CN108754263A - A kind of high intensity space flight aluminium lithium alloy proximate matter and preparation method thereof - Google Patents
A kind of high intensity space flight aluminium lithium alloy proximate matter and preparation method thereof Download PDFInfo
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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Abstract
A kind of high intensity space flight aluminium lithium alloy proximate matter and preparation method thereof, it is related to a kind of space flight aluminium lithium alloy proximate matter and preparation method thereof.Present invention aim to address prior art production aluminium lithium alloys there are cast form difficulty is big, and the low problem of intensity of existing aluminium lithium alloy.A kind of high intensity space flight is made of with aluminium lithium alloy proximate matter Cu, Li, Ti, Zn, Ti, Mg, Zr and Al；Impurity element is Mn, Fe and Si.Preparation method：One, raw material is weighed；Two, melting obtains molten aluminium alloy；Three, plus after Al-Ti-B it refines；Four, injection forming；Five, it is cut into aluminium alloy stub；Six, blind mould squeezes to obtain extrusion billet；Seven, extrusion billet is carried out being squeezed into bar；Eight, squeezed to obtain proximate matter again, nine, proximate matter quenched；Ten, tension straingtening；11, ageing treatment obtains aluminium lithium alloy proximate matter.Present invention is mainly used for prepare high intensity space flight aluminium lithium alloy proximate matter.
Description
Technical field
The present invention relates to a kind of space flight aluminium lithium alloy proximate matters and preparation method thereof.
Background technology
With the development of aerospace industry, novel aluminium alloy constantly develops and emerges in large numbers, and aluminium lithium alloy is even more to have obtained more
More development spaces, Alcoa Inc has made the aluminium lithium alloy production line of profession, and the development of the aluminium lithium alloy in China is still very
Slowly, in order to solve the growth requirement of China's aerospace industry, a kind of aluminium lithium alloy of high intensity is now needed.
Since the elemental lithium in aluminium lithium alloy is especially active, casting process generally use vacuum drying oven, casting process needs complete
Process uses gas shield, and producing equipment is complicated, is more than that difficulty is big, and the aluminium lithium alloy quality of production of high-alloying is very unstable
It is fixed, it is difficult to meet the needs of aerospace industry.Manufactured using traditional vacuum melting mode the aluminium lithium alloy of high-alloying at
Product rate is mostly due to casting metallurgical quality and cast form difficulty is larger less than 50%, caused by waste product, and existing aluminium
The tensile strength of lithium alloy is less than 500MPa, it is specified that nonproportional cyclic straining is less than 500MPa, and elongation after fracture is only up to
6.5%, therefore prior art production aluminium lithium alloy is there are cast form difficulty is big, and the intensity of existing aluminium lithium alloy low is asked
Topic.
Invention content
Present invention aim to address prior art production aluminium lithium alloys there are cast form difficulty is big, and existing aluminium lithium closes
The low problem of intensity of gold proposes a kind of space flight aluminium lithium alloy and aluminium lithium alloy process for making profiles.
A kind of high intensity space flight is made of with aluminium lithium alloy proximate matter Cu, Li, Ti, Zn, Ti, Mg, Zr and Al；The high intensity
The mass fraction that the mass fraction of Cu is 3.7%~4.3%, Li in space flight aluminium lithium alloy proximate matter is 1.1%~1.45%, Zn
Mass fraction be 0.12%~0.25%, Mg mass fraction be 0.25%~0.8%, Zr mass fraction be 0.08%~
The mass fraction that the mass fraction that the mass fraction of 0.16%, Ag are 0.25%~0.6%, Ti is 0.08%~0.12%, B is
0.02%~0.08%, the Al of surplus, the high intensity space flight are Mn, Fe and Si with impurity element in aluminium lithium alloy proximate matter, and
Mass fraction≤0.15% of mass fraction≤0.12%, Si of mass fraction≤0.15%, Fe of Mn.
