CN115874031B - Processing method of 2A12 aluminum alloy plate for aviation - Google Patents
Processing method of 2A12 aluminum alloy plate for aviation Download PDFInfo
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- CN115874031B CN115874031B CN202211566925.3A CN202211566925A CN115874031B CN 115874031 B CN115874031 B CN 115874031B CN 202211566925 A CN202211566925 A CN 202211566925A CN 115874031 B CN115874031 B CN 115874031B
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 57
- 238000003672 processing method Methods 0.000 title claims abstract description 11
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 40
- 239000000956 alloy Substances 0.000 claims abstract description 40
- 238000010438 heat treatment Methods 0.000 claims abstract description 40
- 238000000034 method Methods 0.000 claims abstract description 39
- 238000005096 rolling process Methods 0.000 claims description 36
- 238000005266 casting Methods 0.000 claims description 33
- 238000001816 cooling Methods 0.000 claims description 16
- 238000003723 Smelting Methods 0.000 claims description 10
- 229910052751 metal Inorganic materials 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 7
- 239000000498 cooling water Substances 0.000 claims description 6
- 239000000839 emulsion Substances 0.000 claims description 6
- 238000010008 shearing Methods 0.000 claims description 6
- 239000007921 spray Substances 0.000 claims description 6
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 5
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 claims description 5
- ZGUQGPFMMTZGBQ-UHFFFAOYSA-N [Al].[Al].[Zr] Chemical compound [Al].[Al].[Zr] ZGUQGPFMMTZGBQ-UHFFFAOYSA-N 0.000 claims description 5
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 claims description 5
- CSDREXVUYHZDNP-UHFFFAOYSA-N alumanylidynesilicon Chemical compound [Al].[Si] CSDREXVUYHZDNP-UHFFFAOYSA-N 0.000 claims description 5
- 229910052782 aluminium Inorganic materials 0.000 claims description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 5
- 238000009529 body temperature measurement Methods 0.000 claims description 5
- 229910052802 copper Inorganic materials 0.000 claims description 5
- 239000010949 copper Substances 0.000 claims description 5
- 238000005098 hot rolling Methods 0.000 claims description 5
- UGKDIUIOSMUOAW-UHFFFAOYSA-N iron nickel Chemical compound [Fe].[Ni] UGKDIUIOSMUOAW-UHFFFAOYSA-N 0.000 claims description 5
- KBMLJKBBKGNETC-UHFFFAOYSA-N magnesium manganese Chemical compound [Mg].[Mn] KBMLJKBBKGNETC-UHFFFAOYSA-N 0.000 claims description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 5
- 239000002994 raw material Substances 0.000 claims description 5
- 239000012856 weighed raw material Substances 0.000 claims description 5
- 238000005303 weighing Methods 0.000 claims description 5
- 238000007599 discharging Methods 0.000 claims description 4
- 238000003801 milling Methods 0.000 claims description 4
- 238000001514 detection method Methods 0.000 abstract description 11
- 238000004519 manufacturing process Methods 0.000 abstract description 11
- 238000000265 homogenisation Methods 0.000 abstract description 5
- 238000002360 preparation method Methods 0.000 abstract description 3
- 239000000463 material Substances 0.000 description 4
- 239000012535 impurity Substances 0.000 description 3
- 238000000137 annealing Methods 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 229910017818 Cu—Mg Inorganic materials 0.000 description 1
- QQHSIRTYSFLSRM-UHFFFAOYSA-N alumanylidynechromium Chemical compound [Al].[Cr] QQHSIRTYSFLSRM-UHFFFAOYSA-N 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005496 eutectics Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Metal Rolling (AREA)
Abstract
A processing method of an aviation 2A12 aluminum alloy plate relates to a processing method of an aluminum alloy plate. The invention aims to solve the technical problems of complex homogenization treatment and heating process and long processing time of the 2A12 alloy. According to the invention, when the ingot is subjected to homogenization treatment and ingot heating, a method of integrating uniform heating is adopted, so that two steps of working procedures are shortened into one step of working procedure, the production process takes about 40 hours, at least 15 hours is saved compared with the existing process, the mechanical properties the same as those of a hot rolled plate are obtained, the productivity is greatly saved, and the production cost is reduced; the flaw detection results of the 2A12 aluminum alloy plate prepared by the method are all above A level, part of the flaw detection results can reach AA level or AAA level, and the flaw detection results of the plate obtained by the original preparation method are basically B level or not reach the lowest level.
