High-strength wear-resistant aviation aluminum alloy material and preparation method thereof

Abstract

The invention discloses a high-strength wear-resistant aviation aluminum alloy material and a preparation method, and belongs to the technical field of alloy materials, and the high-strength wear-resistant aviation aluminum alloy material 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 balance of Al and inevitable impurities. The aluminum alloy material disclosed by the invention is high in strength, excellent in wear resistance, excellent in high temperature resistance and good in castability; the preparation method is simple, and the process is easy to control.

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, which 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 getting higher and higher, and traditional aluminum alloy materials cannot meet the high performance requirements of 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, and microcracks will occur, leading to alloy fracture. Therefore, in order to adapt to the development of the manufacturing industry, high-strength and wear-resistant aviation aluminum alloy materials and preparation methods with good castability and excellent high-temperature resistance are urgently needed. 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 thereof. 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] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: 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%, Zn1.6-2.4%, Mg1.2-1.8%, 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 wear-resistant aviation aluminum alloy material comprises 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 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 are Al and unavoidable impurities.

[0007] Preferably, the high-strength 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 of the present invention comprises the following steps:

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

[0010] (2) adding nano-TiC particles weighed in a weight percentage to alloy liquid II, stirring evenly, 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 min, 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 35-42 MPa, and the time is 4-11 min.

[0015] Preferably, the variable temperature solution treatment is: firstly kept at 520-530°C for 0.5-1.5h, then cooled to 425-435°C and kept for 1-2h.

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

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

[0018] Preferably, the aging treatment is carried out at a temperature of 130 to 140° C. and a holding time of 40 to 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 refines the grains in the alloy and enhances the precipitation strengthening effect by optimizing 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, thereby 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, as a new type of aviation aluminum alloy material, has a simple preparation method and an easy-to-control process, which 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 the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in the field without making creative work are within the scope of protection of the present invention. If the specific conditions are not specified in the embodiments, they are carried out according to the normal conditions or the conditions recommended by the manufacturer. If the manufacturer is not specified for the reagents, instruments, and components used, they are all conventional products that can be purchased commercially.

[0021] Example 1

[0022] A high-strength wear-resistant aviation aluminum alloy material, comprising the following components in weight percentage: 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 rest 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 weight percentage of the alloy material is melted 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 weight percentage of the alloy material are added, and then the temperature is raised to 910° C. to melt to form alloy liquid I, and then Si component weighed in weight percentage of the alloy material is added, and then the temperature is raised to 1045° C. to melt to form alloy liquid II, and the slag is removed and stirred evenly;

[0025] (2) adding nano-TiC particles weighed in a weight percentage to 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 temperature and solidify it to obtain a casting;

[0027] (4) The casting was subjected to variable temperature solution treatment, under the following conditions: first, it was kept at 520°C for 1.5 h, then cooled to 425°C at a rate of 0.5-1°C / min and kept at that temperature for 2 h, then cooled in a salt bath at 75°C to 100°C, and then aged at 130°C for 48 h.

[0028] Example 2

[0029] A high-strength wear-resistant aviation aluminum alloy material, comprising the following components in weight percentage: Si 4.01%, Cu 2.63%, Zn 1.84%, Mg 1.25%, Mn 1.2%, Zr 0.35%, nano-TiC particles 0.7%, and the rest 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 weight percentage of the alloy material is melted 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 weight percentage of the alloy material are added, and then the temperature is raised to 915° C. to form alloy liquid I, and then Si component weighed in weight percentage of the alloy material is added, and then the temperature is raised to 1050° C. to form alloy liquid II, and the slag is removed and stirred evenly;

[0032] (2) adding nano-TiC particles weighed in a weight percentage to 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 at this temperature and solidify it to obtain a casting;

[0034] (4) The casting was subjected to variable temperature solution treatment, under the following conditions: first, it was kept at 525°C for 1 h, then cooled to 430°C at a rate of 0.5-1°C / min and kept at that temperature for 1.5 h, then cooled in a salt bath at 85°C to 105°C, and then aged at 135°C for 44 h.

[0035] Example 3

[0036] A high-strength wear-resistant aviation aluminum alloy material, comprising the following components in weight percentage: Si 4.9%, Cu 3.2%, Zn 2.31%, Mg 1.68%, Mn 1.56%, Zr 0.5%, nano-TiC particles 1.21%, and the rest 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) The Al component weighed in weight percentage of the alloy material is melted at a melting temperature of 725° C. When the alloy is melted to a semi-molten state, Cu, Zn, Mg, Mn, and Zr components weighed in weight percentage of the alloy material are added, and then the temperature is raised to 920° C. to melt to form alloy liquid I, and then Si component weighed in weight percentage of the alloy material is added, and then the temperature is raised to 1055° C. to melt to form alloy liquid II, and the slag is removed and stirred evenly;

[0039] (2) adding nano-TiC particles weighed in a weight percentage to 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 min, then continue to keep it at this temperature and pressurize it to 42 MPa for infiltration for 4 min, and then keep it at this temperature and solidify it to obtain a casting;

[0041] (4) The casting was subjected to variable temperature solution treatment, under the following conditions: first, it was kept at 530°C for 0.5 h, then cooled to 435°C at a rate of 0.5-1°C / min and kept at that temperature for 1 h, then cooled in a salt bath at 90°C to 110°C, and then aged at 145°C for 40 h.