A kind of preparation method of high intensity space flight aluminium lithium alloy proximate matter, specifically carries out according to the following steps：
One, according to the matter that the mass fraction that the mass fraction of Cu is 3.7%~4.3%, Li is 1.1%~1.45%, Zn
The mass fraction that the mass fraction that amount score is 0.12%~0.25%, Mg is 0.25%~0.8%, Zr is 0.08%~
The mass fraction that the mass fraction that the mass fraction of 0.16%, Ag are 0.25%~0.6%, Ti is 0.08%~0.12%, B is
0.02%~0.08%, the Al of surplus, impurity element Mn, Fe and Si, and the quality of mass fraction≤0.15%, Fe of Mn point
Mass fraction≤0.15% of≤0.12%, Si of number weighs pure magnesium ingot, cathode plate, Al-Li intermediate alloys, the conjunction of the centres Al-Zr
Gold, Al-Zn intermediate alloys, Al-Ag intermediate alloys, high-purity aluminium ingot and Al-Ti-B；
Two, high-purity aluminium ingot that step 1 weighs is added in smelting furnace, it is molten under the conditions of temperature is 720 DEG C~740 DEG C
6h~8h is refined, aluminum melt is obtained, aluminum melt is cooled to 670 DEG C~690 DEG C, protective gas is then passed through into smelting furnace,
Step 1 is added under protective gas atmosphere and weighs pure magnesium ingot, cathode plate, Al-Li intermediate alloys, Al-Zn intermediate alloys and Al-
Ag intermediate alloys are warming up to 720 DEG C~740 DEG C, add Al-Zr intermediate alloys, are 720 DEG C~740 DEG C and protection in temperature
0.5h~1.5h is kept the temperature under gas atmosphere, obtains molten aluminium alloy；The protective gas is argon gas；
Three, in the case where temperature is 720 DEG C~740 DEG C and protective gas atmosphere into molten aluminium alloy Al-Ti-B, after 5min
Start to refine in the case where temperature is 720 DEG C~740 DEG C and protective gas atmosphere, refining time is 12min~17min；It is quiet after refining
10min~15min is set, casting melt is obtained；The protective gas is argon gas；
Four, the casting melt that step 3 obtains is subjected to injection forming, obtains injection ingot blank；
Five, the oxide skin for the injection ingot blank that removal step four obtains obtains aluminium alloy injection blank, aluminium alloy is sprayed base
Material is cut into aluminium alloy stub；The length of the aluminium alloy stub is 1000mm~1050mm；
Six, the aluminium alloy stub obtained through step 5 is placed in air-heating furnace and is heated, in aluminium alloy stub temperature
It is transferred in blind mould and is squeezed after reaching 450 DEG C~480 DEG C, obtain extrusion billet；The blind mould is the tubular of one end open
The internal diameter of mold, blind mould is identical as the outer diameter of aluminium alloy stub；
Seven, it by extrusion billet made from step 6, carries out being squeezed into bar after more mold exchange, diameter of rod is φ 200mm；
Eight, the extruded bars that step 7 obtains are sawed into the blank of 500mm long, squeezed again, proximate matter is squeezed into,
Nine, the proximate matter that step 8 obtains is placed in air hardening stove and is quenched, proximate matter after being quenched；
Ten, proximate matter after quenching that step 10 obtains is placed on tension stretcher and carries out tension straingtening, obtain tension straingtening
Proximate matter afterwards；The amount of tension of the tension straingtening is 3.5%~4.5%；
11, proximate matter carries out ageing treatment to get to aluminium lithium alloy proximate matter after the tension straingtening for obtaining step 10.
