A high-strength wear-resistant aviation aluminum alloy material and its preparation method

Abstract

The present invention discloses a high-strength, wear-resistant aviation aluminum alloy material and a preparation method. The material belongs to the field of alloy material technology and comprises the following components, calculated by weight: 3.8-5.2% Si, 2.5-3.3% Cu, 1.6-2.4% Zn, 1.2-1.8% Mg, 1.1-1.7% Mn, 0.3-0.52% Zr, 0.6-1.3% nano-TiC particles, with the remainder being Al and unavoidable impurities. The aluminum alloy material of the present invention has high strength, excellent wear resistance, excellent high-temperature resistance, and good castability. Furthermore, the preparation method is simple and the process is easily controlled.

Description

Technical Field

[0001] The invention relates to a high-strength wear-resistant aviation aluminum alloy material and a preparation method thereof, belonging to the technical field of alloy materials. Background Art

[0002] Aluminum alloy materials are a type of non-ferrous metal structural materials that are most widely used in industrial fields such as aviation, aerospace, automobiles, ships, and machinery manufacturing. With the rapid development of the aerospace field, the performance requirements for aluminum alloy materials are becoming increasingly higher, and traditional aluminum alloy materials cannot meet the high performance requirements of the materials. Some existing aluminum alloy materials have certain defects. For example, high-temperature resistant aluminum alloy materials are severely worn and cannot be used continuously; high-strength or high-hardness aluminum alloy materials have poor castability and are not conducive to processing; aluminum alloy materials with good castability have insufficient strength or hardness, which will cause microcracks and lead to alloy fracture. Therefore, in order to adapt to the development of the manufacturing industry, there is an urgent need for high-strength and wear-resistant aviation aluminum alloy materials and preparation methods that have both good castability and excellent high-temperature resistance. Summary of the Invention

[0003] In order to address at least one problem existing in the above-mentioned prior art, the present invention provides a high-strength, wear-resistant aviation aluminum alloy material and a preparation method. The aluminum alloy material has high strength, excellent wear resistance, excellent high temperature resistance, and good castability, and is a new type of aviation aluminum alloy material. At the same time, the preparation method is simple and the process is easy to control.

[0004] To achieve the above objectives, the present invention adopts the following technical solution: a high-strength, wear-resistant aviation aluminum alloy material, comprising the following components in weight percentage: Si 3.8-5.2%, Cu 2.5-3.3%, Zn 1.6-2.4%, Mg 1.2-1.8%, Mn 1.1-1.7%, Zr 0.3-0.52%, nano-TiC particles 0.6-1.3%, and the rest being Al and unavoidable impurities.

[0005] Preferably, the high-strength and wear-resistant aviation aluminum alloy material includes the following components in weight percentage: Si 4.12-4.65%, Cu 2.68-3.06%, Zn 1.93-2.18%, Mg 1.35-1.54%, Mn 1.32-1.47%, Zr 0.42-0.48%, nano-TiC particles 0.86-1.14%, and the rest are Al and unavoidable impurities.

[0006] Preferably, the high-strength and wear-resistant aviation aluminum alloy material comprises the following components in weight percentage: Si 4.35%, Cu 2.86%, Zn 2.03%, Mg 1.44%, Mn 1.39%, Zr 0.45%, nano-TiC particles 1.03%, and the rest being Al and unavoidable impurities.

[0007] Preferably, the high-strength and wear-resistant aviation aluminum alloy material comprises the following components in weight percentage: Si 4.57%, Cu 2.93%, Zn 2.11%, Mg 1.46%, Mn 1.42%, Zr 0.47%, nano-TiC particles 0.98%, and the rest are Al and unavoidable impurities.

