CN110042288B - Aluminum alloy U-shaped frame profile for aerospace and preparation method thereof - Google Patents
Aluminum alloy U-shaped frame profile for aerospace and preparation method thereof Download PDFInfo
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Abstract
The invention discloses an aluminum alloy U-shaped frame profile for spaceflight and a preparation method thereof, wherein the U-shaped frame profile consists of the following elements in percentage by weight: zn5.6-6.5%, Cu1.4-2.4%, Mn less than 0.1%, Mg1.8-2.6%, Cr0.2-0.25%, Fe0.25-0.35%, Si less than or equal to 0.1%, Ti less than 0.08%, and Al in balance. According to the invention, the aluminum alloy U-shaped frame section for aerospace is obtained by setting specific alloy composition and specific preparation processes such as extrusion, roll bending and the like, so that on one hand, the tensile strength and the yield strength of the U-shaped frame section are greatly improved, the final tensile strength can reach 550-609MPa, the yield strength can reach 490-546 MPa, the elongation is 7-11%, the plane gap is less than or equal to 1mm, and the verticality is less than or equal to 1 degree, which is far superior to the use standard. On the other hand, the precision of the U-shaped frame section is greatly improved, the prepared U-shaped frame section has good plane flatness, the stable consistency of the quality is ensured, the use requirements of aerospace aluminum alloy sections can be completely met, and the material guarantee is provided for the research of novel carrier rockets for aerospace in China.
Description
Technical Field
The invention belongs to the technical field of aluminum alloy section processing, and particularly relates to an aluminum alloy U-shaped frame section for spaceflight and a preparation method thereof.
Background
The carrier rocket is a guarantee for realizing rapid deployment, reconstruction, expansion and maintenance of the spacecraft, is an important carrier for large-scale development and utilization of space resources, and is also an important impetus for national economic development. At present, U-shaped frame profiles used by domestic launching frames are mainly formed by stretch bending through a mould and manual processing by personnel, and have the problems of uneven stretch bending radian, uneven manual processing area, low production efficiency and the like. In order to improve the processing efficiency, the bearing capacity, the safety and the service life of the emission frame, the U-shaped frame profile for the aluminum alloy aerospace is required to be formed at one time and has better plane flatness.
Disclosure of Invention
The invention aims to solve the technical problems in the prior art, and provides an aluminum alloy U-shaped frame section for spaceflight, which can improve the processing efficiency and precision of the U-shaped frame section by designing a specific alloy composition, has good plane flatness and can meet the specific use requirements of spaceflight.
The invention also aims to provide a preparation method of the aluminum alloy U-shaped frame profile for aerospace.
In order to achieve the purpose, the invention adopts the following technical scheme: an aluminum alloy U-shaped frame section for aerospace consists of the following elements in percentage by weight: zn5.6-6.5%, Cu1.4-2.4%, Mn less than 0.1%, Mg1.8-2.6%, Cr0.2-0.25%, Fe0.25-0.35%, Si less than or equal to 0.1%, Ti less than 0.08%, and Al in balance.
A preparation method of an aluminum alloy U-shaped frame profile for aerospace comprises the following steps:
(1) re-melted aluminum ingots, zinc ingots, magnesium ingots, electrolytic copper plates, Al-4Cr alloys and Al-10Fe alloys with the taste of more than or equal to 99.85 percent are selected as raw materials according to the element composition;
(2) melting the remelted aluminum ingot, Al-4Cr alloy and Al-10Fe alloy at the temperature of 700-760 ℃, adding a zinc ingot, a magnesium ingot and an electrolytic copper plate into the melt after melting, and stirring and melting into an alloy melt;
(3) purifying the melt by using a nitrogen-chlorine mixed gas blowing method, wherein the blowing time is 8-10 minutes, and standing for 30 minutes after slagging off;
(4) filtering the alloy melt through a foamed ceramic filter plate, and casting the alloy melt into an aluminum alloy round ingot under the process conditions of the casting temperature of 710-725 ℃, the casting speed of 70-75mm/min and the casting water pressure of 0.06-0.10MPa after filtering;
(5) heating the aluminum alloy ingot to 390-DEG C and 400 ℃ for homogenization treatment for 6 hours, then heating to 450-DEG C and 465 ℃ for homogenization treatment for 12 hours, and then cooling to below 250 ℃ along with the furnace;
(6) heating the aluminum alloy round ingot to 410-;
(7) pre-finishing the U-shaped frame section, heating to 472-477 ℃, and carrying out water quenching after keeping the temperature for 60 minutes;
(8) after quenching, finishing roll bending of the U-shaped frame profile within 96 hours;
(9) and (3) carrying out artificial aging according to batches after roll bending forming, keeping the temperature of a hearth at 140 ℃ and 160 ℃, preserving the heat for 16 hours, and carrying out aging treatment to obtain the final aerospace aluminum alloy U-shaped frame profile.