Advantage of the present invention：
1, the aluminium lithium alloy proximate matter for preparing of the present invention can be applied to aerospace industry, the present invention using spray regime carry out at
Shape, course of injection directly use gas shield, will be better than vacuum drying oven from process units and technique and cast, producing equipment letter
Single, operation difficulty is low；Casting melt is very small melt drop, cooling velocity during spray regime is formed simultaneously
Soon, the generation of the problems such as less segregation, so the quality of extruded bars can reach AAA grade of flaw detection rank, realization is high-quality
The novel aluminium lithium alloy of amount and high finished product rate is cast, and the space flight aluminium lithium alloy proximate matter of high intensity is produced using special process,
To meet the needs of aerospace processing.Its aluminium lithium alloy tensile strength is 580MPa, it is specified that nonproportional cyclic straining is 550MPa, breaks
Elongation is up to 8.0% afterwards.Solving prior art production aluminium lithium alloy, there are cast form difficulty to be closed with existing aluminium lithium greatly
The low problem of golden intensity；
2, the present invention is added Al-Ti-B before refining, and starts to refine after 5min, Al-Ti-B before refining, solution
AL-Li alloys of having determined are difficult to click and enter Al-Ti-B problems online, and ensure Al-Ti-B thinning effects, accurately control refining
Time interval and refining time are provided to ensure Al-Ti-B refinements.Addition Al-Ti-B in conventional oven is primarily to adjust
It is made into point, and the present invention is to need special process to play thinning effect to ensure.
3, the temperature of aluminum melt is reduced to after aluminum melt is formed in fusion-casting process by the present invention by 720 DEG C~740 DEG C
670 DEG C~690 DEG C, the pure magnesium ingot being added after cooling and Al-Li intermediate alloys, cooling processing can reduce pure magnesium ingot and Al-
The scaling loss of Li intermediate alloys ensure that the ingredient of alloy is accurate；
4, the present invention increases blind mould extrusion process before hot extrusion, and blind mould extruding can make ingot casting finer and close,
It ensure that the comprehensive performance and interior tissue of aluminium lithium alloy.
5, stretcher leveling is another special process of the present invention, according to conventional technological requirement, the amount of tension of proximate matter
Control does not exceed 3%, and when more than 3%, mechanical property can be deteriorated, surface will appear orange peel problem.And due to the present invention
The particularity of alloying technology is made, the control of tension force stretching amount is 3.5%~4.5%, function admirable, can reach very high strong
Degree, and keep preferable elongation after fracture.
Specific implementation mode
Specific implementation mode one：Present embodiment is a kind of high intensity space flight aluminium lithium alloy proximate matter, it by Cu, Li, Ti,
Zn, Ti, Mg, Zr and Al are formed；The mass fraction of Cu is 3.7%~4.3% in the high intensity space flight aluminium lithium alloy proximate matter,
The mass fraction that the mass fraction that the mass fraction of Li is 1.1%~1.45%, Zn is 0.12%~0.25%, Mg is 0.25%
The mass fraction of~0.8%, Zr are that the mass fraction of 0.08%~0.16%, Ag is the mass fraction of 0.25%~0.6%, Ti
Mass fraction for 0.08%~0.12%, B is 0.02%~0.08%, the Al of surplus, and the high intensity space flight is closed with aluminium lithium
Impurity element is Mn, Fe and Si in metal type material, and mass fraction≤0.12%, Si of mass fraction≤0.15%, Fe of Mn
Mass fraction≤0.15%.
Specific implementation mode two：The difference of present embodiment and specific implementation mode one is：The high intensity space flight is used
The quality that the mass fraction that the mass fraction of Cu is 3.7%~4%, Li in aluminium lithium alloy proximate matter is 1.1%~1.27%, Zn point
The mass fraction that the mass fraction that number is 0.12%~0.18%, Mg is 0.25%~0.52%, Zr is 0.08%~0.12%,
The mass fraction that the mass fraction that the mass fraction of Ag is 0.25%~0.42%, Ti is 0.08%~0.1%, B is 0.02%
~0.05%, the Al of surplus, the high intensity space flight is Mn, Fe and Si with impurity element in aluminium lithium alloy proximate matter, and the matter of Mn
Measure mass fraction≤0.12% of mass fraction≤0.10%, Si of score≤0.12%, Fe.Other and specific implementation mode one
It is identical.
