alloy of the present disclosure has the specific composition described above and has high tensile strength due to precipitation hardening in a state in which solution treatment and aging treatment have been performed. In particular, in the aluminum alloy of the present disclosure, the state in which the 111 planes of the crystal grains are oriented occurs not in a portion of the cross section but throughout the entire cross section. The aluminum alloy of the present disclosure having such a cross section is unlikely to fracture when, for example, the aluminum alloy is stretched in a direction perpendicular to this cross section as the tensile direction. In this regard as well, the aluminum alloy of the present disclosure has high tensile strength. Preferably, the aluminum alloy of the present disclosure has a higher tensile strength than the aluminum alloy described in Patent Document 1. In view of the above, the aluminum alloy of the present disclosure has high strength in a state in which solution treatment and aging treatment have been performed.

In addition, the aluminum alloy of the present disclosure has well-balanced heat resistance, corrosion resistance, and strength, similar to the alloy called 6000 series alloy in the international alloy symbol, when solution treatment and aging treatment have been performed. The aluminum alloy of this disclosure can be suitably used as an aluminum alloy member that requires even higher strength in addition to heat resistance and corrosion resistance, or as a raw material for this aluminum alloy member. Aluminum alloy members are, for example, automobile parts and various structural members. Automobile parts and various structural members may take the form of wires, bars, pipes, etc. The raw materials are, for example, aluminum alloy wire, aluminum alloy plate, etc.

(2) The aluminum alloy of the present disclosure may further contain one or more elements selected from the group consisting of iron, chromium, zinc, titanium, and zirconium. The iron content ranges from 0 mass% to 0.8 mass% or less. The content rate of chromium is more than 0 mass% and 0.35 mass% or less. The zinc content is greater than 0% by mass and less than or equal to 0.5% by mass. The titanium content is greater than 0% by mass and less than or equal to 0.2% by mass. The content rate of zirconium is more than 0 mass% and 0.2 mass% or less.

The aluminum alloys described above tend to have higher tensile strengths.

(3) The aluminum alloy of (2) above contains 1.0 mass% to 1.3 mass% of silicon, 0.5 mass% to 1.2 mass% of magnesium, 0.3 mass% to 0.8 mass% of iron, and 0.1 mass% of copper. Contains not less than 0.4% by mass but not more than 0.2% by mass but not more than 0.5% by mass of manganese, not less than 0% by mass but not more than 0.3% by mass of chromium, and not less than 0.001% by mass and not more than 0.1% by mass of titanium, with the remainder containing aluminum and inevitable impurities. You may have a composition. This aluminum alloy may also contain zirconium in an amount of 0.001% by mass or more and 0.2% by mass or less.

The aluminum alloys described above tend to have higher tensile strengths.

(4) The aluminum alloy of (2) above contains 0.6 mass% to 1.5 mass% of silicon, 0.7 mass% to 1.3 mass% of magnesium, 0.02 mass% to 0.4 mass% of iron, and 0.5 mass% of copper. 1.2 mass% or less, manganese 0.5 mass% or more and 1.1 mass% or less, chromium more than 0 mass% and 0.3 mass% or less, zinc 0.005 mass% or more and 0.5 mass% or less, titanium 0.01 mass% or more and 0.2 mass% or less, It may be provided with a composition containing 0.05 mass% or more and 0.2 mass% or less of zirconium, and the balance containing aluminum and unavoidable impurities.

The aluminum alloys described above tend to have higher tensile strengths.

(5) The aluminum alloy of the present disclosure may have a tensile strength of more than 425 MPa when solution heat treatment and aging treatment have been performed.

The above-described aluminum alloy has high tensile strength and thus high strength.

(6) The aluminum alloy wire according to one aspect of the present disclosure includes the aluminum alloy described in any one of (1) to (5) above.

The aluminum alloy wire of the present disclosure contains the aluminum alloy of the present disclosure and thus has high strength when solution heat treatment and aging treatment are performed. The aluminum alloy wire of this disclosure can be used as a raw material for high-strength aluminum alloy members.

(7) The method of manufacturing an aluminum alloy wire according to an aspect of the present disclosure includes 0.6 mass% to 1.5 mass% of silicon, 0.5 mass% to 1.3 mass% of magnesium, 0.1 mass% to 1.2 mass% of copper, A process of producing a processed material by performing plastic working on a cast material of an aluminum alloy containing 0.2% by mass or more and 1.15% by mass or less of manganese and the balance containing aluminum and inevitable impurities, and first drawing the processed material by cold drawing. A process of manufacturing a first wire drawing by performing processing, a process of manufacturing a softened material by subjecting the first wire drawing to a softening treatment, and subjecting the softened material to a second cold drawing process to produce a second wire drawing. It is equipped with a manufacturing process. The degree of processing in the second wire drawing process is 20% or more and is greater than the degree of processing in the first wire drawing process.

The method for producing an aluminum alloy wire of the present disclosure can produce a high-strength aluminum alloy wire in a state in which solution treatment and aging treatment have been performed. The reason is explained later.

(8) In the method for manufacturing an aluminum alloy wire of the present disclosure, the aluminum alloy may further contain one or more elements selected from the group consisting of iron, chromium, zinc, titanium, and zirconium. The iron content ranges from 0 mass% to 0.8 mass% or less. The content rate of chromium is more than 0 mass% and 0.35 mass% or less. The zinc content is greater than 0% by mass and less than or equal to 0.5% by mass. The titanium content is greater than 0% by mass and less than or equal to 0.2% by mass. The content rate of zirconium is more than 0 mass% and 0.2 mass% or less.

The method for manufacturing the aluminum alloy wire described above can produce an aluminum alloy wire with higher tensile strength.

[Details of the Embodiment of the Present Disclosure]

Hereinafter, embodiments of the present disclosure will be described in detail with appropriate reference to the drawings.

[Aluminum alloy]

(outline)

The aluminum alloy of the embodiment has the following composition and the following cross-sectional structure. The composition of the aluminum alloy of the embodiment includes silicon, magnesium, copper, and manganese in the ranges described later, respectively, and the balance includes aluminum and inevitable impurities. The aluminum alloy of the embodiment may further contain one or more elements selected from the group consisting of iron, chromium, zinc, titanium, and zirconium in the range described later. In the cross-sectional structure of the aluminum alloy of the embodiment, the 111 facets of the crystal grains are oriented in the normal direction of the cross-section in a state in which solution treatment and aging treatment have been performed. In particular, among the crystal grains constituting the cross section of an aluminum alloy, most of the crystal grains have 111 planes oriented in the normal direction of the cross section. Hereinafter, the composition and organization will be explained in order.

In the description below, it may be written as follows.

Silicon, magnesium, copper, and manganese are collectively referred to as primary elements. Iron, chromium, zinc, titanium, and zirconium are collectively referred to as secondary elements.