Further, the nitrogen-chlorine mixed gas in the step (3) is respectively in the proportion of N2=84%、Cl2=16%。
Further, in the step (4), the porosity of the foamed ceramic filter sheet is 50ppi, and the cast aluminum alloy round ingot is a solid round ingot.
Further, the section of the U-shaped frame profile extruded in the step (6) is L-shaped or T-shaped. Further, a 24-meter vertical quenching furnace is adopted for water quenching of the U-shaped frame profile in the step (7).
Further, the U-shaped frame profile extruded in step (8) is roll-bent by using a 40T roll bending machine, and the specific steps are as follows: after feeding, the driving wheel is advanced a certain amount to be positioned, the U-shaped frame section is subjected to oil coating and then is subjected to simmer bending, during simmer bending, the flatness, the verticality and the roundness of the U-shaped frame section are corrected by adjusting the feeding amount of the driving wheel and multiple forward bending and backward bending technologies, finally the diameter of the U-shaped frame section is 3340 and 3346mm, the gap between the outer arc and the theoretical sample plate is not more than 1.5mm, the flatness is controlled within 1.0mm, the plane gap is less than 0.3mm, and the verticality is not more than 0.8 mm.
Further, a 20T/18 meter box type aging furnace is adopted when the artificial aging is carried out in the step (9).
Compared with the prior art, the invention has the following beneficial effects:
1. according to the invention, the aluminum alloy U-shaped frame section for aerospace is obtained by setting specific alloy composition and specific preparation processes such as extrusion, roll bending and the like, so that on one hand, the tensile strength and the yield strength of the U-shaped frame section are greatly improved, the final tensile strength can reach 550-609MPa, the yield strength can reach 490-546 MPa, the elongation is 7-11%, the plane gap is less than or equal to 1mm, and the verticality is less than or equal to 1 degree, which is far superior to the use standard. On the other hand, the problems of uneven stretch bending radian, uneven manual processing area, low production efficiency and the like in the prior art are effectively solved, the precision bottleneck of the manual forming of the U-shaped frame section at present is broken through, the precision of the U-shaped frame section is greatly improved, the prepared U-shaped frame section has good plane flatness, the stable consistency of quality is ensured, the use requirements of aerospace aluminum alloy sections can be completely met, and the material guarantee is provided for the research of novel space rockets in China.
2. In the alloy composition of the aluminum alloy U-shaped frame section bar for spaceflight, Zn and Mg are main strengthening elements of the aluminum alloy section bar, and when the Zn and the Mg coexist, eta (MgZn) can be formed2) And T (Al)2Mg2Zn3) Phase ηThe solubility of the phase T and the phase T in Al is high, and the phase T are changed violently along with the temperature rise and fall, the solubility of MgZn2 at the eutectic temperature reaches 28 percent and is reduced to 4 to 5 percent at the room temperature, the effect of strengthening is very strong, the strength and the hardness of the section bar can be greatly improved by improving the content of Zn and Mg, but the plasticity, the stress corrosion resistance and the fracture toughness are reduced. Cu can reduce the potential difference between crystal and intra-crystal, change the structure of precipitated phase and refine the precipitated phase of crystal boundary, inhibit the cracking tendency along the crystal boundary and improve the stress corrosion resistance of alloy. According to the invention, through systematic research and comparison of alloy components, the relation between the strength and the corrosion resistance of the aluminum alloy U-shaped frame section can be balanced when the Zn content is 5.6-6.5%, the Mg content is 1.8-2.6% and the Cu content is 1.4-2.4%, so that the requirement of a carrier rocket on the high comprehensive performance of the aerospace U-shaped frame section is met. In addition, Mn and Cr elements generate dispersed particles during ingot casting homogenizing annealing, prevent dislocation and grain boundary migration, improve recrystallization temperature, effectively prevent crystal grain growth, refine crystal grains, ensure that the non-recrystallization or partial recrystallization state is prevented after hot working and heat treatment, improve strength and simultaneously have better stress corrosion resistance. According to the invention, through research and comparison of alloy components, the contradiction between the strength and the stress corrosion resistance of the aluminum alloy U-shaped frame profile can be effectively relieved when the Mn content is less than 0.1% and the Cr content is 0.2-0.25%.