Specific implementation mode three：The difference of present embodiment and specific implementation mode one is：The high intensity space flight is used
It is the quality of 1.28%~1.45%, Zn that the mass fraction of Cu, which is the mass fraction of 4%~4.3%, Li, in aluminium lithium alloy proximate matter
The mass fraction that the mass fraction that score is 0.19%~0.25%, Mg is 0.53%~0.8%, Zr is 0.12%~
The mass fraction that the mass fraction that the mass fraction of 0.16%, Ag are 0.43%~0.6%, Ti is 0.1%~0.12%, B is
0.05%~0.08%, the Al of surplus, the high intensity space flight are Mn, Fe and Si with impurity element in aluminium lithium alloy proximate matter, and
Mass fraction≤0.12% of mass fraction≤0.10%, Si of mass fraction≤0.12%, Fe of Mn.Other and specific implementation
Mode one is identical.
Specific implementation mode four：Present embodiment is a kind of preparation method of high intensity space flight aluminium lithium alloy proximate matter, tool
Body is to carry out according to the following steps：
One, according to the matter that the mass fraction that the mass fraction of Cu is 3.7%~4.3%, Li is 1.1%~1.45%, Zn
The mass fraction that the mass fraction that amount score is 0.12%~0.25%, Mg is 0.25%~0.8%, Zr is 0.08%~
The mass fraction that the mass fraction that the mass fraction of 0.16%, Ag are 0.25%~0.6%, Ti is 0.08%~0.12%, B is
0.02%~0.08%, the Al of surplus, impurity element Mn, Fe and Si, and the quality of mass fraction≤0.15%, Fe of Mn point
Mass fraction≤0.15% of≤0.12%, Si of number weighs pure magnesium ingot, cathode plate, Al-Li intermediate alloys, the conjunction of the centres Al-Zr
Gold, Al-Zn intermediate alloys, Al-Ag intermediate alloys, high-purity aluminium ingot and Al-Ti-B；
Two, high-purity aluminium ingot that step 1 weighs is added in smelting furnace, it is molten under the conditions of temperature is 720 DEG C~740 DEG C
6h~8h is refined, aluminum melt is obtained, aluminum melt is cooled to 670 DEG C~690 DEG C, protective gas is then passed through into smelting furnace,
Step 1 is added under protective gas atmosphere and weighs pure magnesium ingot, cathode plate, Al-Li intermediate alloys, Al-Zn intermediate alloys and Al-
Ag intermediate alloys are warming up to 720 DEG C~740 DEG C, add Al-Zr intermediate alloys, are 720 DEG C~740 DEG C and protection in temperature
0.5h~1.5h is kept the temperature under gas atmosphere, obtains molten aluminium alloy；The protective gas is argon gas；
Three, in the case where temperature is 720 DEG C~740 DEG C and protective gas atmosphere into molten aluminium alloy Al-Ti-B, after 5min
Start to refine in the case where temperature is 720 DEG C~740 DEG C and protective gas atmosphere, refining time is 12min~17min；It is quiet after refining
10min~15min is set, casting melt is obtained；The protective gas is argon gas；
Four, the casting melt that step 3 obtains is subjected to injection forming, obtains injection ingot blank；
Five, the oxide skin for the injection ingot blank that removal step four obtains obtains aluminium alloy injection blank, aluminium alloy is sprayed base
Material is cut into aluminium alloy stub；The length of the aluminium alloy stub is 1000mm~1050mm；
Six, the aluminium alloy stub obtained through step 5 is placed in air-heating furnace and is heated, in aluminium alloy stub temperature
It is transferred in blind mould and is squeezed after reaching 450 DEG C~480 DEG C, obtain extrusion billet；The blind mould is the tubular of one end open
The internal diameter of mold, blind mould is identical as the outer diameter of aluminium alloy stub；
Seven, it by extrusion billet made from step 6, carries out being squeezed into bar after more mold exchange, diameter of rod is φ 200mm；
Eight, the extruded bars that step 7 obtains are sawed into the blank of 500mm long, squeezed again, proximate matter is squeezed into,
Nine, the proximate matter that step 8 obtains is placed in air hardening stove and is quenched, proximate matter after being quenched；
Ten, proximate matter after quenching that step 10 obtains is placed on tension stretcher and carries out tension straingtening, obtain tension straingtening
Proximate matter afterwards；The amount of tension of the tension straingtening is 3.5%~4.5%；
11, proximate matter carries out ageing treatment to get to aluminium lithium alloy proximate matter after the tension straingtening for obtaining step 10.