[0008] A method for preparing a high-strength, wear-resistant aviation aluminum alloy material according to the present invention comprises the following steps:

[0009] (1) Al component weighed in accordance with the weight percentage of the alloy material is melted and formed at a melting temperature of 715-730°C. Cu, Zn, Mg, Mn, and Zr components weighed in accordance with the weight percentage of the alloy material are added when the alloy is melted to a semi-molten state, and then the temperature is raised to 910-925°C to melt to form alloy liquid I. Si component weighed in accordance with the weight percentage of the alloy material is then added, and the temperature is raised to 1045-1060°C to melt to form alloy liquid II, and the slag is removed and stirred uniformly;

[0010] (2) adding nano-TiC particles weighed in accordance with the weight percentage to the alloy liquid II, stirring uniformly, and then refining under a protective gas atmosphere at a refining temperature of 715-730° C. for 15-20 min to obtain a refined melt;

[0011] (3) Casting the refined melt and keeping it at 680-690°C for 10-15 minutes, then continue to keep it warm and pressurize it for infiltration, and then solidify it under pressure to obtain a casting;

[0012] (4) The casting is subjected to variable temperature solution treatment, then cooled in a salt bath to a temperature of 100-110°C, and then subjected to aging treatment.

[0013] Preferably, the protective gas is nitrogen, and the refining vacuum is controlled to be 0.06-0.07 MPa.

[0014] Preferably, the pressure of the pressurized infiltration is 35 to 42 MPa, and the time is 4 to 11 minutes.

[0015] Preferably, the variable temperature solution treatment is: first, keep the temperature at 520-530° C. for 0.5-1.5 hours, then cool to 425-435° C. and keep the temperature for 1-2 hours.

[0016] Preferably, the cooling rate is controlled at 0.5-1°C / min.

[0017] Preferably, the salt bath cooling temperature is 75-90°C.

[0018] Preferably, the aging treatment temperature is 130-140° C. and the holding time is 40-48 hours.

[0019] The beneficial effects of the present invention are as follows: the aluminum alloy material of the present invention has high strength, excellent wear resistance, excellent high temperature resistance, good castability, and extends the service life of aluminum alloy products; the present invention optimizes the composite system and system ratio of Si, Cu, Zn, Mg, Mn, Zr elements and nano-TiC particles with Al, and optimizes the casting process and subsequent treatment process, so that the grains in the alloy are refined and the precipitation strengthening effect is enhanced, giving the aluminum alloy material excellent mechanical properties, wear resistance and heat resistance, and improving its castability; the aluminum alloy material of the present invention is a new type of aviation aluminum alloy material, the preparation method is simple, the process is easy to control, and it is conducive to application in actual production. DETAILED DESCRIPTION

[0020] The following is a clear and complete description of the technical solutions in the implementation of the present invention. The described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of the present invention. If specific conditions are not specified in the embodiments, they are carried out according to conventional conditions or the conditions recommended by the manufacturer. If the manufacturer of the reagents, instruments, and components is not specified, they are all conventional products that can be purchased commercially.

[0021] Example 1

[0022] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight: 3.8% Si, 2.5% Cu, 1.6% Zn, 1.2% Mg, 1.1% Mn, 0.3% Zr, 0.6% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0023] The method for preparing the high-strength wear-resistant aviation aluminum alloy material comprises the following steps:

[0024] (1) The Al component weighed in accordance with the weight percentage of the alloy material is melted and formed at a melting temperature of 715°C. When the alloy is melted to a semi-molten state, Cu, Zn, Mg, Mn, and Zr components weighed in accordance with the weight percentage of the alloy material are added, and then the temperature is raised to 910°C to melt to form alloy liquid I. The Si component weighed in accordance with the weight percentage of the alloy material is then added, and the temperature is raised to 1045°C to melt to form alloy liquid II. The slag is removed and stirred evenly.

[0025] (2) adding nano-TiC particles weighed in the weight percentage to the alloy liquid II, stirring evenly, and then refining under a nitrogen atmosphere at a refining temperature of 715°C, a refining time of 20 min, and a refining vacuum of 0.06 MPa to obtain a refined melt;

[0026] (3) Casting the refined melt and keeping it at 680°C for 15 minutes, then continue to keep it at this temperature and pressurize it to 35 MPa for infiltration for 11 minutes, and then keep it at this pressure and solidify it to obtain a casting;

[0027] (4) The castings were subjected to variable temperature solution treatment, which was carried out by first keeping the temperature at 520 °C for 1.5 h, then cooling to 425 °C at a rate of 0.5-1 °C / min and keeping the temperature for 2 h, then cooling in a salt bath at 75 °C to 100 °C, and then aging treatment at 130 °C for 48 h.