Each element is represented by its element symbol. Si means silicon. Mg means magnesium. Cu means copper. Mn means manganese. Al means aluminum. Fe means iron. Cr means chrome. Zn means zinc. Ti means titan. Zr means zirconium.

The state in which solution treatment and aging treatment have been performed on an aluminum alloy is referred to as the state after heat treatment.

(Furtherance)

In the aluminum alloy of the embodiment, the first element is an essential element and the second element is an optional element. Quantitatively, the aluminum alloy of the embodiment contains 0.6 mass% to 1.5 mass% of silicon, 0.5 mass% to 1.3 mass% of magnesium, 0.1 mass% to 1.2 mass% of copper, and 0.2 mass% to 1.15 mass% of manganese. % or less, iron from 0 mass% to 0.8 mass%, chromium from 0 mass% to 0.35 mass%, zinc from 0 mass% to 0.5 mass%, titanium from 0 mass% to 0.2 mass%, zirconium to 0 It has a composition containing not less than 0.2% by mass and not more than 0.2% by mass, with the balance containing aluminum and unavoidable impurities. In the aluminum alloy of the embodiment containing one or more second elements, the iron content is greater than 0% by mass and 0.8% by mass or less. The content rate of chromium is more than 0 mass% and 0.35 mass% or less. The zinc content is greater than 0% by mass and less than or equal to 0.5% by mass. The titanium content is greater than 0% by mass and less than or equal to 0.2% by mass. The content rate of zirconium is more than 0 mass% and 0.2 mass% or less.

When the content ratio of the first element is more than the above-mentioned lower limit, compounds containing the first element, etc. are precipitated in the state after heat treatment. The presence of dispersed precipitates such as the above compounds provides an effect of improving strength through precipitation hardening. When a part of the first element is dissolved in aluminum, which is the main phase of the mother phase, the effect of improving strength through solid solution strengthening is also obtained. When the content ratio of the first element is below the above-mentioned upper limit, grain boundary embrittlement due to segregation of the first element is suppressed, or the compound containing the first element, etc., is unlikely to become coarse. Particles such as coarse compounds can become the origin of cracks. If the coarse particles are small, cracks caused by the coarse particles are unlikely to occur. In these respects, the aluminum alloy of the embodiment has high tensile strength in the state after heat treatment. During the manufacturing process, cracks caused by the coarse particles are unlikely to occur, so cold plastic working, such as cold drawing, can be performed satisfactorily. In this respect, the aluminum alloy of the embodiment is also excellent in manufacturability.

When a second element is included in addition to the first element, one or more effects selected from the group consisting of precipitation hardening, solid solution strengthening, suppression of grain boundary embrittlement, and suppression of grain coarsening can be expected. Due to this effect, the aluminum alloy of the embodiment containing the second element in addition to the first element tends to have a higher tensile strength in the state after heat treatment. When the content ratio of the second element satisfies the above-mentioned upper limit range, it is difficult for the compound containing the second element to become coarse. In addition, depending on the type of the second element, the cast material can have a fine structure. In these respects, the aluminum alloy of the embodiment containing the second element in addition to the first element has excellent workability when plastic working is included in the manufacturing process. Depending on the type of the second element, the injection temperature can be lowered. In these respects, the aluminum alloy of the embodiment containing the second element in addition to the first element has better manufacturability.

Specific examples of compositions containing a second element in addition to the first element include the following first composition, second composition, and third composition.

〈First Composition〉

The first composition includes 1.0 mass% to 1.3 mass% of silicon, 0.5 mass% to 1.2 mass% of magnesium, 0.3 mass% to 0.8 mass% of iron, 0.1 mass% to 0.4 mass% of copper, and manganese. 0.2 mass% or more and 0.5 mass% or less, chromium more than 0 mass% and 0.3 mass% or less, titanium 0.001 mass% or more and 0.1 mass% or less, zirconium 0 mass% or more and 0.2 mass% or less, the balance being aluminum and inevitable Contains impurities.

〈Second Composition〉

The second composition contains 0.6 mass% to 1.5 mass% of silicon, 0.7 mass% to 1.3 mass% of magnesium, 0.02 mass% to 0.4 mass% of iron, 0.5 mass% to 1.2 mass% of copper, and manganese. 0.5 mass% or more and 1.1 mass% or less, chromium more than 0 mass% and 0.3 mass% or less, zinc 0.005 mass% or more and 0.5 mass% or less, titanium 0.01 mass% or more and 0.2 mass% or less, zirconium 0.05 mass% or more and 0.2 mass% It contains not more than % by mass, and the balance includes aluminum and inevitable impurities. The second composition may also contain 0.005 mass% or more and 0.05 mass% or less of strontium.

〈Third Composition〉

The third composition is 0.9 mass% to 1.3 mass% of silicon, 0.8 mass% to 1.2 mass% of magnesium, 0 mass% to 0.4 mass% of iron, 0.65 mass% to 1.1 mass% of copper, and manganese. 0.55 mass% or more and 1.15 mass% or less, chromium more than 0 mass% and 0.35 mass% or less, zinc 0.12 mass% or more and 0.25 mass% or less, titanium more than 0 mass% and 0.075 mass% or less, zirconium 0.05 mass% or more and 0.17 mass% It contains not more than % by mass, and the balance includes aluminum and inevitable impurities. The third composition roughly corresponds to the composition of the alloy represented by the international alloy symbol A6056.

Hereinafter, the content range of the first element and the content range of the second element in the first composition, second composition, and third composition will be exemplified.

〈First Composition〉

The content ratio of silicon may be more than 1.0 mass% and 1.3 mass% or less, or 1.1 mass% or more and 1.3 mass% or less.

The magnesium content may be 0.6 mass% or more and 1.1 mass% or less, or 0.7 mass% or more and 1.0 mass% or less.

The iron content may be 0.3 mass% or more and 0.7 mass% or less, or 0.3 mass% or more and 0.6 mass% or less.

The copper content may be 0.2% by mass or more and 0.4% by mass or less.

The content of manganese may be 0.2 mass% or more and 0.4 mass% or less, or 0.2 mass% or more and 0.3 mass% or less.

The content ratio of chromium may be 0.005 mass% or more and 0.20 mass% or less, or 0.01 mass% or more and 0.10 mass% or less.

The titanium content may be 0.005 mass% or more and 0.05 mass% or less, or 0.01 mass% or more and 0.05 mass% or less.

When zirconium is included, the zirconium content ratio may be 0.001 mass% or more and 0.20 mass% or less, or 0.005 mass% or more and 0.10 mass% or less.

The total content ratio of titanium and zirconium may be 0.01 mass% or more and 0.10 mass% or less.