Specific implementation mode five：The difference of present embodiment and specific implementation mode four is：It is sprayed described in step 4
The technological parameter of forming is as follows：Atomization temperature：720 DEG C~740 DEG C, atomization away from：550~630mm, oblique spray angle：It 27~35 °, connects
Closing quotation rotary speed：35~45rmin-1, take-up reel decrease speed：2.5~3.5mms-1；Other and specific implementation mode
Four is identical.
Specific implementation mode six：Present embodiment and the difference of one of specific implementation mode four or five are：In step 6
The parameter of the extruding：Extruding force is 400MN~500MN, and extrusion time is 15s~5min.Other and specific implementation mode four
Or five is identical.
The blind mould extrusion process of present embodiment use high temperature (450 DEG C~480 DEG C), big extruding force (400MN~
500MN), the mode that (15s~5min) is squeezed in short-term is squeezed, and is that low temperature and extruding for a long time cause nucleus abnormal in order to prevent
Change causes abnormal grain growth, the problem of so as to cause coarse-grain.It is squeezed by the blind mould of present embodiment without finding that coarse-grain is asked
Topic.
Specific implementation mode seven：The difference of present embodiment and one of specific implementation mode four to six is：In step 7
The parameter for being squeezed into bar：Extruding force is 250MN~350MN, and it is 450~460 DEG C to squeeze temperature.Other and specific implementation
Mode four to six is identical.
Specific implementation mode eight：The difference of present embodiment and one of specific implementation mode four to seven is：In step 8
The parameter squeezed again：It is 430 DEG C~450 DEG C to squeeze temperature, and extruding force is 120MN~200MN.Other with it is specific
Embodiment four to seven is identical.
Specific implementation mode nine：The difference of present embodiment and one of specific implementation mode four to eight is：In step 9
The parameter of the quenching：Hardening heat is 510 DEG C~530 DEG C, and Quenching Soaking Time is 0.5h~1.5h.Other and specific implementation
Mode four to eight is identical.
Specific implementation mode ten：The difference of present embodiment and one of specific implementation mode four to nine is：Step 11
Described in ageing treatment parameter：The temperature of ageing treatment is 145 DEG C~165 DEG C, and ageing treatment soaking time is for 24 hours~36h.
Other are identical as specific implementation mode four to nine.
The content of present invention is not limited only to the content of the respective embodiments described above, the group of one of them or several specific implementation modes
Contract sample can also realize the purpose of invention.