3. According to the invention, when the aluminum alloy U-shaped frame section for aerospace is prepared, raw materials are selected according to element compositions, and then the aluminum alloy U-shaped frame section for aerospace is obtained after smelting, purification and standing, casting, homogenization treatment, ingot casting heating, extrusion, pre-finishing, quenching, roll bending and artificial aging treatment, wherein strict logic relations are provided among the steps, and specific process parameters are set in the steps. For example, (1) the homogenization treatment is performed after the completion of casting in the above-mentioned step in order to eliminate macro-and micro-segregation of the alloying elements in the ingot and to sufficiently dissolve the alloying elements and coarse compounds in a solid solution. After a large number of experiments and comparative researches, the invention discovers that the aluminum alloy ingot is heated to 390-DEG C and 400-DEG C for homogenization treatment for 6 hours, then is heated to 450-DEG C and 465-DEG C for homogenization treatment for 12 hours, and then is cooled to below 250 ℃ along with the furnace. Under the specific condition, the macro-micro segregation of Zn, Mg and Cu elements in the ingot can be completely eliminated, and the elements and coarse intermetallic compounds are fully dissolved in a solid state. The homogenization temperature is lower than the temperature condition or the gradient homogenization is not carried out or the time is less than 18 hours, the macro and micro segregation of the intragranular elements cannot be eliminated, and the intermetallic compounds cannot be crushed and refined. If the homogenization temperature exceeds the temperature condition or the homogenization time exceeds 18 hours, local overburning of the aluminum alloy ingot will occur, and the mechanical properties of the aluminum alloy profile will be deteriorated. (2) After a large number of experiments and comparative researches in the steps, the invention discovers that the aluminum alloy round ingot is extruded to the process required length by heating the aluminum alloy round ingot to 410-.
Drawings
FIG. 1 is a process flow diagram of the present invention.
Detailed Description
The present invention will be further described with reference to the following specific examples.
Example 1
An aluminum alloy U-shaped frame section for aerospace consists of the following elements in percentage by weight: zn5.6 percent, Cu2.4 percent, Mn less than 0.1 percent, Mg1.8 percent, Cr0.25 percent, Fe0.25 percent, Si less than or equal to 0.1 percent, Ti less than 0.08 percent and the balance of Al.