[0028] Example 2

[0029] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.01% Si, 2.63% Cu, 1.84% Zn, 1.25% Mg, 1.2% Mn, 0.35% Zr, 0.7% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0030] The method for preparing the high-strength wear-resistant aviation aluminum alloy material comprises the following steps:

[0031] (1) The Al component weighed in accordance with the weight percentage of the alloy material is melted and formed at a melting temperature of 720°C. When the alloy is melted to a semi-molten state, Cu, Zn, Mg, Mn, and Zr components weighed in accordance with the weight percentage of the alloy material are added, and then the temperature is raised to 915°C to melt to form alloy liquid I. The Si component weighed in accordance with the weight percentage of the alloy material is then added, and the temperature is raised to 1050°C to melt to form alloy liquid II. The slag is removed and stirred uniformly;

[0032] (2) adding nano-TiC particles weighed in the weight percentage to the alloy liquid II, stirring evenly, and then refining under a nitrogen atmosphere at a refining temperature of 720°C, a refining time of 17 min, and a refining vacuum of 0.065 MPa to obtain a refined melt;

[0033] (3) Casting the refined melt and keeping it at 685°C for 12 minutes, then continue to keep it at this temperature and pressurize it to 38 MPa for infiltration for 8 minutes, and then keep it under pressure and solidify to obtain a casting;

[0034] (4) The castings were subjected to variable temperature solution treatment, with the conditions being first to keep the temperature at 525 °C for 1 h, then cooling to 430 °C at a rate of 0.5-1 °C / min and keeping the temperature for 1.5 h, then cooling in a salt bath at 85 °C to 105 °C, and then aging treatment at 135 °C for 44 h.

[0035] Example 3

[0036] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.9% Si, 3.2% Cu, 2.31% Zn, 1.68% Mg, 1.56% Mn, 0.5% Zr, 1.21% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0037] The method for preparing the high-strength wear-resistant aviation aluminum alloy material comprises the following steps:

[0038] (1) Al component weighed in accordance with the weight percentage of the alloy material is melted and formed at a melting temperature of 725°C. Cu, Zn, Mg, Mn, and Zr components weighed in accordance with the weight percentage of the alloy material are added when the alloy is melted to a semi-molten state, and then the temperature is raised to 920°C to melt to form alloy liquid I. Si component weighed in accordance with the weight percentage of the alloy material is then added, and the temperature is raised to 1055°C to melt to form alloy liquid II, and the slag is removed and stirred uniformly;

[0039] (2) adding nano-TiC particles weighed in the weight percentage to the alloy liquid II, stirring evenly, and then refining under a nitrogen atmosphere at a refining temperature of 725°C, a refining time of 15 min, and a refining vacuum of 0.07 MPa to obtain a refined melt;

[0040] (3) Casting the refined melt and keeping it at 690°C for 10 minutes, then continue to keep it at this temperature and pressurize it to 42 MPa for 4 minutes, and then keep it at this pressure and solidify it to obtain a casting;

[0041] (4) The castings were subjected to variable temperature solution treatment, with the conditions being first to keep the temperature at 530 °C for 0.5 h, then to cool to 435 °C at a rate of 0.5-1 °C / min and keep the temperature for 1 h, then to cool in a salt bath at 90 °C to 110 °C, and then to perform aging treatment at 145 °C for 40 h.

