CN114934216A - High-strength aerospace material and preparation method thereof - Google Patents
High-strength aerospace material and preparation method thereof Download PDFInfo
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- CN114934216A CN114934216A CN202210696245.7A CN202210696245A CN114934216A CN 114934216 A CN114934216 A CN 114934216A CN 202210696245 A CN202210696245 A CN 202210696245A CN 114934216 A CN114934216 A CN 114934216A
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- 239000011825 aerospace material Substances 0.000 title claims abstract description 36
- 238000002360 preparation method Methods 0.000 title claims abstract description 13
- 229910001148 Al-Li alloy Inorganic materials 0.000 claims abstract description 32
- JFBZPFYRPYOZCQ-UHFFFAOYSA-N [Li].[Al] Chemical compound [Li].[Al] JFBZPFYRPYOZCQ-UHFFFAOYSA-N 0.000 claims abstract description 32
- 239000001989 lithium alloy Substances 0.000 claims abstract description 32
- 239000004005 microsphere Substances 0.000 claims abstract description 31
- 238000002844 melting Methods 0.000 claims abstract description 14
- 230000008018 melting Effects 0.000 claims abstract description 14
- 239000012535 impurity Substances 0.000 claims abstract description 6
- 238000003723 Smelting Methods 0.000 claims description 32
- 229910045601 alloy Inorganic materials 0.000 claims description 26
- 239000000956 alloy Substances 0.000 claims description 26
- 239000000463 material Substances 0.000 claims description 19
- 239000006104 solid solution Substances 0.000 claims description 13
- 239000007788 liquid Substances 0.000 claims description 12
- 229910052744 lithium Inorganic materials 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 10
- 230000032683 aging Effects 0.000 claims description 9
- 229910052802 copper Inorganic materials 0.000 claims description 8
- 229910052749 magnesium Inorganic materials 0.000 claims description 8
- 229910052748 manganese Inorganic materials 0.000 claims description 8
- 229910052709 silver Inorganic materials 0.000 claims description 8
- 229910052725 zinc Inorganic materials 0.000 claims description 8
- 229910052726 zirconium Inorganic materials 0.000 claims description 8
- 229910052782 aluminium Inorganic materials 0.000 claims description 7
- 238000003756 stirring Methods 0.000 claims description 7
- 238000001514 detection method Methods 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 5
- 239000002245 particle Substances 0.000 claims description 3
- 239000000243 solution Substances 0.000 claims description 3
- 230000000052 comparative effect Effects 0.000 description 5
- 239000011325 microbead Substances 0.000 description 5
- 238000011161 development Methods 0.000 description 4
- 230000018109 developmental process Effects 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 3
- 238000005266 casting Methods 0.000 description 3
- 230000007812 deficiency Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000002708 enhancing effect Effects 0.000 description 3
- 230000002431 foraging effect Effects 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000010791 quenching Methods 0.000 description 3
- 230000000171 quenching effect Effects 0.000 description 3
- 238000010183 spectrum analysis Methods 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 239000010881 fly ash Substances 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 229910052729 chemical element Inorganic materials 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000006355 external stress Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000002910 solid waste Substances 0.000 description 1
- 239000012798 spherical particle Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22B—PRODUCTION AND REFINING OF METALS; PRETREATMENT OF RAW MATERIALS
- C22B9/00—General processes of refining or remelting of metals; Apparatus for electroslag or arc remelting of metals
- C22B9/04—Refining by applying a vacuum
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/10—Alloys containing non-metals
- C22C1/1036—Alloys containing non-metals starting from a melt
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/10—Alloys containing non-metals
- C22C1/1036—Alloys containing non-metals starting from a melt
- C22C1/1047—Alloys containing non-metals starting from a melt by mixing and casting liquid metal matrix composites
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/10—Alloys containing non-metals
- C22C1/1094—Alloys containing non-metals comprising an after-treatment
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
- C22C32/001—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
Abstract
The invention discloses a high-strength aerospace material and a preparation method thereof, and belongs to the technical field of aerospace materials. The high-strength aerospace material comprises the following components in percentage by mass: 0.72-1.0% of Li0.6-3.15% of Cu2.6-0.72% of Mg0.23-0.72%, less than or equal to 0.45% of Mn, 0.04-0.17% of Zr0.10-0.50% of Ag0.10-0.50% of Zn, less than or equal to 0.32% of hollow microsphere, and the balance of Al and inevitable impurities. According to the invention, the hollow microspheres are added into the aluminum-lithium alloy, vacuum melting is introduced in the preparation process, and parameters are controlled during the addition of the hollow microspheres, so that the strength of the aluminum-lithium alloy is effectively improved, the density of the aluminum-lithium alloy is reduced, and the high-strength aerospace material is obtained.