The preparation method of the aluminum alloy U-shaped frame section for spaceflight comprises the following steps:
(1) re-melted aluminum ingots, zinc ingots, magnesium ingots, electrolytic copper plates, Al-4Cr alloys and Al-10Fe alloys with the taste of more than or equal to 99.85 percent are selected as raw materials according to the element composition;
(2) melting the remelted aluminum ingot, Al-4Cr alloy and Al-10Fe alloy at 700 ℃ by using a resistance reverberatory furnace, adding a zinc ingot, a magnesium ingot and an electrolytic copper plate into the melt after melting, and stirring and melting into an alloy melt;
(3) melt purification is carried out by a nitrogen-chlorine mixed gas blowing method, wherein the proportion of the nitrogen-chlorine mixed gas is N2=84%、Cl2=16%, the blowing time was 8 minutesStanding for 30 minutes after slagging off;
(4) filtering the alloy melt through a foamed ceramic filter plate, wherein the porosity of the foamed ceramic filter plate is 50ppi, and casting the alloy melt into a solid aluminum alloy round ingot under the process conditions of the casting temperature of 710 ℃, the casting speed of 70mm/min and the casting water pressure of 0.06MPa after filtering;
(5) heating the aluminum alloy ingot to 390 ℃ for homogenization treatment for 6 hours, then heating to 450 ℃ for homogenization treatment for 12 hours, and then cooling to below 250 ℃ along with the furnace;
(6) heating the aluminum alloy round cast ingot to 410 ℃, extruding the aluminum alloy round cast ingot into a U-shaped frame profile at the extrusion cylinder temperature of 410 ℃ and the extrusion speed of 0.6mm/s, wherein the section of the U-shaped frame profile is L-shaped or T-shaped, and air-cooling the U-shaped frame profile to room temperature;
(7) pre-finishing the U-shaped frame section, heating to 472 ℃, preserving heat for 60 minutes, and performing water quenching by adopting a 24-meter vertical quenching furnace;
(8) after quenching, roll bending the U-shaped frame profile within 96 hours by using a 40T roll bending machine, which comprises the following specific steps: after feeding, the driving wheel is advanced a certain amount to be positioned, the U-shaped frame section is subjected to oil coating and then is subjected to simmer bending, during simmer bending, the flatness, the verticality and the roundness of the U-shaped frame section are corrected by adjusting the feeding amount of the driving wheel and multiple forward bending and backward bending technologies, finally the diameter of the U-shaped frame section is 3340 and 3346mm, the gap between the outer arc and the theoretical sample plate is not more than 1.5mm, the flatness is controlled within 1.0mm, the plane gap is less than 0.3mm, and the verticality is not more than 0.8 mm.
(9) And after roll bending forming, carrying out artificial aging by adopting a 20T/18-meter box type aging furnace according to batches, keeping the temperature of a hearth at 140 ℃, preserving the heat for 16 hours, and carrying out aging treatment to obtain the final aluminum alloy U-shaped frame profile for spaceflight.
Example 2
An aluminum alloy U-shaped frame section for aerospace consists of the following elements in percentage by weight: zn6.0%, Cu2.0%, Mn less than 0.1%, Mg2.2%, Cr0.22%, Fe0.30%, Si less than or equal to 0.1%, Ti less than 0.08%, and the balance of Al.
The preparation method of the aluminum alloy U-shaped frame section for spaceflight comprises the following steps:
(1) re-melted aluminum ingots, zinc ingots, magnesium ingots, electrolytic copper plates, Al-4Cr alloys and Al-10Fe alloys with the taste of more than or equal to 99.85 percent are selected as raw materials according to the element composition;
(2) melting the remelted aluminum ingot, Al-4Cr alloy and Al-10Fe alloy at 760 ℃ by using a resistance reverberatory furnace, adding a zinc ingot, a magnesium ingot and an electrolytic copper plate into the melt after melting, and stirring and melting into an alloy melt;
(3) melt purification is carried out by a nitrogen-chlorine mixed gas blowing method, wherein the proportion of the nitrogen-chlorine mixed gas is N2=84%、Cl2=16%, the blowing time is 10 minutes, and the mixture is kept still for 30 minutes after slag removal;
(4) filtering the alloy melt through a foamed ceramic filter plate, wherein the porosity of the foamed ceramic filter plate is 50ppi, and casting the alloy melt into a solid aluminum alloy round ingot under the process conditions of a casting temperature of 725 ℃, a casting speed of 75mm/min and a casting water pressure of 0.10MPa after filtering;
(5) heating the aluminum alloy ingot to 400 ℃ for homogenization treatment for 6 hours, then heating to 465 ℃ for homogenization treatment for 12 hours, and then cooling to below 250 ℃ along with the furnace;
(6) heating the aluminum alloy round cast ingot to 430 ℃, extruding the aluminum alloy round cast ingot into a U-shaped frame profile at the extrusion cylinder temperature of 430 ℃ and the extrusion speed of 1.2mm/s, wherein the section of the U-shaped frame profile is L-shaped or T-shaped, and air-cooling the U-shaped frame profile to room temperature;
(7) pre-finishing the U-shaped frame section, heating to 477 ℃, preserving heat for 60 minutes, and performing water quenching by adopting a 24-meter vertical quenching furnace;
(8) after quenching, roll bending the U-shaped frame profile within 96 hours by using a 40T roll bending machine, which comprises the following specific steps: after feeding, the driving wheel is advanced a certain amount to be positioned, the U-shaped frame section is subjected to oil coating and then is subjected to simmer bending, during simmer bending, the flatness, the verticality and the roundness of the U-shaped frame section are corrected by adjusting the feeding amount of the driving wheel and multiple forward bending and backward bending technologies, finally the diameter of the U-shaped frame section is 3340 and 3346mm, the gap between the outer arc and the theoretical sample plate is not more than 1.5mm, the flatness is controlled within 1.0mm, the plane gap is less than 0.3mm, and the verticality is not more than 0.8 mm.
