CN108103351A - A kind of big reaming cavity liner Cu alloy material and preparation method thereof - Google Patents
A kind of big reaming cavity liner Cu alloy material and preparation method thereof Download PDFInfo
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- CN108103351A CN108103351A CN201711398321.1A CN201711398321A CN108103351A CN 108103351 A CN108103351 A CN 108103351A CN 201711398321 A CN201711398321 A CN 201711398321A CN 108103351 A CN108103351 A CN 108103351A
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- 229910000881 Cu alloy Inorganic materials 0.000 title claims abstract description 28
- 239000000956 alloy Substances 0.000 title claims abstract description 22
- 238000002360 preparation method Methods 0.000 title claims abstract description 16
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 33
- 239000000843 powder Substances 0.000 claims abstract description 32
- 238000002844 melting Methods 0.000 claims abstract description 30
- 230000008018 melting Effects 0.000 claims abstract description 30
- 239000010949 copper Substances 0.000 claims abstract description 26
- 229910052802 copper Inorganic materials 0.000 claims abstract description 24
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 14
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 14
- 239000004411 aluminium Substances 0.000 claims abstract description 13
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 claims abstract description 10
- 238000010894 electron beam technology Methods 0.000 claims abstract description 10
- 239000002994 raw material Substances 0.000 claims abstract description 3
- 238000005242 forging Methods 0.000 claims description 60
- 238000010438 heat treatment Methods 0.000 claims description 21
- 229910002804 graphite Inorganic materials 0.000 claims description 11
- 239000010439 graphite Substances 0.000 claims description 11
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 9
- 238000001953 recrystallisation Methods 0.000 claims description 9
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 8
- 238000005266 casting Methods 0.000 claims description 8
- 239000012299 nitrogen atmosphere Substances 0.000 claims description 8
- 239000000314 lubricant Substances 0.000 claims description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 6
- 238000000265 homogenisation Methods 0.000 claims description 5
- 238000012545 processing Methods 0.000 claims description 5
- 238000001816 cooling Methods 0.000 claims description 4
- 229910052757 nitrogen Inorganic materials 0.000 claims description 4
- 238000002791 soaking Methods 0.000 claims description 4
- 238000004321 preservation Methods 0.000 claims description 3
- QQQBOMFXRYOZOM-UHFFFAOYSA-L [Mo](=S)=S.S(=O)(=O)([O-])[O-].[Ba+2] Chemical compound [Mo](=S)=S.S(=O)(=O)([O-])[O-].[Ba+2] QQQBOMFXRYOZOM-UHFFFAOYSA-L 0.000 claims description 2
- 239000011248 coating agent Substances 0.000 claims description 2
- 238000000576 coating method Methods 0.000 claims description 2
- 239000003973 paint Substances 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims 1
- 239000000155 melt Substances 0.000 claims 1
- 239000011812 mixed powder Substances 0.000 claims 1
- BPJYAXCTOHRFDQ-UHFFFAOYSA-L tetracopper;2,4,6-trioxido-1,3,5,2,4,6-trioxatriarsinane;diacetate Chemical compound [Cu+2].[Cu+2].[Cu+2].[Cu+2].CC([O-])=O.CC([O-])=O.[O-][As]1O[As]([O-])O[As]([O-])O1.[O-][As]1O[As]([O-])O[As]([O-])O1 BPJYAXCTOHRFDQ-UHFFFAOYSA-L 0.000 claims 1
- 239000000463 material Substances 0.000 abstract description 24
- 230000035515 penetration Effects 0.000 abstract description 10
- 238000005461 lubrication Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 7
- 239000000203 mixture Substances 0.000 description 7
- 239000004567 concrete Substances 0.000 description 6
- 230000000149 penetrating effect Effects 0.000 description 6
- 239000012535 impurity Substances 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 239000004615 ingredient Substances 0.000 description 4
- 229910045601 alloy Inorganic materials 0.000 description 3
- 229910052797 bismuth Inorganic materials 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 229910052745 lead Inorganic materials 0.000 description 3
- 229910052698 phosphorus Inorganic materials 0.000 description 3
- 239000002689 soil Substances 0.000 description 3
- 239000011701 zinc Substances 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 238000005474 detonation Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000005553 drilling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000004452 microanalysis Methods 0.000 description 2
- 238000010274 multidirectional forging Methods 0.000 description 2
- 239000004810 polytetrafluoroethylene Substances 0.000 description 2
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- JBQYATWDVHIOAR-UHFFFAOYSA-N tellanylidenegermanium Chemical compound [Te]=[Ge] JBQYATWDVHIOAR-UHFFFAOYSA-N 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 229910052725 zinc Inorganic materials 0.000 description 2
- 229910001257 Nb alloy Inorganic materials 0.000 description 1
- 238000003723 Smelting Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000011149 active material Substances 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000010422 painting Methods 0.000 description 1
- 238000004663 powder metallurgy Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 229910052717 sulfur Inorganic materials 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C9/00—Alloys based on copper
- C22C9/04—Alloys based on copper with zinc as the next major constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/03—Making non-ferrous alloys by melting using master alloys
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/0425—Copper-based alloys
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/08—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of copper or alloys based thereon
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Powder Metallurgy (AREA)
- Forging (AREA)
Abstract
The present invention provides a kind of big reaming cavity liner Cu alloy material and preparation method thereof, raw material is copper powder, zinc powder and aluminium powder, and melting is sintered using powder compact, and the melting is vacuum electron beam melting, vacuum degree >=2 × 10‑3Pa.Cu alloy material density prepared by the present invention is in 6~7g/cm3, and elongation percentage is higher, compared with traditional fine copper shaped charge material, keeps high Penetration Depth, its Penetration is improved in increase reaming aperture.