Description
Technical Field
The invention relates to the technical field of aerospace materials, in particular to a high-strength aerospace material and a preparation method thereof.
Background
Aerospace materials are a very special class of materials that are closely related to military applications. Meanwhile, the progress of aerospace materials has profound influence on modern industries. The development of new materials and new processes in the aerospace field is promoted, the related technical progress and the industry development can be led and driven, and more extensive new materials and new processes for military and civil use are derived.
Aluminum alloy with excellent comprehensive performance and mature design and processing methodAnd a reliable detection means, and becomes a main structural material of the aerospace craft. The AI-Li series alloy is a novel ultra-light structure material which attracts people to pay attention in recent years, and the research and application of the alloy mark the important development in the field of aluminum alloy for more than half a century. Lithium is an extremely reactive and very light chemical element with a density of 0.533g/cm 3 1/5 for aluminum, the addition of lithium to an aluminum alloy can reduce its density and improve the properties of the alloy. The novel aluminum-lithium alloy has low density, high specific strength, high elastic modulus, good high-temperature and low-temperature performance, low fatigue crack propagation rate, good corrosion resistance and better processability, and is an ideal aerospace light structure material.
Through the development of nearly a hundred years, the aluminum lithium alloy has entered the mature period, and has become the key material in the structural design by virtue of the characteristics of high specific strength, high ratio, excellent comprehensive mechanical properties and the like. How to further improve the strength of the aluminum lithium alloy to meet more demands is a subject to be researched in the field.
Disclosure of Invention
The invention aims to provide a high-strength aerospace material and a preparation method thereof. By adding the hollow microspheres into the aluminum lithium alloy and controlling the preparation process, the novel aluminum lithium alloy with lower density and higher strength is obtained.
In order to achieve the purpose, the invention provides the following technical scheme:
one of the technical schemes of the invention is as follows: the high-strength aerospace material comprises the following components in percentage by mass:
0.72-1.0% of Li, 2.6-3.15% of Cu, 0.23-0.72% of Mg, less than or equal to 0.45% of Mn, 0.04-0.17% of Zr, 0.10-0.50% of Ag, less than or equal to 0.32% of Zn, 8-10% of hollow microspheres, and the balance of Al and inevitable impurities.
Preferably, the high-strength aerospace material comprises the following components in percentage by mass: 0.72-1.0% of Li, 2.6-3.15% of Cu, 0.23-0.72% of Mg, less than or equal to 0.45% of Mn, 0.04-0.17% of Zr, 0.10-0.50% of Ag, less than or equal to 0.32% of Zn, 10% of hollow microspheres, and the balance of Al and inevitable impurities.
Preferably, the particle size of the hollow microsphere is less than or equal to 60 mu m, and the density is 0.6-1.1 g/cm 3 。
The hollow microspheres used in the invention are light hollow spherical particles extracted from waste fly ash discharged from a power plant, the density of the hollow microspheres is low, the density of the aluminum-lithium alloy can be further reduced when the hollow microspheres are used for preparing the aluminum-lithium alloy, and meanwhile, the strength and the rigidity of a matrix material can be improved by adding the hollow microspheres. The invention takes the hollow micro-beads as raw materials, and realizes the reutilization of the solid waste of the fly ash.
In addition, for aerospace materials, weight reduction has great influence on cost reduction, and popularization and application can save a large amount of fuel resources and is beneficial to environmental protection.