(9) And after roll bending forming, carrying out artificial aging by adopting a 20T/18-meter box type aging furnace according to batches, keeping the temperature of a hearth at 160 ℃ for 16 hours, and carrying out aging treatment to obtain the final aluminum alloy U-shaped frame profile for spaceflight.
Example 3
An aluminum alloy U-shaped frame section for aerospace consists of the following elements in percentage by weight: zn6.5%, Cu1.4%, Mn less than 0.1%, Mg2.6%, Cr0.2%, Fe0.35%, Si less than or equal to 0.1%, Ti less than 0.08%, and the balance of Al.
The preparation method of the aluminum alloy U-shaped frame section for spaceflight comprises the following steps:
(1) re-melted aluminum ingots, zinc ingots, magnesium ingots, electrolytic copper plates, Al-4Cr alloys and Al-10Fe alloys with the taste of more than or equal to 99.85 percent are selected as raw materials according to the element composition;
(2) melting the remelted aluminum ingot, Al-4Cr alloy and Al-10Fe alloy at 730 ℃ by using a resistance reverberatory furnace, adding a zinc ingot, a magnesium ingot and an electrolytic copper plate into the melt after melting, and stirring and melting into an alloy melt;
(3) melt purification is carried out by a nitrogen-chlorine mixed gas blowing method, wherein the proportion of the nitrogen-chlorine mixed gas is N2=84%、Cl2=16%, the blowing time is 9 minutes, and the mixture is kept still for 30 minutes after slag removal;
(4) filtering the alloy melt through a foamed ceramic filter plate, wherein the porosity of the foamed ceramic filter plate is 50ppi, and casting the alloy melt into a solid aluminum alloy round ingot under the process conditions of the casting temperature of 720 ℃, the casting speed of 7mm/m < 2 > 2in and the casting water pressure of 0.08MPa after filtering;
(5) heating the aluminum alloy ingot to 395 ℃ for homogenization treatment for 6 hours, then heating to 460 ℃ for homogenization treatment for 12 hours, and then cooling to below 250 ℃ along with the furnace;
(6) heating the aluminum alloy round cast ingot to 420 ℃, extruding the aluminum alloy round cast ingot into a U-shaped frame profile at the extrusion cylinder temperature of 420 ℃ and the extrusion speed of 0.8mm/s, and air-cooling the U-shaped frame profile to room temperature, wherein the section of the U-shaped frame profile is L-shaped or T-shaped;
(7) pre-finishing the U-shaped frame section, heating to 475 ℃, preserving heat for 60 minutes, and performing water quenching by adopting a 24-meter vertical quenching furnace;
(8) after quenching, roll bending the U-shaped frame profile within 96 hours by using a 40T roll bending machine, which comprises the following specific steps: after feeding, the driving wheel is advanced a certain amount to be positioned, the U-shaped frame section is subjected to oil coating and then is subjected to simmer bending, during simmer bending, the flatness, the verticality and the roundness of the U-shaped frame section are corrected by adjusting the feeding amount of the driving wheel and multiple forward bending and backward bending technologies, finally the diameter of the U-shaped frame section is 3340 and 3346mm, the gap between the outer arc and the theoretical sample plate is not more than 1.5mm, the flatness is controlled within 1.0mm, the plane gap is less than 0.3mm, and the verticality is not more than 0.8 mm.