〈Second Composition〉

The content ratio of silicon may be 0.8 mass% or more and 1.4 mass% or less, or 1.1 mass% or more and 1.3 mass% or less.

The magnesium content may be 0.8 mass% or more and 1.3 mass% or less, or 0.8 mass% or more and 1.0 mass% or less.

The iron content may be 0.05 mass% or more and 0.40 mass% or less.

The content ratio of copper may be 0.8 mass% or more and 1.2 mass% or less.

The content ratio of manganese may be 0.7 mass% or more and 1.1 mass% or less.

The content ratio of chromium may be 0.01 mass% or more and 0.30 mass% or less, or 0.05 mass% or more and 0.30 mass% or less.

The zinc content may be 0.05 mass% or more and 0.25 mass% or less.

The titanium content may be 0.01 mass% or more and 0.15 mass% or less.

The content ratio of zirconium may be 0.08 mass% or more and 0.2 mass% or less.

The total content ratio of titanium and zirconium may be 0.10 mass% or more and 0.20 mass% or less.

When strontium is included, the strontium content may be 0.005 mass% or more and 0.04 mass% or less.

〈Third Composition〉

The content ratio of silicon may be 0.9 mass% or more and 1.2 mass% or less.

The magnesium content may be 0.8 mass% or more and 1.0 mass% or less.

The iron content may be 0.10 mass% or more and 0.25 mass% or less.

The copper content may be 0.65 mass% or more and 0.85 mass% or less.

The content ratio of manganese may be 0.55 mass% or more and 0.80 mass% or less, or 0.55 mass% or more and 0.65 mass% or less.

The content rate of chromium may be 0.01 mass% or more and 0.10 mass% or less, or 0.02 mass% or more and 0.05 mass% or less.

The zinc content may be 0.13 mass% or more and 0.25 mass% or less.

The titanium content may be 0.001 mass% or more and 0.075 mass% or less, or 0.01 mass% or more and 0.075 mass% or less.

The content ratio of zirconium may be 0.10 mass% or more and 0.17 mass% or less.

The total content ratio of titanium and zirconium may be 0.11 mass% or more and 0.20 mass% or less.

〈Other Elements〉

When containing titanium, the aluminum alloy of the embodiment may further contain boron in a range of 50 mass ppm or less.

(group)

The present inventors have obtained the knowledge that it is desirable for an aluminum alloy having high tensile strength in the state after heat treatment to have the following structure. It is preferable that the 111 plane of the crystal grain is oriented more than the other crystal planes in the grain throughout the cross section of the aluminum alloy. That is, it is desirable that most of the crystal grains constituting the cross section of the aluminum alloy have 111 planes oriented. Quantitatively, in the aluminum alloy of the embodiment, the average value of the orientation degree of 111 planes obtained by X-ray diffraction of the entire cross section in the state after heat treatment is 50% or more. In addition, the dispersion of the degree of orientation of the 111 faces is 45% or less. An aluminum alloy having a plurality of such cross-sections and the plurality of cross-sections arranged in a direction perpendicular to one cross-section is difficult to fracture even when stretched with the vertical direction as the tensile direction.

If the average value of the degree of orientation of the 111 plane is 50% or more, the 111 plane is oriented in the normal direction of the cross section in more than half of the crystal grains constituting the cross section of the aluminum alloy. If the dispersion of the degree of orientation of the 111 plane is 45% or less, the distribution of the oriented crystal planes among the crystal grains constituting the cross section of the aluminum alloy becomes a distribution concentrated on the 111 plane. The aluminum alloy of this embodiment has high orientation of the 111 planes of crystal grains. In general, the higher the orientation of the 111 planes of aluminum alloy grains, the higher the tensile strength tends to be. Therefore, the aluminum alloy of the embodiment has high tensile strength in the state after heat treatment. The larger the average value of the degree of orientation of the 111 planes and the smaller the dispersion of the degree of orientation of the 111 planes, the higher the tensile strength is likely to be. From the viewpoint of improving strength, the average orientation of the 111 faces may be 55% or more, and may even be 60% or more. The dispersion of the degree of orientation of the 111 planes may be 40% or less, and may even be 38% or less.

In addition, the average value of the degree of orientation of the 111 faces is 50% or more and 100% or less. The dispersion of the orientation of the 111 planes is more than 0% and less than 45%. Considering manufacturability, the average orientation degree of the 111 faces may be 99% or less, and the dispersion of the orientation degree of the 111 faces may be 1% or more.

In the aluminum alloy of the embodiment, the orientation of the 111 planes of crystal grains is evaluated not in a portion of the cross section but in the entire cross section. In this regard, the aluminum alloy of the embodiment clearly has a higher strength structure in the state after heat treatment than when only a portion of the cross section is evaluated.

When the aluminum alloy of the embodiment is a wire rod, the cross section for measuring the degree of orientation of the 111 plane is a cross section cut on a plane perpendicular to the longitudinal direction at an arbitrary position in the longitudinal direction of the wire rod. Hereinafter, a cross section cut along a plane perpendicular to the longitudinal direction of a wire containing the aluminum alloy of the embodiment, that is, the aluminum alloy wire 1 of the embodiment, may be shown as a cross section. In the wire rod, as described above, the 111 facets of the crystal grains are more oriented than the other crystal faces throughout each cross section. The orientation direction of the 111 planes in each cross section is the normal direction of the cross section, that is, the direction along the longitudinal direction of the wire. Such wire rods are difficult to fracture even when stretched with the length direction of the wire rod being the direction of tension.

In addition, in the aluminum alloy of the embodiment, even if only solution treatment is performed and no aging treatment is performed, the average value of the orientation degree of the 111 planes is 50% or more, and the dispersion of the orientation degree of the 111 planes is 45% or less. am. In other words, it is thought that the orientation of the 111 faces of the crystal grains does not substantially change before and after aging treatment.

(tensile strength)

The aluminum alloy of the embodiment has a tensile strength of more than 425 MPa at room temperature, for example, in the state after heat treatment. The room temperature here is 5°C or higher and 35°C or lower. Embodiment aluminum alloys with tensile strengths greater than 425 MPa have excellent strength. The aluminum alloy of the embodiment having a tensile strength of greater than 427 MPa, greater than 430 MPa, and even greater than 440 MPa has superior strength. Depending on the composition or manufacturing conditions, the aluminum alloy of the embodiment has a high tensile strength of 450 MPa or more, 460 MPa or more, and even 470 MPa or more.

The upper limit of tensile strength is not particularly determined. Considering manufacturability, the tensile strength at room temperature may be, for example, greater than 425 MPa and less than or equal to 550 MPa.