The second technical scheme of the invention is as follows: the preparation method of the high-strength aerospace material comprises the following steps:
(1) preparing materials: preparing Li, Cu, Mg, Mn, Zr, Ag, Zn, cenospheres and Al according to preset mass percentage;
(2) smelting: firstly, smelting Li, Cu, Mg, Mn, Zr, Ag, Zn and Al, then adding hollow microspheres, and stirring;
(3) and (3) detection: detecting the components of the alloy liquid and adjusting;
(4) vacuum smelting: continuously carrying out vacuum melting on the adjusted alloy liquid;
(5) molding: forming the alloy liquid ingot after vacuum melting to obtain an aluminum-lithium alloy ingot;
(6) solid solution and aging treatment: and carrying out solid solution and aging treatment on the aluminum-lithium alloy ingot to prepare the high-strength aerospace material.
Preferably, the smelting temperature in the step (2) is 800-850 ℃, and the time is 60-90 min; the temperature of the hollow microspheres during adding is 600-630 ℃; the stirring speed is 800-1000 rpm, and the time is 10-15 min.
Preferably, the temperature of the vacuum melting in the step (4) is 700-750 ℃, the vacuum degree is 1000-2000 Pa, and the time is 20-30 min.
According to the invention, vacuum melting is added in the preparation process of the aluminum-lithium alloy, so that hydrogen absorption of the aluminum-lithium alloy melt is effectively prevented, the burning loss of volatile lithium elements in the melt is reduced, and the effect of enhancing the plasticity of the aluminum-lithium alloy is achieved.
Preferably, the temperature of the solution treatment in the step (6) is 400 ℃ and the time is 5 h.
Preferably, the temperature of the aging treatment in the step (6) is 180 ℃ and the time is 1 h.
The invention has the following beneficial technical effects:
according to the invention, the hollow microspheres are added into the aluminum lithium alloy, the hollow microspheres distributed in a dispersing manner block dislocation movement which causes plastic deformation of the aluminum lithium alloy, and along with the gradual increase of external stress, dislocations are bent more and more, so that dislocation loops are formed finally, and the strength of the aluminum lithium alloy is improved; under the action of external load, dislocation and slippage in the aluminum lithium alloy matrix are retarded on the interface of the aluminum lithium alloy and the hollow microspheres, and stress concentration is generated on the hollow microspheres, so that the effect of enhancing the strength of the aluminum lithium alloy is achieved; the added hollow micro-beads generate micro-cracks to consume energy by virtue of factors such as phase change, expansion mismatch and stress induction, the load toughness of the aluminum-lithium alloy is improved, and the high-strength aerospace material is obtained.
According to the invention, vacuum melting is introduced in the preparation process and parameters are controlled when the hollow microspheres are added, so that the impurity content in the prepared high-strength aerospace material is reduced, the hollow microspheres are uniformly distributed in the aluminum-lithium alloy matrix, and the purpose of enhancing the performance of the aluminum-lithium alloy is achieved.
Detailed Description
Reference will now be made in detail to various exemplary embodiments of the invention, the detailed description should not be construed as limiting the invention but as a more detailed description of certain aspects, features and embodiments of the invention. It is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention.
In addition, for numerical ranges in the present disclosure, it is understood that each intervening value, to the upper and lower limit of that range, is also specifically disclosed. Every intervening value, to the extent any stated value or intervening value in a stated range, and any other stated or intervening value in a stated range, is encompassed within the invention. The upper and lower limits of these smaller ranges may independently be included or excluded in the range.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Although only preferred methods and materials are described herein, any methods and materials similar or equivalent to those described herein can be used in the practice or testing of the present invention.
As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including but not limited to.
The hollow micro-beads used in the invention have the particle size of less than or equal to 60 mu m and the density of 0.95g/cm 3 The chemical compositions are shown in Table 1.