Description
Technical Field
The invention relates to a processing method of an aluminum alloy plate.
Background
The 2A12 aluminum alloy (Al-Cu-Mg alloy) is a heat-treatable strengthening alloy, and is an aluminum alloy structural material widely applied in China and having good comprehensive performance. The composite material has the characteristics of small density, high strength, excellent corrosion resistance, good formability, good low-temperature performance and the like, and is widely applied to the field of military materials such as aviation, aerospace, ship manufacturing and the like. The main states of the 2A12 aluminum alloy are H112, T351 and T4, and the alloy is mainly used for manufacturing parts such as a framework, a skin, ribs, spars and the like of an airplane. The 2A12 aluminum alloy plate needs to be subjected to homogenizing annealing and ingot heating before rolling, and the homogenizing annealing aims to uniformly distribute unbalanced eutectic structures in the ingot in a matrix and eliminate casting stress; the purpose of ingot heating is to reduce metal deformation resistance, improve alloy plasticity and facilitate subsequent production, processing and use. However, the homogenization treatment and heating processes of the 2A12 alloy are complex, the processing time is long, and the processing efficiency is affected.
Disclosure of Invention
The invention aims to solve the technical problems of complicated homogenization treatment and heating process and long processing time of a 2A12 alloy, and provides a processing method of an aviation 2A12 aluminum alloy plate.
The processing method of the aviation 2A12 aluminum alloy plate comprises the following steps:
1. according to the mass percentage of elements, si is 0.1 to 0.27 percent, fe is 0.15 to 0.45 percent, cu is 4.55 to 4.85 percent, mn is 0.5 to 0.80 percent, mg is 1.5 to 1.8 percent, ni is 0 to 0.1 percent, zn is 0.08 to 0.2 percent, ti is 0 to 0.1 percent, zr is 0.05 to 0.15 percent, fe+Ni is 0 to 0.5 percent and the balance is Al, respectively weighing an aluminum-silicon intermediate alloy, an iron-nickel intermediate alloy, electrolytic copper, a magnesium-manganese intermediate alloy, a pure zinc ingot, an aluminum-titanium intermediate alloy, an aluminum-zirconium intermediate alloy and an aluminum ingot as raw materials, putting the weighed raw materials into a dry smelting furnace, and smelting for 5 to 6 hours at 890 to 924 ℃ to obtain an aluminum alloy solution;
the single impurity in the aviation 2A12 aluminum alloy plate is less than or equal to 0.05 percent, and the total impurity is less than 0.1 percent, so that the impurity in the range has no influence on the performance of the plate;
2. casting the aluminum alloy solution in the first step into an aluminum alloy square ingot by adopting a semi-continuous water-cooling casting method; the thickness of the aluminum alloy square ingot is 420mm, and the width is 1820mm;
the semi-continuous water-cooling casting method comprises the following technological parameters: the casting temperature is 750-770 ℃, the casting speed is 80-12 mm/min, and the cooling water pressure is 0.25-0.38 MPa;
3. placing the square aluminum alloy ingot obtained in the second step into a longitudinal pushing type heating furnace for uniform heating integrated treatment after surface milling and sawing to obtain an aluminum alloy ingot capable of being directly rolled:
the homogeneous heating integrated process comprises the following steps: vertically arranging aluminum alloy square ingots, arranging a plurality of N-type or K-type couples between each layer for metal temperature measurement, setting the heating temperature to be 520-550 ℃, changing the setting temperature to be 490-500 ℃ when the high-point temperature of the ingots measured by the couples reaches 480+/-5 ℃, changing the setting temperature to be 475-480 ℃ when the low-point temperature of the ingots measured by the couples reaches 475+/-5 ℃, preserving heat for 19-22 h, and discharging and rolling when the temperature of the ingots reaches 475-480 ℃;
4. rolling the cast ingot in the third step, wherein the rolling temperature is 470-480 ℃, the maximum processing deformation is controlled to be 32-41%, the plate is rolled to 74-82% of the thickness of the finished product, and the thickness allowance of 18-26% is reserved, so that a hot-rolled long plate is obtained;
5. performing temperature control rolling on the hot rolled long plate obtained in the step four, performing spray cooling on the plate by using hot rolling mill emulsion, controlling the temperature of the plate to be 140-220 ℃, continuing rolling, finishing rolling the thickness allowance reserved in the step four, and shearing according to the multiple length number to obtain a prefabricated plate;
6. stretching the prefabricated plate obtained in the fifth step, and sawing to obtain a finished plate; the elongation parameters were 2.4% + -0.2.