Using following verification experimental verifications effect of the present invention
Embodiment 1：A kind of preparation method of high intensity space flight aluminium lithium alloy proximate matter, specifically carries out according to the following steps：
One, it is 0.15% according to the mass fraction that the mass fraction that the mass fraction of Cu is 4.0%, Li is 1.2%, Zn,
The mass fraction that the mass fraction that the mass fraction that the mass fraction of Mg is 0.5%, Zr is 0.12%, Ag is 0.42%, Ti is
The mass fraction of 0.1%, B are 0.05%, the Al of surplus, impurity element Mn, Fe and Si, and the mass fraction of Mn≤
Mass fraction≤0.15% of mass fraction≤0.12%, Si of 0.15%, Fe weighs in pure magnesium ingot, cathode plate, Al-Li
Between alloy, Al-Zr intermediate alloys, Al-Zn intermediate alloys, Al-Ag intermediate alloys, high-purity aluminium ingot and Al-Ti-B；
Two, high-purity aluminium ingot that step 1 weighs is added in smelting furnace, melting 6h under the conditions of temperature is 725 DEG C is obtained
To aluminum melt, aluminum melt is cooled to 675 DEG C, protective gas is then passed through into smelting furnace, is added under protective gas atmosphere
Step 1 weighs pure magnesium ingot, cathode plate, Al-Li intermediate alloys, Al-Zn intermediate alloys and Al-Ag intermediate alloys, is warming up to
730 DEG C, Al-Zr intermediate alloys are added, 1h is kept the temperature in the case where temperature is 730 DEG C and protective gas atmosphere, obtains molten aluminium alloy；
The protective gas is argon gas；
Three, in the case where temperature is 730 DEG C and protective gas atmosphere into molten aluminium alloy Al-Ti-B, in temperature after 5min
To start to refine under 730 DEG C and protective gas atmosphere, refining time 15min；10min is stood after refining, obtains casting melt；
The protective gas is argon gas；
Four, the casting melt that step 3 obtains is subjected to injection forming, obtains injection ingot blank；The technique of the injection forming
Parameter is as follows：Atomization temperature：730 DEG C, atomization away from：600mm, oblique spray angle：30 °, receive disc spin speed：38r·min-1, receive
Disk decrease speed：3.0mm·s-1；
Five, the oxide skin for the injection ingot blank that removal step four obtains obtains aluminium alloy injection blank, aluminium alloy is sprayed base
Material is cut into aluminium alloy stub；The length of the aluminium alloy stub is 1020mm；
Six, the aluminium alloy stub obtained through step 5 is placed in air-heating furnace and is heated, in aluminium alloy stub temperature
It is transferred in blind mould and is squeezed after reaching 460 DEG C, obtain extrusion billet；The blind mould is the cylindrical die of one end open, blind
The internal diameter of mould is identical as the outer diameter of aluminium alloy stub；The parameter of the extruding：Extruding force is 450MN, extrusion time 1min；
Seven, it by extrusion billet made from step 6, carries out being squeezed into bar after more mold exchange, diameter of rod is φ 200mm；
The parameter for being squeezed into bar：Extruding force is 280MN, and it is 450 DEG C to squeeze temperature；
Eight, the extruded bars that step 7 obtains are sawed into the blank of 500mm long, squeezed again, proximate matter is squeezed into,
The parameter squeezed again：It is 440 DEG C to squeeze temperature, extruding force 150MN；
Nine, the proximate matter that step 8 obtains is placed in air hardening stove and is quenched, proximate matter after being quenched；In step 9
The parameter of the quenching：Hardening heat is 525 DEG C, Quenching Soaking Time 1h；
Ten, proximate matter after quenching that step 10 obtains is placed on tension stretcher and carries out tension straingtening, obtain tension straingtening
Proximate matter afterwards；The amount of tension of the tension straingtening is 4.2%；
11, proximate matter carries out ageing treatment to get to aluminium lithium alloy proximate matter after the tension straingtening for obtaining step 10；It is described
The parameter of ageing treatment：The temperature of ageing treatment is 160 DEG C, and ageing treatment soaking time is 36h.
For the present embodiment ingot casting using being injected into shaped cast ingot, ingot casting ignorant of the economics mould squeezes and is squeezed into the flaw detection grade after bar stock can
To reach AAA grades.The refining controlling time is cleverly designed during founding factory, increases addition Al-Ti-B in stove, solves
AL-Li alloys are difficult to click and enter Al-Ti-B problems online, have refined alloy grain.The super large extensibility of alloy is conducive to alloy
Improve intensity.Originally the product amount of tension for applying example has reached 4% or more.It is 605MPa that its final mechanical property, which is tensile strength, rule
It is 576MPa to determine nonproportional cyclic straining, and elongation after fracture is up to 9.2%.