(Form of use)

The aluminum alloy of embodiments may have various shapes. For example, the aluminum alloy of the embodiment has a somewhat elongated shape. The aluminum alloy of this embodiment has an end surface including a plane perpendicular to its longitudinal direction and an elongated portion extending in the longitudinal direction. The length along the longitudinal direction in the stretched portion is longer than the diameter of a circle having an area equal to the area of the outer peripheral outline of the end face. In the aluminum alloy of the embodiment having the stretched portion, the cross section for measuring the orientation of the 111 planes described above is obtained by cutting the stretched portion in a plane perpendicular to the longitudinal direction.

Aluminum alloys of the embodiment having an elongated portion are, for example, wire rods, pipes, plates, etc. In other words, the stretched portion may be a solid body such as a wire rod or plate, or a hollow body such as a pipe.

〈Seonjae〉

The aluminum alloy wire 1 of the embodiment includes the aluminum alloy of the embodiment. The aluminum alloy wire 1 of the embodiment has an end surface 10 and an extended portion 11 as shown in FIG. 1. The end surface 10 here is a surface perpendicular to the longitudinal direction of the aluminum alloy wire 1. The elongated portion 11 extends in the longitudinal direction. The aluminum alloy wire 1 of the embodiment typically has the same outer peripheral outline and the same wire diameter over the entire length of the stretched portion 11, as shown in FIG. 1 . The line diameter here is the diameter of a circle having an area equal to the area of the end surface 10 or the area of a cross section cut by a plane perpendicular to the longitudinal direction. Figure 1 illustrates a case where the outer circumference of the end surface 10 and the outer circumference of an arbitrary cross section cut in a plane perpendicular to the longitudinal direction are circular. The outer circumferential outline of the end surface 10 and the outer circumferential outline of the cross section may be a polygon such as a square or a curved shape such as an oval. The wire diameter of the aluminum alloy wire 1 of the embodiment is not particularly limited. The wire diameter is, for example, about 3 mm or more and 15 mm or less.

In the aluminum alloy wire 1 of the embodiment, the cross section for measuring the orientation of the 111 planes described above is the cross section. In the aluminum alloy wire 1 of the embodiment, the average value of the orientation degree of 111 planes obtained by X-ray diffraction over the entire cross section is 50% or more. In addition, the dispersion of the degree of orientation of the 111 faces is 45% or less. In the aluminum alloy wire 1 of the embodiment, these cross sections are arranged in the longitudinal direction. The aluminum alloy wire 1 of this embodiment has a high tensile strength exceeding 425 MPa in the state after heat treatment.

<Aluminum alloy member>

The aluminum alloy of the embodiment can constitute an aluminum alloy member. For example, the aluminum alloy member contains the aluminum alloy of the embodiment and has been subjected to solution treatment and aging treatment. A specific example is an aluminum alloy member to which solution treatment and aging treatment were performed after plastic working was performed on the aluminum alloy wire 1 of the embodiment. Another example is an aluminum alloy member in which solution treatment and aging treatment are performed after plastic working is performed on a sheet material containing the aluminum alloy of the embodiment. The plastic working here is performed so that the cross section of the aluminum alloy member has the specific orientation described above after solution treatment and aging treatment. Another example is an aluminum alloy member to which solution treatment and aging treatment have been applied to the aluminum alloy wire 1 of the embodiment. That is, the aluminum alloy member may be linear or rod-shaped. In addition, the aluminum alloy member may be cylindrical.

For example, the aluminum alloy member includes an extruded material obtained by extruding the aluminum alloy wire 1 with the longitudinal direction of the aluminum alloy wire 1 of the embodiment as the extrusion direction. This aluminum alloy member extends along the extrusion direction. In this aluminum alloy member, the cross section for measuring the degree of orientation of the 111 planes described above is obtained by cutting the aluminum alloy member in a plane perpendicular to the extrusion direction. The average value of the orientation of 111 planes obtained by X-ray diffraction of the entire cross section is more than 50%. In addition, the dispersion of the degree of orientation of the 111 faces is 45% or less.

The above-described aluminum alloy member has high strength because it contains an aluminum alloy having the above-described specific composition and the above-described specific structure. Additionally, this aluminum alloy member is lightweight compared to a metal member containing an iron-based alloy such as steel. These aluminum alloy members can be used in applications requiring light weight and high strength, such as automobile parts and various structural members.

(Method for producing aluminum alloy)

The present inventors studied a method of manufacturing an aluminum alloy having the above-described specific composition and having excellent strength when solution treatment and aging treatment were performed. As a result, the present inventors obtained the knowledge that it is desirable that the plastic working performed immediately before the solution heat treatment is cold working and has a high degree of workability. From this knowledge, when manufacturing the aluminum alloy of the embodiment, for example, the following aluminum alloy manufacturing method can be used.

A method for manufacturing an aluminum alloy includes a process of manufacturing a cold-worked material by cold working a material containing an aluminum alloy. The aluminum alloy has a composition containing the above-described first element in the above-mentioned range and the balance containing aluminum and inevitable impurities.

The material is a processed material on which first plastic working has been performed. The cold working is a second plastic working with a workability of 20% or more.

The aluminum alloy may have a composition containing a second element within the above-mentioned range in addition to the above-described first element.

Dislocations are more likely to be liberated in hot working and warm working compared to cold working. In contrast, since the second plastic working is cold working, deformation, or dislocations, due to the second plastic working are more likely to accumulate in the aluminum alloy compared to the case of warm working or hot working. As dislocations accumulate, the 111 planes of crystal grains are more likely to be oriented during the subsequent solution treatment. As a result, when solution treatment and aging treatment are performed as described above, a structure in which the 111 planes of crystal grains are highly oriented is obtained throughout the cross section of the aluminum alloy.

Hereinafter, the manufacturing method of the above-described aluminum alloy will be described in detail.

<Material>

The material containing the above-described aluminum alloy is a cast material subjected to first plastic working. The first plastic working is, for example, rolling processing. The first plastic working is, for example, hot working.

〈Early Yeonhwa〉

The above-described materials can be subjected to softening treatment under the following conditions. Hereinafter, the softening treatment performed on the material may be referred to as initial softening treatment.

《Conditions for softening treatment》

The heating temperature is a temperature selected from the range of 250°C or more and less than 500°C. The holding time is a time selected from the range of 1 hour to 100 hours. The atmosphere during softening is, for example, an atmospheric atmosphere or a non-oxidizing atmosphere. Non-oxidizing atmospheres include, for example, reduced pressure atmospheres, inert gas atmospheres, and reducing gas atmospheres.

The heating temperature may be 300°C or higher and 480°C or lower, and may also be 300°C or higher and 460°C or lower.

By subjecting the material to an initial softening treatment, the plastic workability of the aluminum alloy after the initial softening treatment increases. Therefore, the workability of the second plastic working can be increased. When the material is not subjected to initial softening treatment, dislocations introduced by the first plastic working are accumulated in the aluminum alloy. As a result, an aluminum alloy in which many dislocations are accumulated is easy to obtain.