[0042] Example 4

[0043] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 5.2% Si, 3.3% Cu, 2.4% Zn, 1.8% Mg, 1.7% Mn, 0.52% Zr, 1.3% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0044] The method for preparing the high-strength wear-resistant aviation aluminum alloy material comprises the following steps:

[0045] (1) The Al component weighed in accordance with the weight percentage of the alloy material is melted and formed at a melting temperature of 730°C. When the alloy is melted to a semi-molten state, Cu, Zn, Mg, Mn, and Zr components weighed in accordance with the weight percentage of the alloy material are added, and then the temperature is raised to 925°C to melt to form alloy liquid I. The Si component weighed in accordance with the weight percentage of the alloy material is then added, and the temperature is raised to 1060°C to melt to form alloy liquid II, and the slag is removed and stirred evenly;

[0046] (2) adding nano-TiC particles weighed in the weight percentage to the alloy liquid II, stirring evenly, and then refining under a nitrogen atmosphere at a refining temperature of 730°C, a refining time of 15 min, and a refining vacuum of 0.07 MPa to obtain a refined melt;

[0047] (3) Casting the refined melt and keeping it at 690°C for 10 minutes, then continue to keep it at this temperature and pressurize it to 42 MPa for 4 minutes, and then keep it at this pressure and solidify it to obtain a casting;

[0048] (4) The castings were subjected to variable temperature solution treatment, with the conditions being first to keep the temperature at 530 °C for 0.5 h, then to cool to 435 °C at a rate of 0.5-1 °C / min and keep the temperature for 1 h, then to cool in a salt bath at 90 °C to 110 °C, and then to perform aging treatment at 145 °C for 40 h.

[0049] Example 5

[0050] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.82% Si, 2.9% Cu, 2.2% Zn, 1.7% Mg, 1.25% Mn, 0.32% Zr, 0.72% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0051] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0052] Example 6

[0053] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 3.85% Si, 2.55% Cu, 1.7% Zn, 1.25% Mg, 1.62% Mn, 0.48% Zr, 1.2% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0054] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0055] Example 7

[0056] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.12% Si, 2.68% Cu, 1.93% Zn, 1.35% Mg, 1.32% Mn, 0.42% Zr, 0.86% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0057] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0058] Example 8

[0059] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.28% Si, 2.75% Cu, 1.98% Zn, 1.4% Mg, 1.38% Mn, 0.44% Zr, 0.95% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0060] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0061] Example 9

[0062] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.35% Si, 2.86% Cu, 2.03% Zn, 1.44% Mg, 1.39% Mn, 0.45% Zr, 1.03% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0063] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0064] Example 10

[0065] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.46% Si, 3% Cu, 2.15% Zn, 1.5% Mg, 1.44% Mn, 0.46% Zr, 1.1% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0066] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0067] Example 11

[0068] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.57% Si, 2.93% Cu, 2.11% Zn, 1.46% Mg, 1.42% Mn, 0.47% Zr, 0.98% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0069] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0070] Example 12

[0071] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.65% Si, 3.06% Cu, 2.18% Zn, 1.54% Mg, 1.47% Mn, 0.48% Zr, 0.14% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0072] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0073] Comparative Example 1

[0074] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 10.3% Si, 2.63% Cu, 1.84% Zn, 1.25% Mg, 0.5% Mn, 0.1% Zr, 0.3% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0075] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0076] Comparative Example 2

[0077] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 8.3% Si, 2.63% Cu, 1.84% Zn, 1.25% Mg, 0% Mn, 0.35% Zr, 0.7% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0078] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0079] Comparative Example 3

[0080] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: Si 0%, Cu 2.63%, Zn 1.84%, Mg 1.25%, Mn 1.2%, Zr 0.35%, nano-TiC particles 0.7%, and the remainder being Al and unavoidable impurities;

[0081] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0082] Comparative Example 4

[0083] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.01% Si, 2.63% Cu, 1.84% Zn, 1.25% Mg, 1.2% Mn, 0.35% Zr, 0% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0084] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0085] Comparative Example 5

[0086] A high-strength, wear-resistant aviation aluminum alloy material comprises the following components, calculated by weight percentage: 4.01% Si, 2.63% Cu, 1.84% Zn, 1.25% Mg, 1.2% Mn, 0% Zr, 0.7% nano-TiC particles, and the remainder being Al and unavoidable impurities.

[0087] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is the same as that in Example 2.