Claims (10)
1. a kind of high intensity space flight aluminium lithium alloy proximate matter, it is characterised in that a kind of high intensity space flight with aluminium lithium alloy proximate matter by
Cu, Li, Ti, Zn, Ti, Mg, Zr and Al are formed；The high intensity space flight is with the mass fraction of Cu in aluminium lithium alloy proximate matter
The mass fraction of 3.7%~4.3%, Li are that the mass fraction of 1.1%~1.45%, Zn is the matter of 0.12%~0.25%, Mg
The mass fraction that the mass fraction that amount score is 0.25%~0.8%, Zr is 0.08%~0.16%, Ag is 0.25%~
The mass fraction that the mass fraction of 0.6%, Ti are 0.08%~0.12%, B is 0.02%~0.08%, the Al of surplus, described
High intensity space flight is Mn, Fe and Si with impurity element in aluminium lithium alloy proximate matter, and the quality of mass fraction≤0.15%, Fe of Mn
Mass fraction≤0.15% of score≤0.12%, Si.
2. a kind of high intensity space flight aluminium lithium alloy proximate matter according to claim 1, it is characterised in that the high intensity boat
It is the matter of 1.1%~1.27%, Zn that it, which is the mass fraction of 3.7%~4%, Li with the mass fraction of Cu in aluminium lithium alloy proximate matter,
The mass fraction that the mass fraction that amount score is 0.12%~0.18%, Mg is 0.25%~0.52%, Zr is 0.08%~
The mass fraction that the mass fraction that the mass fraction of 0.12%, Ag are 0.25%~0.42%, Ti is 0.08%~0.1%, B is
0.02%~0.05%, the Al of surplus, the high intensity space flight are Mn, Fe and Si with impurity element in aluminium lithium alloy proximate matter, and
Mass fraction≤0.12% of mass fraction≤0.10%, Si of mass fraction≤0.12%, Fe of Mn.
3. a kind of high intensity space flight aluminium lithium alloy proximate matter according to claim 1, it is characterised in that the high intensity boat
It is 1.28%~1.45%, Zn's with the mass fraction that the mass fraction of Cu in aluminium lithium alloy proximate matter is 4%~4.3%, Li
The mass fraction that the mass fraction that mass fraction is 0.19%~0.25%, Mg is 0.53%~0.8%, Zr is 0.12%~
The mass fraction that the mass fraction that the mass fraction of 0.16%, Ag are 0.43%~0.6%, Ti is 0.1%~0.12%, B is
0.05%~0.08%, the Al of surplus, the high intensity space flight are Mn, Fe and Si with impurity element in aluminium lithium alloy proximate matter, and
Mass fraction≤0.12% of mass fraction≤0.10%, Si of mass fraction≤0.12%, Fe of Mn.
4. a kind of preparation method of high intensity space flight aluminium lithium alloy proximate matter as described in claim 1, it is characterised in that a kind of
High intensity space flight is to carry out according to the following steps with the preparation method of aluminium lithium alloy proximate matter：
One, according to the quality that the mass fraction that the mass fraction of Cu is 3.7%~4.3%, Li is 1.1%~1.45%, Zn point
The mass fraction that the mass fraction that number is 0.12%~0.25%, Mg is 0.25%~0.8%, Zr is 0.08%~0.16%,
The mass fraction that the mass fraction that the mass fraction of Ag is 0.25%~0.6%, Ti is 0.08%~0.12%, B is 0.02%
~0.08%, the Al of surplus, impurity element Mn, Fe and Si, and the mass fraction of mass fraction≤0.15%, Fe of Mn≤
Mass fraction≤0.15% of 0.12%, Si, weigh pure magnesium ingot, cathode plate, Al-Li intermediate alloys, Al-Zr intermediate alloys,
Al-Zn intermediate alloys, Al-Ag intermediate alloys, high-purity aluminium ingot and Al-Ti-B；
Two, high-purity aluminium ingot that step 1 weighs is added in smelting furnace, melting 6h under the conditions of temperature is 720 DEG C~740 DEG C
~8h, obtains aluminum melt, and aluminum melt is cooled to 670 DEG C~690 DEG C, protective gas is then passed through into smelting furnace, is being protected
Step 1 is added under gas atmosphere to weigh in pure magnesium ingot, cathode plate, Al-Li intermediate alloys, Al-Zn intermediate alloys and Al-Ag
Between alloy, be warming up to 720 DEG C~740 DEG C, add Al-Zr intermediate alloys, temperature be 720 DEG C~740 DEG C and protective gas
0.5h~1.5h is kept the temperature under atmosphere, obtains molten aluminium alloy；The protective gas is argon gas；