TABLE 1 chemical composition of cenospheres (%)
Example 1
Preparing a high-strength aerospace material:
(1) preparing materials: 0.72 percent of Li, 3.15 percent of Cu, 0.5 percent of Mg, 0.36 percent of Mn, 0.1 percent of Zr, 0.4 percent of Ag, 0.32 percent of Zn, 10 percent of hollow microsphere and 84.45 percent of Al;
(2) smelting: putting Li, Cu, Mg, Mn, Zr, Ag, Zn and Al into a smelting furnace, smelting for 90min at 800 ℃, reducing the temperature of the smelting furnace to 600 ℃, adding hollow microspheres, and stirring for 10min at the speed of 1000rpm to obtain an alloy melt;
(3) and (3) detection: detecting alloy components in the alloy melt by utilizing a spectral analysis method, and complementing the deficiency amount;
(4) vacuum smelting: putting the adjusted alloy liquid into a vacuum smelting furnace for smelting again, wherein the smelting temperature is 750 ℃, the time is 25min, and the vacuum degree is 1500 Pa;
(5) molding: casting the alloy liquid after vacuum melting into a steel mould to obtain an aluminum-lithium alloy cast ingot;
(6) solid solution and aging treatment: putting the aluminum lithium alloy cast ingot obtained in the step (5) into a box-type resistance furnace, carrying out solid solution treatment for 5h at 500 ℃, and immediately quenching by using cold water after solid solution; and putting the quenched cast ingot into a box-type resistance furnace at the temperature of 180 ℃ for aging treatment for 1h to prepare the high-strength aerospace material.
Example 2
Preparing a high-strength aerospace material:
(1) preparing materials: 0.10% of Li, 2.8% of Cu, 0.72% of Mg, 0.40% of Mn, 0.04% of Zr, 0.5% of Ag, 0.25% of Zn, 8% of hollow microsphere and 87.19% of Al;
(2) smelting: putting Li, Cu, Mg, Mn, Zr, Ag, Zn and Al into a smelting furnace, smelting for 75min at 830 ℃, reducing the temperature of the smelting furnace to 630 ℃, adding hollow microspheres, and stirring for 15min at the speed of 800rpm to obtain an alloy melt;
(3) and (3) detection: detecting alloy components in the alloy melt by utilizing a spectral analysis method, and complementing the deficiency amount;
(4) vacuum smelting: putting the adjusted alloy liquid into a vacuum smelting furnace for smelting again, wherein the smelting temperature is 730 ℃, the time is 30min, and the vacuum degree is 2000 Pa;
(5) molding: casting the alloy liquid after vacuum melting into a steel mould to obtain an aluminum-lithium alloy cast ingot;
(6) solid solution and aging treatment: putting the aluminum lithium alloy cast ingot obtained in the step (5) into a box-type resistance furnace, carrying out solid solution treatment for 5h at 500 ℃, and immediately quenching by using cold water after solid solution; and putting the quenched cast ingot into a box-type resistance furnace at the temperature of 180 ℃ for aging treatment for 1h to prepare the high-strength aerospace material.
Example 3
Preparing a high-strength aerospace material:
(1) preparing materials: 0.8% of Li, 2.6% of Cu, 0.23% of Mg, 0.30% of Mn, 0.17% of Zr, 0.1% of Ag, 0.2% of Zn, 9% of hollow microspheres and 86.6% of Al;
(2) smelting: putting Li, Cu, Mg, Mn, Zr, Ag, Zn and Al into a smelting furnace, smelting for 60min at 850 ℃, reducing the temperature of the smelting furnace to 610 ℃, adding hollow microspheres, and stirring for 12min at the speed of 900rpm to obtain an alloy melt;
(3) and (3) detection: detecting alloy components in the alloy melt by using a spectral analysis method, and complementing the deficiency amount;
(4) vacuum smelting: putting the adjusted alloy liquid into a vacuum smelting furnace for smelting again, wherein the smelting temperature is 750 ℃, the time is 25min, and the vacuum degree is 1500 Pa;
(5) molding: casting the alloy liquid after vacuum melting into a steel mould to obtain an aluminum-lithium alloy cast ingot;
(6) solid solution and aging treatment: putting the aluminum lithium alloy cast ingot obtained in the step (5) into a box-type resistance furnace, carrying out solid solution treatment for 5h at 500 ℃, and immediately quenching by using cold water after solid solution; and (3) putting the quenched cast ingot into a box-type resistance furnace at the temperature of 180 ℃ for aging treatment for 1h to obtain the high-strength aerospace material.
Comparative example 1
Preparing a high-strength aerospace material:
compared with example 1, the difference is that the addition of the hollow microbeads in step (2) is omitted, and the other steps and operations are the same as those of example 1.
Comparative example 2
Preparing a high-strength aerospace material:
the difference from example 1 is that the amount of cenospheres added was adjusted to 20%, and other steps and operations were the same as example 1.