[0042] Example 4

[0043] A high-strength wear-resistant aviation aluminum alloy material, comprising the following components in weight percentage: Si 5.2%, Cu 3.3%, Zn 2.4%, Mg 1.8%, Mn 1.7%, Zr 0.52%, nano-TiC particles 1.3%, and the rest 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 weight percentage of the alloy material is melted 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 weight percentage of the alloy material are added, and then the temperature is raised to 925° C. to melt to form alloy liquid I, and then Si component weighed in weight percentage of the alloy material is added, and then 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 a weight percentage to 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 min, then continue to keep it at this temperature and pressurize it to 42 MPa for infiltration for 4 min, and then keep it at this temperature and solidify it to obtain a casting;

[0048] (4) The casting was subjected to variable temperature solution treatment, under the following conditions: first, it was kept at 530°C for 0.5 h, then cooled to 435°C at a rate of 0.5-1°C / min and kept at that temperature for 1 h, then cooled in a salt bath at 90°C to 110°C, and then aged at 145°C for 40 h.

[0049] Example 5

[0050] A high-strength wear-resistant aviation aluminum alloy material, comprising the following components in weight percentage: Si 4.82%, Cu 2.9%, Zn 2.2%, Mg 1.7%, Mn 1.25%, Zr 0.32%, nano-TiC particles 0.72%, and the rest 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, comprising the following components in 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 rest 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, comprising the following components in weight percentage: Si 4.12%, Cu 2.68%, Zn 1.93%, Mg 1.35%, Mn 1.32%, Zr 0.42%, nano-TiC particles 0.86%, and the rest 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, comprising the following components in weight percentage: Si 4.28%, Cu 2.75%, Zn 1.98%, Mg 1.4%, Mn 1.38%, Zr 0.44%, nano-TiC particles 0.95%, and the rest 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, comprising 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;

[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, comprising the following components in weight percentage: Si 4.46%, Cu 3%, Zn 2.15%, Mg 1.5%, Mn 1.44%, Zr 0.46%, nano-TiC particles 1.1%, and the rest 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] Embodiment 11

[0068] A high-strength wear-resistant aviation aluminum alloy material, comprising 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 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, comprising the following components in weight percentage: Si 4.65%, Cu 3.06%, Zn 2.18%, Mg 1.54%, Mn 1.47%, Zr 0.48%, nano-TiC particles 0.14%, and the rest 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, comprising the following components in weight percentage: Si 10.3%, Cu 2.63%, Zn 1.84%, Mg 1.25%, Mn 0.5%, Zr 0.1%, nano-TiC particles 0.3%, and the rest 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, comprising the following components in weight percentage: Si 8.3%, Cu 2.63%, Zn 1.84%, Mg 1.25%, Mn 0%, Zr 0.35%, nano-TiC particles 0.7%, and the rest 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, comprising the following components in weight percentage: Si0%, Cu2.63%, Zn1.84%, Mg1.25%, Mn1.2%, Zr0.35%, nano-TiC particles0.7%, and the rest 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, comprising the following components in weight percentage: Si 4.01%, Cu 2.63%, Zn 1.84%, Mg 1.25%, Mn 1.2%, Zr 0.35%, nano-TiC particles 0%, and the rest 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, comprising the following components in weight percentage: Si 4.01%, Cu 2.63%, Zn 1.84%, Mg 1.25%, Mn 1.2%, Zr 0%, nano-TiC particles 0.7%, and the rest 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 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 are the same as those in Example 2;

[0093] The method for preparing the high-strength wear-resistant aviation aluminum alloy material is different 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 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, the conditions being that it is first kept at 525°C for 1 hour, then cooled to 430°C at a rate of 0.5-1°C / min and kept at this temperature for 1.5 hours, then naturally cooled to 105°C, and then aged at 135°C for 44 hours.

[0097] The aluminum alloy materials prepared in the above Examples 1 to 12 and Comparative Examples 1 to 8 were extruded and extended by an extruder to form aluminum alloy plates, and then performance tests were performed. The strength, elongation and wear resistance are shown in Table 1 and 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 test of metallic materials - Part 1: Room temperature test method".

[0099] The test method for wear resistance is based on GB / T12444-2006 "Metallic material 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 "High Temperature Tensile Test Method for Metallic Materials".

[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 Surface normal Surface normal Easy to deform Surface damage Example 8 Surface normal Surface normal Surface normal Easy to deform Example 9 Surface normal Surface normal Surface normal Surface normal Example 10 Surface normal Surface normal Surface normal Easy to deform Embodiment 11 Surface normal Surface normal Surface normal Surface normal Comparative Example 1 There are cracks on the surface Surface damage Surface damage Surface damage Comparative Example 2 There are 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 Surface normal Surface damage Surface damage Surface damage Comparative Example 7 Surface normal Surface damage Surface damage Surface damage Comparative Example 8 Surface normal 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, higher high temperature resistance and lower wear resistance, 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 implemented in other specific forms without departing from the spirit and essential features of the present invention. Therefore, the embodiments should be considered exemplary and non-restrictive in all respects, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention.

[0111] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description 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 may also be appropriately combined to form other implementation modes 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 weight percentage: 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, and the rest are Al and inevitable 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 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 inevitable 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 inevitable 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 inevitable 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) The Al component weighed in weight percentage of the alloy material is melted and formed at a melting temperature of 715-730° C. When the alloy is melted to a semi-molten state, Cu, Zn, Mg, Mn, and Zr components weighed in weight percentage of the alloy material are added, and then the temperature is raised to 910-925° C. to melt to form alloy liquid I, and then Si component weighed in weight percentage of the alloy material is added, and then the temperature is raised to 1045-1060° C. to melt to form alloy liquid II, and the slag is removed and stirred evenly; (2) adding nano-TiC particles weighed in a weight percentage to alloy liquid II, stirring evenly, 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), variable temperature solution treatment is performed: first, the temperature is kept at 520-530°C for 0.5-1.5 hours, and then the temperature is reduced 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 temperature of the salt bath cooling is 75 to 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 insulation 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.

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