(9) And after roll bending forming, carrying out artificial aging by adopting a 20T/18-meter box type aging furnace according to batches, keeping the temperature of a hearth at 150 ℃ for 16 hours, and carrying out aging treatment to obtain the final aluminum alloy U-shaped frame profile for spaceflight.
The final aerospace aluminum alloy U-shaped frame profile prepared by the method is detected, and the detection result is shown in the following table.
Claims (7)
1. The utility model provides an aluminum alloy U type frame section bar for space flight which characterized in that: the material consists of the following elements in percentage by weight: zn5.6-6.5%, Cu1.4-2.4%, Mn less than 0.1%, Mg1.8-2.6%, Cr0.2-0.25%, Fe0.25-0.35%, Si less than or equal to 0.1%, Ti less than 0.08%, and Al in balance; the preparation method of the aluminum alloy U-shaped frame section for spaceflight comprises the following steps:
(1) re-melted aluminum ingots, zinc ingots, magnesium ingots, electrolytic copper plates, Al-4Cr alloys and Al-10Fe alloys with the grade of more than or equal to 99.85 percent are selected as raw materials according to the element composition;
(2) melting the remelted aluminum ingot, Al-4Cr alloy and Al-10Fe alloy at the temperature of 700-760 ℃, adding a zinc ingot, a magnesium ingot and an electrolytic copper plate into the melt after melting, and stirring and melting into an alloy melt;
(3) purifying the melt by using a nitrogen-chlorine mixed gas blowing method, wherein the blowing time is 8-10 minutes, and standing for 30 minutes after slagging off;
(4) filtering the alloy melt through a foamed ceramic filter plate, and casting the alloy melt into an aluminum alloy round ingot under the process conditions of the casting temperature of 710-725 ℃, the casting speed of 70-75mm/min and the casting water pressure of 0.06-0.10MPa after filtering;
(5) heating the aluminum alloy ingot to 390-DEG C and 400 ℃ for homogenization treatment for 6 hours, then heating to 450-DEG C and 465 ℃ for homogenization treatment for 12 hours, and then cooling to below 250 ℃ along with the furnace;
(6) heating the aluminum alloy round ingot to 410-;
(7) pre-finishing the U-shaped frame section, heating to 472-477 ℃, and carrying out water quenching after keeping the temperature for 60 minutes;
(8) after quenching, finishing roll bending of the U-shaped frame profile within 96 hours;
(9) and (3) carrying out artificial aging according to batches after roll bending forming, keeping the temperature of a hearth at 140 ℃ and 160 ℃, preserving the heat for 16 hours, and carrying out aging treatment to obtain the final aerospace aluminum alloy U-shaped frame profile.
2. An aluminum alloy U-shaped frame profile for aerospace as claimed in claim 1, wherein: the proportion of the nitrogen-chlorine mixed gas in the step (3) is N respectively2=84%、Cl2=16%。
3. An aluminum alloy U-shaped frame profile for aerospace as claimed in claim 1, wherein: and (4) the porosity of the foamed ceramic filter sheet in the step (4) is 50ppi, and the cast aluminum alloy round ingot is a solid round ingot.
4. An aluminum alloy U-shaped frame profile for aerospace as claimed in claim 1, wherein: the section of the U-shaped frame profile extruded in the step (6) is L-shaped or T-shaped.
5. An aluminum alloy U-shaped frame profile for aerospace as claimed in claim 1, wherein: and (4) in the step (7), a 24-meter vertical quenching furnace is adopted for water quenching of the U-shaped frame section.
6. An aluminum alloy U-shaped frame profile for aerospace as claimed in claim 1, wherein: and (3) roll bending the extruded U-shaped frame profile in the step (8) by using a 40T roll bending machine, and the method comprises the following specific steps: after feeding, the driving wheel is advanced a certain amount to be positioned, the U-shaped frame section is subjected to oil coating and then is subjected to simmer bending, during simmer bending, the flatness, the verticality and the roundness of the U-shaped frame section are corrected by adjusting the feeding amount of the driving wheel and multiple forward bending and backward bending technologies, finally the diameter of the U-shaped frame section is 3340 and 3346mm, the gap between the outer arc and the theoretical sample plate is not more than 1.5mm, the flatness is controlled within 1.0mm, the plane gap is less than 0.3mm, and the verticality is not more than 0.8 mm.