[0088] Comparative Example 6

[0089] A high-strength, wear-resistant aviation aluminum alloy material, the components and weight percentages of which are the same as those in Example 2;

[0090] The method for preparing the high-strength wear-resistant aviation aluminum alloy material is different from that of Example 2 in that: in step (3), the refined melt is cast and kept warm and pressurized for 12 minutes at a temperature of 685° C. and a pressure of 38 MPa.

[0091] Comparative Example 7

[0092] A high-strength, wear-resistant aviation aluminum alloy material, the components and weight percentages of which are the same as those in Example 2;

[0093] The method for preparing the high-strength wear-resistant aviation aluminum alloy material differs from that of Example 2 in that: in step (4), the casting is solution treated at a temperature of 525°C for 4 hours, then cooled in a salt bath at a temperature of 85°C to a temperature of 105°C, and then aged at a temperature of 135°C for 44 hours.

[0094] Comparative Example 8

[0095] A high-strength, wear-resistant aviation aluminum alloy material, the components and weight percentages of which are the same as those in Example 2;

[0096] The preparation method of the high-strength wear-resistant aviation aluminum alloy material is different from that of Example 2 in that: (4) the casting is subjected to a variable temperature solution treatment, under the conditions of first keeping it at 525°C for 1 hour, then cooling it to 430°C at a rate of 0.5-1°C / min and keeping it at that temperature for 1.5 hours, then naturally cooling it to a temperature of 105°C, and then performing an aging treatment at a temperature of 135°C for 44 hours.

[0097] The aluminum alloy materials prepared in Examples 1 to 12 and Comparative Examples 1 to 8 were extruded and extended by an extruder to form aluminum alloy plates. The performance tests were then conducted. The strength, elongation, and wear resistance were shown in Table 1 and the high temperature performance Tables 2 and 3.

[0098] The test methods for strength and elongation are determined in accordance with GB / T 228.1-2010 "Tensile tests on metallic materials - Part 1: Room temperature test methods".

[0099] The test method for wear resistance is based on GB / T12444-2006 "Metallic materials wear test method - Test ring-test block sliding wear test".

[0100] The test method for high temperature performance is determined in accordance with GB / T 4338-2006 "Metallic Materials - High Temperature Tensile Test Method".

[0101] Table 1 Strength, elongation and wear resistance at room temperature

[0102]

[0103]

[0104] Table 2 Strength, elongation and wear resistance at 500℃

[0105]

[0106]

[0107] Table 3 Castability and high temperature resistance

[0108] Room temperature 550℃ 600℃ 650℃ Example 2 Normal surface Normal surface Easy to deform Surface damage Example 8 Normal surface Normal surface Normal surface Easy to deform Example 9 Normal surface Normal surface Normal surface Normal surface Example 10 Normal surface Normal surface Normal surface Easy to deform Example 11 Normal surface Normal surface Normal surface Normal surface Comparative Example 1 Cracks on the surface Surface damage Surface damage Surface damage Comparative Example 2 Cracks on the surface Surface damage Surface damage Surface damage Comparative Example 3 Surface microcracks Surface damage Surface damage Surface damage Comparative Example 4 Surface microcracks Surface damage Surface damage Surface damage Comparative Example 5 Surface microcracks Surface damage Surface damage Surface damage Comparative Example 6 Normal surface Surface damage Surface damage Surface damage Comparative Example 7 Normal surface Surface damage Surface damage Surface damage Comparative Example 8 Normal surface Surface damage Surface damage Surface damage

[0109] According to the data results in Tables 1, 2 and 3 above, the embodiments of the present invention optimize the composite system and system ratio of Si, Cu, Zn, Mg, Mn, Zr elements and nano-TiC particles with Al, and the aluminum alloy material of the present invention has good castability, and is combined with optimized casting process and subsequent treatment process to further improve the mechanical properties, wear resistance and high temperature resistance of the aluminum alloy material; compared with the comparative example, the aluminum alloy material of the embodiment of the present invention has higher tensile strength, yield strength and elongation at break, which greatly improves the strength of the aluminum alloy material, has good castability, and has higher high temperature resistance and lower wear resistance, which can meet the requirements of high-performance aluminum alloy materials and is a new type of aviation aluminum alloy material.