According to the invention, in the third step, a production process integrating uniform heating is adopted, so that the production period of the 2A12 aluminum alloy plate is greatly shortened, and meanwhile, the flaw detection grade of the plate is improved.
The invention has the advantages that:
1. the invention is a novel simple processing method of 2A12 aluminum alloy plate, when the ingot homogenization treatment and ingot heating are adopted, the two steps are shortened into one step by adopting a method of uniform heating integration, the production process takes about 40 hours, compared with the prior art, the production process saves at least 15 hours, and the mechanical property the same as that of the hot rolled plate is obtained, thereby greatly saving the productivity and reducing the production cost;
2. compared with the plate prepared by the original method, the 2A12 aluminum alloy plate prepared by the invention has the advantages that the temperature control rolling technology is utilized, the Zr element control is added, the flaw detection result of the plate can be greatly improved, and the plate has better safety level when being applied to the fields of aviation, aerospace and the like. With GB/T6519-2013 as a detection standard, flaw detection results of the aluminum alloy plate prepared by the method are all above A level, part of the flaw detection results can reach AA level or AAA level, and the flaw detection results of the plate obtained by the original preparation method are basically B level or not reach the lowest level.
Drawings
FIG. 1 is a photograph of a metallographic structure of a 2A12-H112 alloy using a conventional "ingot soaking+ingot heating" process;
FIG. 2 is a photograph of the metallographic structure of the 2A12-H112 alloy prepared by the process of test one.
Detailed Description
The first embodiment is as follows: the embodiment is a processing method of an aviation 2A12 aluminum alloy plate, which specifically comprises the following steps:
1. according to the mass percentage of elements, si is 0.1 to 0.27 percent, fe is 0.15 to 0.45 percent, cu is 4.55 to 4.85 percent, mn is 0.5 to 0.80 percent, mg is 1.5 to 1.8 percent, ni is 0 to 0.1 percent, zn is 0.08 to 0.2 percent, ti is 0 to 0.1 percent, zr is 0.05 to 0.15 percent, fe+Ni is 0 to 0.5 percent and the balance is Al, respectively weighing an aluminum-silicon intermediate alloy, an iron-nickel intermediate alloy, electrolytic copper, a magnesium-manganese intermediate alloy, a pure zinc ingot, an aluminum-titanium intermediate alloy, an aluminum-zirconium intermediate alloy and an aluminum ingot as raw materials, putting the weighed raw materials into a dry smelting furnace, and smelting for 5 to 6 hours at 890 to 924 ℃ to obtain an aluminum alloy solution;
2. casting the aluminum alloy solution in the first step into an aluminum alloy square ingot by adopting a semi-continuous water-cooling casting method; the thickness of the aluminum alloy square ingot is 420mm, and the width is 1820mm;
the semi-continuous water-cooling casting method comprises the following technological parameters: the casting temperature is 750-770 ℃, the casting speed is 80-120 mm/min, and the cooling water pressure is 0.25-0.38 MPa;
3. placing the square aluminum alloy ingot obtained in the second step into a longitudinal pushing type heating furnace for uniform heating integrated treatment after surface milling and sawing to obtain an aluminum alloy ingot capable of being directly rolled:
the homogeneous heating integrated process comprises the following steps: vertically arranging aluminum alloy square ingots, arranging a plurality of N-type or K-type couples between each layer for metal temperature measurement, setting the heating temperature to be 520-550 ℃, changing the setting temperature to be 490-500 ℃ when the high-point temperature of the ingots measured by the couples reaches 480+/-5 ℃, changing the setting temperature to be 475-480 ℃ when the low-point temperature of the ingots measured by the couples reaches 475+/-5 ℃, preserving heat for 19-22 h, and discharging and rolling when the temperature of the ingots reaches 475-480 ℃;
4. rolling the cast ingot in the third step, wherein the rolling temperature is 470-480 ℃, the maximum processing deformation is controlled to be 32-41%, the plate is rolled to 74-82% of the thickness of the finished product, and the thickness allowance of 18-26% is reserved, so that a hot-rolled long plate is obtained;
5. performing temperature control rolling on the hot rolled long plate obtained in the step four, performing spray cooling on the plate by using hot rolling mill emulsion, controlling the temperature of the plate to be 140-220 ℃, continuing rolling, finishing rolling the thickness allowance reserved in the step four, and shearing according to the multiple length number to obtain a prefabricated plate;
6. stretching the prefabricated plate obtained in the fifth step, and sawing to obtain a finished plate; the elongation parameters were 2.4% + -0.2.