Three, in the case where temperature is 720 DEG C~740 DEG C and protective gas atmosphere into molten aluminium alloy Al-Ti-B, in temperature after 5min
For degree to start to refine under 720 DEG C~740 DEG C and protective gas atmosphere, refining time is 12min~17min；It is stood after refining
10min~15min obtains casting melt；The protective gas is argon gas；
Four, the casting melt that step 3 obtains is subjected to injection forming, obtains injection ingot blank；
Five, the oxide skin for the injection ingot blank that removal step four obtains obtains aluminium alloy injection blank, and aluminium alloy injection blank is cut
At aluminium alloy stub；The length of the aluminium alloy stub is 1000mm~1050mm；
Six, the aluminium alloy stub obtained through step 5 is placed in air-heating furnace and is heated, reached in aluminium alloy stub temperature
It is transferred in blind mould and is squeezed after 450 DEG C~480 DEG C, obtain extrusion billet；The blind mould is the cylindrical die of one end open,
The internal diameter of blind mould is identical as the outer diameter of aluminium alloy stub；
Seven, it by extrusion billet made from step 6, carries out being squeezed into bar after more mold exchange, diameter of rod is φ 200mm；
Eight, the extruded bars that step 7 obtains are sawed into the blank of 500mm long, squeezed again, proximate matter is squeezed into,
Nine, the proximate matter that step 8 obtains is placed in air hardening stove and is quenched, proximate matter after being quenched；
Ten, proximate matter after quenching that step 10 obtains is placed on tension stretcher and carries out tension straingtening, obtain tension straingtening rear profile
Material；The amount of tension of the tension straingtening is 3.5%~4.5%；
11, proximate matter carries out ageing treatment to get to aluminium lithium alloy proximate matter after the tension straingtening for obtaining step 10.
5. a kind of preparation method of high intensity space flight aluminium lithium alloy proximate matter according to claim 4, it is characterised in that step
The technological parameter that forming is sprayed described in rapid four is as follows：Atomization temperature：720 DEG C~740 DEG C, atomization away from：550~630mm tiltedly sprays
Angle：27~35 °, receive disc spin speed：35~45rmin-1, take-up reel decrease speed：2.5~3.5mms-1。
6. a kind of preparation method of high intensity space flight aluminium lithium alloy proximate matter according to claim 5, it is characterised in that step
The parameter squeezed described in rapid six：Extruding force is 400MN~500MN, and extrusion time is 15s~5min.
7. a kind of preparation method of high intensity space flight aluminium lithium alloy proximate matter according to claim 4,5 or 6, feature exist
The parameter of bar is squeezed into described in step 7：Extruding force is 250MN~350MN, and it is 450~460 DEG C to squeeze temperature.
8. a kind of preparation method of high intensity space flight aluminium lithium alloy proximate matter according to claim 7, it is characterised in that step
The parameter squeezed again described in rapid eight：It is 430 DEG C~450 DEG C to squeeze temperature, and extruding force is 120MN~200MN.
9. a kind of preparation method of high intensity space flight aluminium lithium alloy proximate matter according to claim 8, it is characterised in that step
The parameter quenched described in rapid nine：Hardening heat is 510 DEG C~530 DEG C, and Quenching Soaking Time is 0.5h~1.5h.
10. a kind of preparation method of high intensity space flight aluminium lithium alloy proximate matter according to claim 9, it is characterised in that step
The parameter of ageing treatment described in rapid 11：The temperature of ageing treatment is 145 DEG C~165 DEG C, and ageing treatment soaking time is for 24 hours
~36h.
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| CN112538600A (en) * | 2020-11-10 | 2021-03-23 | 中国航发北京航空材料研究院 | Forming method of aluminum-lithium alloy complex component |
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