[0110] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the present invention can be embodied in other specific forms without departing from the spirit and essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations that come within the meaning and range of equivalents of the claims be embraced therein.

[0111] In addition, it should be understood that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

Claims

1. A high-strength, wear-resistant aviation aluminum alloy material, characterized in that: The invention comprises the following components in percentage by weight: 3.8-5.2% of Si, 2.5-3.3% of Cu, 1.6-2.4% of Zn, 1.2-1.8% of Mg, 1.1-1.7% of Mn, 0.3-0.52% of Zr, 0.6-1.3% of nano-TiC particles, and the rest being Al and unavoidable impurities.

2. The high-strength, wear-resistant aviation aluminum alloy material according to claim 1, characterized in that: The invention comprises the following components in percentage by weight: Si 4.12-4.65%, Cu 2.68-3.06%, Zn 1.93-2.18%, Mg 1.35-1.54%, Mn 1.32-1.47%, Zr 0.42-0.48%, nano-TiC particles 0.86-1.14%, and the rest being Al and unavoidable impurities.

3. A high-strength, wear-resistant aviation aluminum alloy material according to claim 2 or 1, characterized in that: The invention comprises the following components in weight percentage: Si 4.35%, Cu 2.86%, Zn 2.03%, Mg 1.44%, Mn 1.39%, Zr 0.45%, nano-TiC particles 1.03%, and the rest are Al and unavoidable impurities.

4. A high-strength, wear-resistant aviation aluminum alloy material according to claim 2 or 1, characterized in that: The invention comprises the following components in weight percentage: Si 4.57%, Cu 2.93%, Zn 2.11%, Mg 1.46%, Mn 1.42%, Zr 0.47%, nano-TiC particles 0.98%, and the rest are Al and unavoidable impurities.

5. A method for preparing the high-strength, wear-resistant aviation aluminum alloy material according to claim 1, characterized in that: The following steps are involved: (1) Al component weighed in accordance with the weight percentage of the alloy material is melted and formed at a melting temperature of 715-730°C. Cu, Zn, Mg, Mn, and Zr components weighed in accordance with the weight percentage of the alloy material are added when the alloy is melted to a semi-molten state, and then the temperature is raised to 910-925°C to melt to form alloy liquid I. Si component weighed in accordance with the weight percentage of the alloy material is then added, and the temperature is raised to 1045-1060°C to melt to form alloy liquid II, and the slag is removed and stirred uniformly; (2) adding nano-TiC particles weighed in accordance with the weight percentage to the alloy liquid II, stirring uniformly, and then refining under a protective gas atmosphere at a refining temperature of 715-730° C. for 15-20 min to obtain a refined melt; (3) Casting the refined melt and keeping it at 680-690°C for 10-15 minutes, then continue to keep it warm and pressurize it for infiltration, and then solidify it under pressure to obtain a casting; (4) The casting is subjected to variable temperature solution treatment, then cooled in a salt bath to a temperature of 100-110°C, and then subjected to aging treatment.

6. The method for preparing a high-strength wear-resistant aviation aluminum alloy material according to claim 5, characterized in that: In step (3), the pressure of the pressurized infiltration is 35 to 42 MPa, and the time is 4 to 11 minutes.

7. The method for preparing a high-strength wear-resistant aviation aluminum alloy material according to claim 5, characterized in that: In step (4), the temperature-variable solution treatment is carried out: first, the temperature is kept at 520-530°C for 0.5-1.5 hours, and then the temperature is lowered to 425-435°C and kept for 1-2 hours.

8. The method for preparing a high-strength wear-resistant aviation aluminum alloy material according to claim 5, characterized in that: In step (4), the salt bath cooling temperature is 75-90°C.

9. The method for preparing a high-strength wear-resistant aviation aluminum alloy material according to claim 5, characterized in that: In step (4), aging treatment: the temperature is 130-140° C., and the holding time is 40-48 h.

10. The method for preparing a high-strength, wear-resistant aviation aluminum alloy material according to claim 5, characterized in that: In step (2), the protective gas is nitrogen, and the refining vacuum is controlled to be 0.06-0.07 MPa.

Images