〈Second plastic processing〉

The second plastic working performed on the material is cold working, as described above. The second plastic processing is, for example, drawing processing, rolling processing, extrusion processing, etc. If the second plastic working is wire drawing, a wire rod is obtained. If the second plastic working is rolling processing, a sheet material is typically obtained. If the second plastic working is extrusion processing, wire rods, plates, pipes, etc. are obtained depending on the shape of the extrusion die.

《Processing》

The greater the degree of second plastic working, the higher the orientation of the 111 plane. From the viewpoint of improving strength, the workability of the second plastic working may be 30% or more, 40% or more, or 60% or more. The workability here is the ratio of the difference between the cross-sectional area before the second plastic working and the cross-sectional area after the second plastic working divided by the cross-sectional area before the second plastic working.

〈Middle Lotus Flower〉

Softening treatment can be performed during the second plastic working. Hereinafter, the softening treatment performed during the second plastic working may be referred to as an intermediate softening treatment. The conditions of the intermediate softening treatment may refer to the conditions of the initial softening treatment described above. By performing cold working before and after the intermediate softening treatment, dislocations are more likely to accumulate in the aluminum alloy compared to the case where warm working or hot working is performed as described above. Additionally, by performing the intermediate softening treatment, the workability of cold working after the intermediate softening treatment can be increased. Therefore, dislocations can be accumulated in the aluminum alloy by cold working after intermediate softening treatment. The greater the degree of cold working after intermediate softening treatment, the higher the orientation of the 111 plane. In addition, when performing intermediate softening treatment, it is preferable that the workability in cold working after the intermediate softening treatment is greater than the workability in cold working before the intermediate softening treatment. In particular, the workability in cold working after intermediate softening treatment may be 30% or more, 40% or more, and even 60% or more.

(Manufacturing method of aluminum alloy wire)

The inventors obtained the knowledge that in order to manufacture the aluminum alloy wire 1 of the embodiment, it is desirable to satisfy the following conditions. From this knowledge, the manufacturing method of the aluminum alloy wire of the embodiment includes the following first process, second process, third process, and fourth process.

<condition>

The drawing process is carried out cold. Softening treatment is performed during wire drawing. The workability of wire drawing after the softening treatment is 20% or more and is greater than the workability of wire drawing before the softening treatment.

The first process is a process of manufacturing a processed material by performing plastic working on a cast material of an aluminum alloy containing the above-described first element in the above-mentioned range and the balance containing aluminum and inevitable impurities. The aluminum alloy constituting the cast material may contain a second element in the above-mentioned range in addition to the first element.

The second process is a process of producing a first drawn material by subjecting the processed material to a first cold drawing process.

The third process is a process of producing a softened material by subjecting the first wire material to a softening treatment.

The fourth process is a process of producing a second wire drawing by subjecting the softened material to a second cold drawing process.

In the method for manufacturing an aluminum alloy wire of the embodiment, the degree of workability in the second wire drawing process is 20% or more. Additionally, the degree of processing in the second wire drawing process is greater than the degree of processing in the first wire drawing process.

The plastic working in the first process corresponds to the first plastic working described above. The softening treatment in the third step corresponds to the intermediate softening treatment described above. The first drawing process and the second drawing process correspond to the above-described second plastic working.

As described above, the manufacturing method of the aluminum alloy wire of the embodiment performs cold drawing before and after the softening treatment, so that dislocations are more likely to accumulate in the aluminum alloy compared to the case of performing warm working or hot working. Additionally, by performing the softening treatment, the degree of workability of the second drawing process after the softening treatment can be increased as described above. Therefore, dislocations can be accumulated in the aluminum alloy through the second wire drawing process after the softening treatment. The manufacturing method of the aluminum alloy wire of this embodiment can manufacture the aluminum alloy wire 1 of the embodiment. In addition, as described above, a material containing an aluminum alloy having a specific composition has excellent cold drawing processability. The manufacturing method of the aluminum alloy wire of the embodiment using such a material can mass-produce the aluminum alloy wire 1 of the embodiment.

Below, each process is explained. In addition, the basic operation in the method for manufacturing an aluminum alloy wire of the embodiment can refer to a known method for manufacturing an aluminum alloy wire.

〈First process〉

In the first process, the cast material is manufactured using, for example, a mold casting method or a continuous casting method. In the first process, the plastic working is, for example, hot rolling processing, and the processed material is, for example, a continuous casting or rolling material. If the processed material is a continuously cast or rolled material, a continuous long aluminum alloy wire can be manufactured. In this regard, when the processed material is a continuous casting or rolled material, the aluminum alloy wire 1 of the embodiment can be mass-produced.

The processed material may be subjected to the initial softening treatment described above. When performing the initial softening treatment, the degree of processing of the next first drawing process can be increased as described above. If the initial softening treatment is not performed, it is easy to obtain an aluminum alloy wire in which a large amount of dislocations are ultimately accumulated, as described above.

〈Second Process〉

In the second process, it is preferable that the degree of processing of the first drawing process is 30% or more. If the degree of workability of the first wire drawing process is 30% or more, the dislocations introduced by the first wire drawing process are likely to remain to some extent after the softening treatment. As a result, it is easy to obtain an aluminum alloy wire in which a large amount of dislocations are ultimately accumulated. The processing degree of the first wire drawing may be 35% or more and 40% or more. The degree of processing of the first drawing process also varies depending on the final wire diameter, but is selected from a range of, for example, 30% to 80%. The degree of processing of the first wire-drawing process is the ratio of the difference between the cross-sectional area before the first wire-drawing process and the cross-sectional area after the first wire-drawing process divided by the cross-sectional area before the first wire-drawing process.

〈Third process〉

For the conditions of the softening treatment in the third process, refer to the conditions of the initial softening treatment described above. By performing softening treatment in the third step, the processability of the softened material after softening treatment increases. Therefore, the degree of processing of the second drawing process in the fourth process can be increased. In particular, the degree of workability of the second drawing process in the fourth process can be made greater than the degree of workability of the first wire drawing process in the second process. As a result, dislocations can be accumulated in the aluminum alloy by the second wire drawing process.

〈Fourth Process〉

The greater the degree of second wire drawing in the fourth process, the higher the orientation of the 111 planes. If the workability of the second wire drawing is 20% or more, it is easy to obtain an aluminum alloy wire in which a large amount of dislocations are ultimately accumulated. Even when the degree of workability of the second wire drawing is greater than that of the first wire drawing, it is easy to obtain an aluminum alloy wire in which a large amount of dislocations are ultimately accumulated. As described above, since the degree of workability of the first drawing process is preferably 30% or more, the degree of workability of the second wire drawing process may be more than 30%, 40% or more, and even 60% or more. The processing degree of the second wire drawing process is selected from a range of 20% to 99.9% so that a second wire wire having a predetermined final wire diameter is obtained. The workability of the second wire drawing process is the ratio of the difference between the cross-sectional area before the second wire drawing process and the cross-sectional area after the second wire drawing process divided by the cross-sectional area before the second wire drawing process.