7. An aluminum alloy U-shaped frame profile for aerospace as claimed in claim 2, wherein: and (4) adopting a 20T/18 meter box type aging furnace when performing artificial aging in the step (9).
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4305763A (en) * | 1978-09-29 | 1981-12-15 | The Boeing Company | Method of producing an aluminum alloy product |
| EP1127952A1 (en) * | 2000-02-23 | 2001-08-29 | Société Métallurgique de Gerzat | Process for making hollow bodies for pressure containers from AlZnMgCu alloy |
| CN101760679A (en) * | 2009-12-28 | 2010-06-30 | 东北轻合金有限责任公司 | Preparation method of 7B04 aluminium alloy section |
| CN102108463A (en) * | 2010-01-29 | 2011-06-29 | 北京有色金属研究总院 | Aluminium alloy product suitable for manufacturing structures and preparation method |
| CN102978488A (en) * | 2012-12-11 | 2013-03-20 | 丛林集团有限公司 | Production technology of aluminum alloy sectional bar for automobile bumper |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1198570B (en) * | 1962-12-13 | 1965-08-12 | Fuchs Fa Otto | Process for the production of hot-hardened wrought products from aluminum alloys of the type AlZnMgCu |
| US4711762A (en) * | 1982-09-22 | 1987-12-08 | Aluminum Company Of America | Aluminum base alloys of the A1-Cu-Mg-Zn type |
| JPS60180637A (en) * | 1984-02-29 | 1985-09-14 | Kobe Steel Ltd | Manufacture of high strength al-zn-mg aluminum-alloy forging material excellent in resistance to stress-corrosion cracking |
| JP5083816B2 (en) * | 2007-11-08 | 2012-11-28 | 住友軽金属工業株式会社 | Al-Zn-Mg-Cu alloy extruded material excellent in warm workability, production method thereof, and warm worked material using the extruded material |
| CN104959393B (en) * | 2015-07-20 | 2017-03-15 | 东北轻合金有限责任公司 | A kind of manufacture method of high-quality aerial blade with aluminum alloy heat extruded barses |
| CN105525169B (en) * | 2015-12-17 | 2017-07-14 | 江西雄鹰铝业股份有限公司 | A kind of preparation method of Aluminium Alloy Extruded Bar |
| CN109890536B (en) * | 2016-10-27 | 2022-09-23 | 诺维尔里斯公司 | High strength7XXX series aluminum alloys and methods of making the same |
| CN106399881A (en) * | 2016-11-16 | 2017-02-15 | 山东南山铝业股份有限公司 | Technique for improving performances of 7075 aluminum alloy extruded material |
| CN108165848A (en) * | 2016-12-07 | 2018-06-15 | 郝金芳 | A kind of manufacturing method of aviation alloyed aluminium section bar |
| CN109576526A (en) * | 2018-12-27 | 2019-04-05 | 吉林大学 | A kind of molten internal in-situ multiphase mixes scale ceramic reinforced Al-Zn-Mg-Cu aluminium alloy and preparation method thereof |
-
2019
- 2019-05-10 CN CN201910389466.8A patent/CN110042288B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4305763A (en) * | 1978-09-29 | 1981-12-15 | The Boeing Company | Method of producing an aluminum alloy product |
| EP1127952A1 (en) * | 2000-02-23 | 2001-08-29 | Société Métallurgique de Gerzat | Process for making hollow bodies for pressure containers from AlZnMgCu alloy |
| CN101760679A (en) * | 2009-12-28 | 2010-06-30 | 东北轻合金有限责任公司 | Preparation method of 7B04 aluminium alloy section |
| CN102108463A (en) * | 2010-01-29 | 2011-06-29 | 北京有色金属研究总院 | Aluminium alloy product suitable for manufacturing structures and preparation method |
| CN102978488A (en) * | 2012-12-11 | 2013-03-20 | 丛林集团有限公司 | Production technology of aluminum alloy sectional bar for automobile bumper |
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