The second embodiment is as follows: the first difference between this embodiment and the specific embodiment is that: in the first step, according to the mass percentages of elements, si of 0.12%, fe of 0.18%, cu of 4.51%, mn of 0.63%, mg of 1.57%, ni of 0.0053%, zn of 0.068%, ti of 0.0264%, zr of 0.11%, fe+Ni of 0-0.5% and the balance Al, respectively weighing an aluminum-silicon intermediate alloy, an iron-nickel intermediate alloy, electrolytic copper, a magnesium-manganese intermediate alloy, a pure zinc ingot, an aluminum-chromium intermediate alloy, an aluminum-titanium intermediate alloy, an aluminum-zirconium intermediate alloy and an aluminum ingot as raw materials, placing the weighed raw materials in a dry smelting furnace, and smelting for 5.5 hours at 915 ℃ to obtain an aluminum alloy solution. The other is the same as in the first embodiment.
And a third specific embodiment: this embodiment differs from the first or second embodiment in that: the technological parameters of the semi-continuous water-cooling casting method in the second step are as follows: the casting temperature is 760 ℃, the casting speed is 110mm/min, and the cooling water pressure is 0.32MPa. The other embodiments are the same as those of the first or second embodiment.
The specific embodiment IV is as follows: this embodiment differs from one of the first to third embodiments in that: the technical process of uniform heating integration in the third step is as follows: the aluminum alloy square ingots are vertically listed, a plurality of N-type or K-type couples are arranged between each layer for metal temperature measurement, the heating temperature is set to be 530 ℃, the set temperature is changed to be 490 ℃ when the high-point temperature of the ingots measured by the couples reaches 480 ℃, the set temperature is changed to be 475 ℃ when the low-point temperature of the ingots measured by the couples reaches 475 ℃, the temperature is kept for 19 hours, and the ingots are discharged for rolling when the temperatures of the ingots reach 475 ℃. The other is the same as in one of the first to third embodiments.
Fifth embodiment: the fourth difference between this embodiment and the third embodiment is that: and step four, rolling the cast ingot in the step three, wherein the rolling temperature is 476 ℃, the maximum processing deformation is controlled to be 40%, the plate is rolled to 81% of the thickness of the finished product, and the thickness allowance of 20% is reserved, so that the hot-rolled long plate is obtained. The other is the same as in the fourth embodiment.
Specific embodiment six: the fifth difference between this embodiment and the third embodiment is that: and fifthly, performing temperature-controlled rolling on the hot-rolled long plate obtained in the step four, performing spray cooling on the plate by using hot mill emulsion, controlling the temperature of the plate to 175 ℃, continuing rolling, finishing rolling the thickness allowance reserved in the step four, and shearing according to the multiple length number to obtain the prefabricated plate. The other is the same as in the fifth embodiment.
Seventh embodiment: the sixth embodiment differs from the first embodiment in that: step six, stretching the prefabricated plate obtained in the step five, and sawing to obtain a finished plate; the elongation parameter was 2.5%. The other is the same as in the sixth embodiment.