(Method for manufacturing aluminum alloy members)

The method of manufacturing the above-described aluminum alloy member includes, for example, the following processing process and heat treatment process.

The processing process is a process of manufacturing a third processed material by subjecting the second plastic worked material to which the above-described second plastic working has been performed or the above-mentioned second drawn material to third plastic working.

The heat treatment process is a process of manufacturing an aged material by sequentially performing solution treatment and aging treatment on the third processed material.

The third plastic processing is, for example, extrusion processing, forging processing, wire drawing processing, etc. The conditions for solution treatment and aging treatment are as described above.

[Main effect of embodiment]

The aluminum alloy of the embodiment and the aluminum alloy wire 1 of the embodiment have high tensile strength in a state in which solution treatment and aging treatment have been performed. In Test Example 1 below, the above-mentioned effect is explained in detail by taking the aluminum alloy wire 1 of the embodiment as an example.

The method for manufacturing the aluminum alloy wire of the embodiment can produce the aluminum alloy wire 1 of the embodiment having high tensile strength in a state in which solution treatment and aging treatment have been performed.

[Test Example 1]

The aluminum alloy wire having the composition shown in Table 1 was subjected to solution treatment and aging treatment, and its structure was observed and its tensile strength was investigated. The manufacturing conditions and investigation results of the aluminum alloy wire are shown in Tables 2 to 4.

(Production of samples)

The aluminum alloy wire of each sample is basically manufactured by cold drawing processing on continuous casting and rolling material. Continuous casting and rolling materials can be produced, for example, by a known properzi type continuous casting and rolling mill. Except for some of the samples, softening treatment is performed during drawing processing.

The first composition, second composition, and third composition in the composition items in Tables 2 to 4 correspond to the first composition, second composition, and third composition shown in Table 1, respectively.

In Tables 2 to 4, the softening treatment items indicate heating temperature (°C) and holding time (hours). For example, “380°C x 10 h” means that the heating temperature is 380°C and the holding time is 10 hours.

Tables 2 to 4 describe samples whose conditions are described in three items: degree of workability (%) in the first drawing process, softening treatment, and degree of workability (%) in the second wire drawing process. The aluminum alloy wires of these samples are manufactured by sequentially performing cold first wire drawing, softening treatment, and cold second wire drawing on the continuously cast and rolled material. The aluminum alloy wires of these samples were not subjected to initial softening treatment.

In Tables 2 to 4, a hyphen "-" is written in the degree of workability (%) of the first wire drawing process, and the conditions are described in the two items of the degree of workability (%) of the softening treatment and the second wire drawing process. do. The aluminum alloy wires of these samples are manufactured by subjecting the continuously cast rolled material to a softening treatment and then cold drawing it at the degree of work (%) of the second wire drawing process. The aluminum alloy wires of these samples were continuously cast and rolled and subjected to an initial softening treatment followed by cold wire drawing, and no intermediate softening treatment was performed.

In Tables 2 to 4, the conditions are described in two items, the degree of workability (%) of the first wire drawing process and the degree of workability (%) of the second wire drawing process, and the samples with a hyphen "-" in the softening treatment are described. do. The aluminum alloy wire of these samples is cold drawn to the continuous casting and rolled material at the workability (%) of the first wire drawing, and then subjected to cold drawing to the workability (%) of the second wire drawing without performing an intermediate softening treatment. It is manufactured by carrying out cold drawing processing. That is, for the aluminum alloy wires of these samples, cold drawing was continuously performed on continuous casting and rolling materials, and neither initial softening treatment nor intermediate softening treatment was performed. The total workability in this cold wire drawing is greater than the workability described in the item of workability (%) in the second wire drawing in Tables 2 to 4.

The wire diameter of the continuously cast rolled material is selected from the range of 5 mm to 30 mm. The wire diameter of the second wire drawn material manufactured after the second wire drawing process is a value selected from the range of approximately 1.0 mm to 21 mm depending on the degree of processing.

(tissue observation)

<Orientation diagram of 111 sides>

The aluminum alloy wire of each sample obtained is subjected to solution treatment and aging treatment under the conditions described above to manufacture a heat-treated wire. A disk-shaped sample is obtained by cutting the obtained heat-treated line along a plane perpendicular to the longitudinal direction of the heat-treated line. The sample has two circular cross-sections. The entire cross section of one of the two cross sections is smoothed by mechanical polishing. The surface roughness of the cross section after polishing is approximately 0.2 ㎛ in arithmetic average roughness Ra. For mechanical polishing, for example, 2000-count water resistant paper can be used. The entire polished cross section is subjected to X-ray diffraction as follows.

As shown in FIG. 6, the sample 3 is placed on a surface 51f including a plane provided on the movable stage 51. This arrangement is such that the above-described machine-polished cross-section 30 of the sample 3 is parallel to the surface 51f, and the This is done so that it can be investigated. The predetermined direction (D) is a direction corresponding to the predetermined surface index (F). A given plane index (F) is a crystal plane specified by the mirror index. Here, the facet index (F) is one of three crystal faces: 111 facet, 200 facet, and 220 facet. In addition, FIG. 6 shows X-rays 6 and diffracted X-rays 60 from an X-ray source not shown with broken lines.

By radiating X-rays 6 from a predetermined direction D to the cross-section 30 of the sample 3, the X-rays 60 diffracted from the cross-section 30 are detected by the detector 52. Detection of the By doing this, the distribution of diffraction intensity throughout the cross section 30 is obtained. Additionally, when the sample 3 is moved two-dimensionally, the X-rays 6 do not move. Additionally, the calculation device 53 described later is set to exclude the diffraction intensity from the position where the cross section 30 does not exist.

By changing the angle (θ) and angle (2θ) according to the plane index (F), the distribution of diffraction intensity of the 111 plane, the diffraction intensity distribution of the 200 plane, and the diffraction intensity distribution of the 220 plane are obtained. The angle (θ) is the angle formed by the surface index (F) and the X-ray (6). The angle 2θ is the angle formed between the predetermined direction D and the diffracted X-ray 60. The normalized value of each diffraction intensity described above is calculated using theoretical values based on a predetermined direction (D). The above standardized value is a value obtained by dividing each diffraction intensity by the theoretical value of the peak intensity of the diffraction intensity of X-ray diffraction. Using the above normalized values, a normalized distribution is calculated from the distribution of each diffraction intensity. That is, the standardized distribution of 111 sides, the standardized distribution of 200 sides, and the standardized distribution of 220 sides are calculated. The theoretical value can be obtained from the PDF (Powder Diffraction File) database published by ICDD (International Center for Diffraction Data). Additionally, the peak intensity may not be the peak intensity of raw data, but may be obtained by fitting X-ray profile data at each measurement point and using the maximum value or integral value of this fitting curve. Fitting functions used for the above fitting are, for example, Lorentz function and Gauss function.