Comparative example 3
Preparing a high-strength aerospace material:
compared with the embodiment 1, the difference is that the vacuum melting is omitted, and other steps and operations are the same as the embodiment 1.
Comparative example 4
Preparing a high-strength aerospace material:
compared with the example 1, the difference is that the temperature reduction treatment is not carried out when the hollow microspheres are added in the step (2), and other steps and operations are the same as those in the example 1.
The elastic modulus, tensile strength, yield strength and density of the high-strength aerospace materials prepared in examples 1-3 and comparative examples 1-4 were measured, and the measurement results are shown in table 2.
Table 2 results of performance measurement of high-strength aerospace material prepared from each group
As can be seen from Table 1, after the hollow microspheres are added, the elasticity modulus, the tensile strength and the yield strength of the prepared high-strength aerospace material are improved, and the density of the prepared material is lower; when the hollow micro-beads are excessively added, the strength of the material is affected; under the condition of omitting vacuum melting, all properties of the prepared material are reduced; in the process of adding the cenospheres, if the temperature of the alloy melt is not controlled, the elastic modulus of the prepared material is not changed greatly, but the tensile strength and the yield strength are obviously reduced, because the cenospheres are aggregated in the alloy melt after being added, the elastic modulus of the material is not obviously influenced, but the strength is obviously reduced due to uneven dispersion of the cenospheres.
The above-described embodiments are only intended to illustrate the preferred embodiments of the present invention, and not to limit the scope of the present invention, and various modifications and improvements made to the technical solution of the present invention by those skilled in the art without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.
Claims (8)
1. The high-strength aerospace material is characterized by comprising the following components in percentage by mass: 0.72-1.0% of Li, 2.6-3.15% of Cu, 0.23-0.72% of Mg, less than or equal to 0.45% of Mn, 0.04-0.17% of Zr, 0.10-0.50% of Ag, less than or equal to 0.32% of Zn, 8-10% of hollow microspheres, and the balance of Al and inevitable impurities.
2. The high strength aerospace material of claim 1, wherein the components, in mass percent, comprise: 0.72-1.0% of Li, 2.6-3.15% of Cu, 0.23-0.72% of Mg, less than or equal to 0.45% of Mn, 0.04-0.17% of Zr, 0.10-0.50% of Ag, less than or equal to 0.32% of Zn, 10% of hollow microspheres, and the balance of Al and inevitable impurities.
3. The high-strength aerospace material according to claim 1 or 2, wherein the cenospheres have a particle size of not more than 60 μm and a density of 0.6-1.1 g/cm 3 。
4. A preparation method of the high-strength aerospace material as claimed in any one of claims 1 to 3, characterized by comprising the following steps:
(1) preparing materials: preparing Li, Cu, Mg, Mn, Zr, Ag, Zn, cenospheres and Al according to preset mass percentage;
(2) smelting: firstly, smelting Li, Cu, Mg, Mn, Zr, Ag, Zn and Al, then adding hollow microspheres, and stirring;
(3) and (3) detection: detecting the components of the alloy liquid and adjusting;
(4) vacuum smelting: continuously carrying out vacuum melting on the adjusted alloy liquid;
(5) molding: forming the alloy liquid ingot after vacuum melting to obtain an aluminum-lithium alloy ingot;
(6) solid solution and aging treatment: and carrying out solid solution and aging treatment on the aluminum-lithium alloy cast ingot to prepare the high-strength aerospace material.
5. The preparation method according to claim 4, wherein the smelting in the step (2) is carried out at a temperature of 800-850 ℃ for 60-90 min; the temperature of the hollow microspheres during adding is 600-630 ℃; the stirring speed is 800-1000 rpm, and the time is 10-15 min.
6. The preparation method according to claim 4, wherein the temperature of the vacuum melting in the step (4) is 700-750 ℃, the vacuum degree is 1000-2000 Pa, and the time is 20-30 min.
7. The method according to claim 4, wherein the solution treatment in step (6) is carried out at a temperature of 400 ℃ for a period of 5 hours.
8. The method according to claim 4, wherein the temperature of the aging treatment in the step (6) is 180 ℃ and the time is 1 hour.
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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