The invention was verified with the following test:
test one: the test is a processing method of an aviation 2A12 aluminum alloy plate, and specifically comprises the following steps:
1. according to the mass percentage of elements, si is 0.12%, fe is 0.18%, cu is 4.51%, mn is 0.63%, mg is 1.57%, ni is 0.0053%, zn is 0.068%, ti is 0.0264%, zr is 0.11%, fe+Ni is 0-0.5% and the balance is Al, respectively weighing an aluminum-silicon intermediate alloy, an iron-nickel intermediate alloy, electrolytic copper, a magnesium-manganese intermediate alloy, a pure zinc ingot, an aluminum-titanium intermediate alloy, an aluminum-zirconium intermediate alloy and an aluminum ingot as raw materials, putting the weighed raw materials into a dry smelting furnace, and smelting for 5.5 hours at 915 ℃ to obtain an aluminum alloy solution;
2. casting the aluminum alloy solution in the first step into an aluminum alloy square ingot by adopting a semi-continuous water-cooling casting method; the thickness of the aluminum alloy square ingot is 420mm, and the width is 1820mm;
the semi-continuous water-cooling casting method comprises the following technological parameters: the casting temperature is 760 ℃, the casting speed is 110mm/min, and the cooling water pressure is 0.32MPa;
3. placing the square aluminum alloy ingot obtained in the second step into a longitudinal pushing type heating furnace for uniform heating integrated treatment after surface milling and sawing to obtain an aluminum alloy ingot capable of being directly rolled:
the homogeneous heating integrated process comprises the following steps: vertically arranging aluminum alloy square ingots, arranging a plurality of N-type couples between each layer to measure metal temperature, setting the heating temperature to be 530 ℃, changing the setting temperature to be 490 ℃ when the high-point temperature of the cast ingot measured by the couples reaches 480 ℃, changing the setting temperature to be 475 ℃ when the low-point temperature of the cast ingot measured by the couples reaches 475 ℃, preserving heat for 19 hours, and discharging and rolling when the temperature of the cast ingot reaches 475 ℃;
4. rolling the cast ingot obtained in the third step, wherein the rolling temperature is 476 ℃, the maximum processing deformation is controlled to be 40%, the plate is rolled to 81% of the thickness of the finished product, and the thickness allowance of 20% is reserved, so that a hot-rolled long plate is obtained;
5. performing temperature control rolling on the hot rolled long plate obtained in the step four, performing spray cooling on the plate by using hot rolling mill emulsion, controlling the temperature of the plate to 175 ℃, continuing rolling, finishing rolling the thickness allowance reserved in the step four, and shearing according to the multiple length number to obtain a prefabricated plate;
6. stretching the prefabricated plate obtained in the fifth step, and sawing to obtain a finished plate; the elongation parameter was 2.5%.
The mechanical property data comparison is carried out on the finished products with different thicknesses obtained by the traditional ingot casting average fire and ingot casting heating process and the ingot casting average fire heating integrated process in test I:
analysis: the statistics of the performance indexes of the 2A12-H112 alloy of the conventional ingot casting average fire and ingot casting heating process under different thicknesses and the statistics of the performance indexes of the 2A12-H112 alloy of the ingot casting average fire heating integrated process of the first test and the corresponding thickness performance indexes thereof are carried out; the mechanical properties of the two are similar to the tensile strength, the yield strength and the elongation index, so that the conclusion can be drawn that the mechanical property index of the 2A12 aluminum alloy plate prepared by adopting the homogeneous heating integrated process and the conventional ingot homogeneous heating and ingot heating process is consistent, the preparation method can be achieved by only one step of process, the production time is greatly reduced, and the mechanical property of the material can be ensured.
Fig. 1 is a photograph of a metallographic structure of a 2a12-H112 alloy prepared by a conventional process of ingot homogenizing and heating, and fig. 2 is a photograph of a metallographic structure of a 2a12-H112 alloy prepared by a process of test one, and as can be seen from fig. 1 and 2, the alloy prepared by the conventional process of ingot homogenizing and heating and the ingot obtained by the process system of the invention are basically crushed and uniformly distributed, but compared with the former, the latter is crushed to a larger extent and the size is smaller; according to the corresponding relation between the material property and the compound size, the smaller the size of the compound has smaller negative influence on the board, so that the board has better performance, and the grade which can be achieved by flaw detection is higher, thus the invention has positive influence on the flaw detection grade of the board.