For each measurement point, obtain the normalized value of the diffraction intensity of the 111 side, the normalized value of the diffraction intensity of the 200 side, and the normalized value of the diffraction intensity of the 220 side. Additionally, the sum of these three standardized values is obtained. Additionally, the ratio of the normalized diffraction intensity of 111 planes to the above total value is obtained. This ratio is the orientation of 111 planes. The average value of the orientation of 111 surfaces is the average value of the orientation of 111 surfaces at all measurement points. The variance of the degree of orientation of 111 planes is obtained from the above averaged value.

X-rays 6 can use, for example, BL16 present in the synchrotron radiation facility SAGA-LS. This beam line can use X-rays with a wavelength of, for example, λ=0.0919 nm. The slit width can be, for example, 0.5 mm square. The detector 52 can be, for example, a commercially available two-dimensional detector, PILATUS 100K from Dectris. The distance from the cross section 30 of the sample 3 to the two-dimensional detector is 0.512 m. The computing device 53 can use a commercially available computer.

The angles (θ, 2θ) are selected according to the wavelength described above. The angles (θ, 2θ) are, for example, the following values when λ is 0.0919 nm.

When the predetermined surface index (F) is 111 surfaces, the angle (θ) formed between the 111 surfaces of the sample 3 and the X-ray 6 is 11.3 degrees. The angle (2θ) formed between the predetermined direction (D) and the diffracted X-rays (60) is 22.6 degrees. Additionally, Figure 6 shows θ and 2θ to be larger than the actual values.

When the predetermined surface index (F) is 200 surfaces, the angle (θ) formed between the 200 surfaces of the sample 3 and the X-ray 6 is 13 degrees. The angle 2θ formed between the predetermined direction D and the diffracted X-ray 60 is 26 degrees.

When the predetermined surface index is 220 surfaces, the angle θ formed between the 220 surfaces of the sample 3 and the X-ray 6 is 18.6 degrees. The angle (2θ) formed between the predetermined direction (D) and the diffracted X-rays (60) is 37.2 degrees.

<tensile strength>

Tensile strength (MPa) is measured based on JIS Z 2241:2011. Here, the tensile strength at room temperature is measured.

〈Ingredient Analysis〉

The composition of the aluminum alloy wire of each obtained sample is the same as that in Table 1. That is, the aluminum alloy constituting the aluminum alloy wire of each sample contains the elements shown in Table 1 within the range shown in Table 1, and the remainder contains Al and inevitable impurities. Known methods can be used to analyze the composition of aluminum alloy wire. For analysis of the composition, for example, an energy dispersive X-ray analysis device can be used.

In the following description, Sample No. 1 to Sample No. 9, Sample No. 11 to No. 19, and No. 21 to No. 29 may be collectively referred to as the first sample group. There are cases where samples No. 101 to No. 104 are combined and called the second sample group.

As shown in Tables 2 to 4, the aluminum alloy wire of the first sample group has a higher tensile strength compared to the aluminum alloy wire of the second sample group. Quantitatively, the aluminum alloy wire of the first sample group has a tensile strength of more than 425 MPa. Most samples have a tensile strength of more than 440 MPa. Depending on the composition, some samples have a high tensile strength of 470 MPa or more.

One of the reasons why the above-mentioned results were obtained is thought to be the difference in the degree of orientation of the 111 planes. In the aluminum alloy wire of the first sample group, compared to the aluminum alloy wire of the second sample group, the average value of the orientation degree of 111 planes is large, and the dispersion of the orientation degree of 111 planes is small. Quantitatively, in the aluminum alloy wire of the first sample group, the average value of the degree of orientation of the 111 sides was 50% or more, and the dispersion of the degree of orientation of the 111 sides was 45% or less. For most samples, the average value of the degree of orientation of the 111 sides is 60% or more, and the dispersion of the degree of orientation of the 111 sides is 35% or less. Depending on the composition, the average value of the degree of orientation of the 111 sides is 70% or more, and the dispersion of the degree of orientation of the 111 sides is 30% or less. This is visually explained with reference to FIGS. 2 to 5.

Figures 2 and 3 show the distribution of the orientation degree of 111 planes for the aluminum alloy wire of sample No. 3. Figures 4 and 5 show the distribution of the orientation degree of 111 planes for the aluminum alloy wire of sample No. 1.

Figures 2 and 4 are diagrams in which the orientation of 111 planes at each of the above-described measurement points across the entire cross section of the aluminum alloy wire is converted into shades of gray scale. The bars shown on the right side of FIG. 2 and the right side of FIG. 4 represent lightness and shade according to the number of counts. The orientation of the 111 sides of each measurement point is converted into a count number from zero to 100, for example. Black means that the count is zero. White means the count is 100. The greater the degree of orientation of the 111 plane, the greater the count, that is, the closer it is to white.

Figures 3 and 5 show the distribution of orientation degrees of 111 planes as contour lines. Each contour line connects measurement points with the same orientation on 111 planes. Figures 2 and 4 show the following four types of contour lines. The thin solid line is a contour line connecting the measurement points where the orientation of the 111 planes is 20%. The thin dashed line is a contour line connecting the measurement points where the orientation of the 111 planes is 40%. The thin dotted line is a contour line connecting the measurement points where the orientation of the 111 planes is 60%. The thick solid line is a contour line connecting the measurement points where the orientation of the 111 planes is 80%.

In the aluminum alloy wire of sample No. 3, which has a high tensile strength of 470 MPa, there are many white measurement points, a few light gray measurement points, and almost no black measurement points, as shown in FIG. 2. In other words, there are many measurement points with high count counts, and the variation in count counts is small. The fact that there are many measurement points with high count counts is also supported by the fact that the area surrounded by a thick solid line has a large area, as shown in FIG. 3. Here, the shape and size of the area surrounded by the thick solid line are quite close to the shape and size of the cross section of the aluminum alloy wire of Sample No. 3. Additionally, the area with this large area contains almost no areas surrounded by other contour lines. The small deviation is also supported by the fact that the areas surrounded by the four types of contour lines described above draw approximately the same shape, as shown in FIG. 3. The aluminum alloy wire of sample No. 3 has 111 planes equally oriented in the normal direction of the cross section throughout the cross section. By having such a structure in which 111 planes are oriented, the aluminum alloy wire of Sample No. 3 is thought to have high tensile strength.