Claims (6)
1. The processing method of the 2A12 aluminum alloy plate for aviation is characterized by comprising the following steps of:
1. according to the mass percentage of elements, si is 0.1% -0.27%, fe is 0.15% -0.45%, cu is 4.55% -4.85%, mn is 0.5% -0.80%, mg is 1.5% -1.8%, ni is 0% -0.1%, zn is 0.08% -0.2%, ti is 0% -0.1%, zr is 0.05% -0.15%, fe+Ni is 0% -0.5% and the balance is Al, respectively weighing an aluminum-silicon intermediate alloy, an iron-nickel intermediate alloy, electrolytic copper, a magnesium-manganese intermediate alloy, a pure zinc ingot, an aluminum-titanium intermediate alloy, an aluminum-zirconium intermediate alloy and an aluminum ingot as raw materials, placing the weighed raw materials into a dry smelting furnace, and smelting for 5 h-6 h at 890 ℃ -924 ℃ to obtain an aluminum alloy solution;
2. casting the aluminum alloy solution in the first step into an aluminum alloy square ingot by adopting a semi-continuous water-cooling casting method; the thickness of the aluminum alloy square ingot is 420mm, and the width is 1820mm;
the semi-continuous water-cooling casting method comprises the following technological parameters: the casting temperature is 750-770 ℃, the casting speed is 80-120 mm/min, and the cooling water pressure is 0.25-0.38 MPa;
3. placing the square aluminum alloy ingot obtained in the second step into a longitudinal pushing type heating furnace for uniform heating integrated treatment after surface milling and sawing to obtain an aluminum alloy ingot capable of being directly rolled:
the homogeneous heating integrated process comprises the following steps: vertically arranging aluminum alloy square ingots, arranging a plurality of N-type or K-type thermocouples between each layer to perform metal temperature measurement, setting the heating temperature to be 520-550 ℃, changing the setting temperature to be 490-500 ℃ when the high-point temperature of the ingots measured by the thermocouples reaches 480+/-5 ℃, changing the setting temperature to be 475-480 ℃ when the low-point temperature of the ingots measured by the thermocouples reaches 475+/-5 ℃, preserving heat for 19-22 h, and discharging and rolling when the temperature of the ingots reaches 475-480 ℃;
4. rolling the cast ingot in the third step, wherein the rolling temperature is 470-480 ℃, the maximum processing deformation is controlled to be 32-41%, the sheet is rolled to 74-82% of the thickness of the finished product, and the thickness allowance of 18-26% is reserved, so that a hot-rolled long plate is obtained;
5. performing temperature control rolling on the hot rolled long plate obtained in the step four, performing spray cooling on the plate by using hot rolling mill emulsion, controlling the temperature of the plate to be 140-220 ℃, continuing rolling, finishing rolling the thickness allowance reserved in the step four, and shearing according to the multiple length number to obtain a prefabricated plate;
6. stretching the prefabricated plate obtained in the fifth step, and sawing to obtain a finished plate; the elongation parameters were 2.4% + -0.2.
2. The method for processing an aluminum alloy sheet 2A12 for aviation according to claim 1, wherein the semi-continuous water-cooling casting method in the second step comprises the following technological parameters: the casting temperature is 760 ℃, the casting speed is 110mm/min, and the cooling water pressure is 0.32MPa.
3. The method for processing the 2A12 aluminum alloy plate for aviation according to claim 1, wherein the homogeneous heating integrated process in the third step comprises the following steps: the aluminum alloy square ingots are vertically listed, a plurality of N-type or K-type couples are arranged between each layer for metal temperature measurement, the heating temperature is set to be 530 ℃, the set temperature is changed to be 490 ℃ when the high-point temperature of the ingots measured by the couples reaches 480 ℃, the set temperature is changed to be 475 ℃ when the low-point temperature of the ingots measured by the couples reaches 475 ℃, the temperature is kept for 19 hours, and the ingots are discharged for rolling when the temperatures of the ingots reach 475 ℃.
4. The method for processing the 2A12 aluminum alloy plate for aviation according to claim 1, wherein in the fourth step, the cast ingot in the third step is rolled at 476 ℃, the maximum processing deformation is controlled to be 40%, the plate is rolled to 81% of the thickness of the finished product, and the thickness allowance of 20% is reserved, so that the hot-rolled long plate is obtained.
5. The method for processing the 2A12 aluminum alloy plate for aviation according to claim 1, wherein in the fifth step, the hot rolled long plate obtained in the fourth step is subjected to temperature control rolling, the plate is subjected to spray cooling by using hot rolling mill emulsion, the plate temperature is controlled to 175 ℃, rolling is continued, the rolling of the thickness allowance reserved in the fourth step is completed, and shearing is carried out according to the number of times of the length, so that the prefabricated plate is obtained.
6. The method for processing the 2A12 aluminum alloy plate for aviation according to claim 1, wherein in the sixth step, the prefabricated plate obtained in the fifth step is stretched and then sawed to obtain a finished plate; the elongation parameter was 2.5%.
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