In the aluminum alloy wire of Sample No. 1, which has a lower tensile strength than Sample No. 3, more dark gray measurement points and black measurement points are seen than those of Sample No. 3, as shown in FIG. 4. Additionally, dark gray measurement points are dotted. In other words, it includes measurement points with small count counts, and the variation in count counts is somewhat large. The inclusion of measurement points with small count numbers is also supported by the presence of a plurality of areas surrounded by thin solid lines, as shown in FIG. 5 . The fact that the deviation is somewhat large is also supported by the fact that the shapes and sizes of the areas surrounded by the four types of contour lines described above are different, as shown in FIG. 5. Additionally, there are multiple areas surrounded by thick solid lines, but the total area is small. From this, it is thought that the aluminum alloy wire of the second sample group, which has a lower tensile strength than sample No. 1, contains many measurement points with a smaller count than sample No. 1, and also has a large variation in count counts.

In addition, the following results appear from this test.

(1) The aluminum alloy wire having the first composition and the second composition tends to have a larger average value of the degree of orientation of the 111 planes than the aluminum alloy wire having the third composition, and the dispersion of the degree of orientation of the 111 planes tends to be smaller. In this respect, the aluminum alloy wire having the first composition and the second composition has higher strength.

(2) An aluminum alloy wire in which the average value of the degree of orientation of 111 planes is large and the dispersion of the degree of orientation of 111 planes is small in the state in which solution treatment and aging treatment have been performed is manufactured by a manufacturing method that satisfies the above-mentioned <conditions>. It can be manufactured. In the aluminum alloy wire of the first sample group, it is believed that dislocations are accumulated in the state after the second wire drawing process by satisfying the above-mentioned <Conditions>. On the other hand, in the aluminum alloy wire of the second sample group, the degree of second wire drawing is small compared to the aluminum alloy wire of the first sample group. In addition, in the aluminum alloy wire of the second sample group, the workability of the second wire drawing process is smaller than that of the first wire drawing process, or is the same as the workability of the first wire drawing process. From these points, it is thought that dislocations are not sufficiently accumulated in the aluminum alloy wire of the second sample group in the state after the second wire drawing process.

The present disclosure is not limited to these examples, but is indicated by the terms of the claims, and is intended to include all changes within the scope and meaning equivalent to the terms of the claims. For example, in Test Example 1, the composition of the aluminum alloy can be changed, or the manufacturing conditions, such as the degree of wire-drawing processing and the softening treatment conditions, can be changed.

1: Aluminum alloy wire 3: Sample
10: end surface 11: elongated part
30: cross section 6, 60: X-ray
51: movable stage 51f: surface
52: detector 53: computing device
D: Direction F: Face index
θ, 2θ: angle

Claims (8)

Silicone: 0.6% by mass or more and 1.5% by mass or less,
Magnesium: 0.5% by mass or more and 1.3% by mass or less,
Copper 0.1% by mass or more and 1.2% by mass or less,
It has a composition containing not less than 0.2% by mass and not more than 1.15% by mass of manganese, with the balance containing aluminum and inevitable impurities,
An aluminum alloy in which the average value of the orientation degree of 111 planes obtained by X-ray diffraction of the entire cross section in a state in which solution treatment and aging treatment have been performed is 50% or more, and the dispersion of the orientation degree of the 111 planes is 45% or less. The method of claim 1, further comprising at least one element selected from the group consisting of iron, chromium, zinc, titanium and zirconium,
The iron content is greater than 0% by mass and less than or equal to 0.8% by mass,
The content of chromium is greater than 0% by mass and less than or equal to 0.35% by mass,
The zinc content is greater than 0% by mass and less than or equal to 0.5% by mass,
The titanium content is greater than 0% by mass and less than or equal to 0.2% by mass,
An aluminum alloy wherein the zirconium content is greater than 0% by mass and less than or equal to 0.2% by mass. The method of claim 2, wherein the silicon is 1.0% by mass or more and 1.3% by mass or less,
Magnesium: 0.5% by mass or more and 1.2% by mass or less,
0.3 mass% or more and 0.8 mass% or less of iron,
Copper 0.1% by mass or more and 0.4% by mass or less,
Manganese: 0.2% by mass or more and 0.5% by mass or less,
Chromium exceeding 0% by mass but not more than 0.3% by mass,
An aluminum alloy having a composition containing 0.001% by mass or more and 0.1% by mass or less of titanium, with the balance containing aluminum and inevitable impurities. The method of claim 2, wherein the silicon is 0.6% by mass or more and 1.5% by mass or less,
Magnesium: 0.7% by mass or more and 1.3% by mass or less,
Iron 0.02% by mass or more and 0.4% by mass or less,
Copper 0.5 mass% or more and 1.2 mass% or less,
Manganese: 0.5% by mass or more and 1.1% by mass or less,
Chromium exceeding 0% by mass but not more than 0.3% by mass,
Zinc 0.005% by mass or more and 0.5% by mass or less,
Titanium 0.01% by mass or more and 0.2% by mass or less,
An aluminum alloy having a composition containing 0.05% by mass or more and 0.2% by mass or less of zirconium, with the balance containing aluminum and inevitable impurities. The aluminum alloy according to any one of claims 1 to 4, wherein the tensile strength is greater than 425 MPa when solution treated and aged. An aluminum alloy ship comprising the aluminum alloy according to any one of claims 1 to 5. Contains 0.6 mass% or more and 1.5 mass% or less of silicon, 0.5 mass% or more and 1.3 mass% or less of magnesium, 0.1 mass% or more and 1.2 mass% or less of copper, and 0.2 mass% or more and 1.15 mass% or less of manganese, with the balance being aluminum and A process of manufacturing a workpiece by subjecting a cast material of aluminum alloy having a composition containing unavoidable impurities to plastic working;
A process of manufacturing a first drawn material by subjecting the processed material to a first cold drawing process;
A process of manufacturing a softened material by subjecting the first wire material to a softening treatment, and
A process of manufacturing a second wire drawing material by subjecting the softened material to a second cold drawing process,
A method of manufacturing an aluminum alloy wire, wherein the degree of workability in the second wire drawing is 20% or more and is greater than the workability in the first wire drawing. The method of claim 7, wherein the aluminum alloy further contains at least one element selected from the group consisting of iron, chromium, zinc, titanium, and zirconium,
The iron content is greater than 0% by mass and less than or equal to 0.8% by mass,
The content of chromium is greater than 0% by mass and less than or equal to 0.35% by mass,
The zinc content is greater than 0% by mass and less than or equal to 0.5% by mass,
The titanium content is greater than 0% by mass and less than or equal to 0.2% by mass,
A method for manufacturing an aluminum alloy wire, wherein the zirconium content is greater than 0% by mass and less than or equal to 0.2% by mass.

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