Description
Technical field
The present invention relates to technical field of metal material more particularly to a kind of big reaming cavity liner Cu alloy material and its systems
Preparation Method.
Background technology
In modern war, the living or death of the important military installations such as hardpoint, arm store is directly related to walking for war
To.In order to tackle this kind of hard-to-hit target, begin to develop the earth-drilling bomb of attack buried target from last century the eighties.Earth-drilling bomb
Mainly there are kinetic energy Penetrating Warhead, series connection Penetrating Warhead, wherein series connection Penetrating Warhead prime perforate is for angle of impact requirement
Not high, trajectory adaptability is preferable, and rate request is low, is the military powers such as the U.S., Britain prior development direction.
The high-speed jet (speed is up to 6000m/s) that series connection Penetrating Warhead is generated first with prime beehive-shaped charge explosion exists
The dielectric surfaces such as soil, rock, concrete destroy to form a larger-diameter hole, then make that follow-up diameter is slightly smaller second
Grade causes damage effectiveness with detonating after entering target internal along the hole that prime is outputed into warhead.Such as BROACH-1 warheads
Weight 450kg, weight of charge about 55kg, can 3.4~6.1m of penetration concrete or 6.1~9.1m soil layers, equip storm wind shadow guided missile,
Army is equipped；For another example NEB-83 penetrator bombs weight 415kg is about 1.8m, and preposition warhead loads PBX-110 high explosives,
It can penetration 2~2.5m thickness armored concrete targets.
In the development of the deep Penetrating Warhead technology of series connection, a variety of design angles and Research idea, foreign study are embodied
Mechanism has carried out numerous studies in detonation mode, charge type, shaped charge material, Types of Medicine cover structure etc., it is therefore an objective to before making
Grade beehive-shaped charge cavity liner holes aperture bigger, is to open passage with into warhead.Such as Aylslt is using numerical simulation and examination
The method being combined is tested, has studied eccentric detonation and powder charge draw ratio to eccentric sub- hemispherical Cu-Ti-Nb alloy cavity liner cumulatives
The influence of charge jet deflection；For another example USN's patent US6547993 describes a kind of Al/PTFE active material formulations and system
Technique is made, PTFE and Al powder mass ratioes are about 2.77: 1, increase reaming effect.The country is also in tracking imitation stage, research weight
Point is examined in the emulation of energy-gathering jetting cavity liner structural simulation, powder charge matching and experiment, and shaped charge material is mainly fine copper, right
In the broken relation between first jet stream cavity liner interior tissue (grain size, pattern, crystal boundary etc.), manufacturing process and shaped charge action of tradition
Make largely and in-depth study；The cavity liner material of the heterogeneous targets such as armored concrete, rock-soil layer is not destroyed for penetration
The influence of material and the matching, shaped charge material self-characteristic of prime cavity liner reaming aperture and Penetration Depth to reaming is ground
Study carefully less.Mostly using fine copper, reaming aperture mismatches Penetrating Warhead prime of connecting shaped charge material with Penetration Depth.
The content of the invention
Present invention solves the technical problem that be to provide a kind of big reaming cavity liner Cu alloy material and preparation method thereof,
Make the Cu alloy material density of preparation in 6~7g/cm3, and elongation percentage is higher, compared with traditional fine copper shaped charge material, keeps
High Penetration Depth, increase reaming aperture, improves its Penetration.
The object of the present invention is achieved like this：
A kind of big reaming cavity liner Cu alloy material and preparation method thereof, raw material is copper powder, zinc powder and aluminium powder, using powder
Last green compact is sintered melting, and the melting is vacuum electron beam melting, vacuum degree >=2 × 10-3Pa。
The vacuum electron beam melting be secondary beam melting, melting once speed (50~80) kg/h, ingot blank rotation
Casting speed (2~4) mm/min；Secondary smelting speed (80~120) kg/h, ingot blank rotation casting speed (3~6) mm/min.
Above-mentioned big reaming cavity liner Cu alloy material and preparation method thereof, further includes the multiway forging after melting, described
Multiway forging is that blank heating is carried out to multiway forging to 300~600 DEG C on 75000kN forging hammers, single forging ratio >=2.5,
Forging times 3~6 times.
Lubricant is applied in blank surface in above-mentioned multiway forging, lubricant can be with water-base nano graphite paint or molybdenum disulfide
Barium sulfate coating.
Specifically, above-mentioned big reaming cavity liner Cu alloy material and preparation method thereof, comprises the following steps：
(1) powder prepares：Using electrolytic copper powder (650~900 mesh), zinc powder (325~540 mesh), aluminium powder (200~325
Mesh)；
(2) powder and green compact are mixed：Three kinds of powder are uniformly mixed, carry out compacting blank；
(3) it is pre-sintered：Using nitrogen atmosphere protection stove, 2~4h is sintered under the conditions of 420~600 DEG C, then is cooled to the furnace
Less than 100 DEG C are come out of the stove, to obtain the preform of some strength；
(4) vacuum electron beam melting：By step (3) preform progress vacuum secondary beam melting sublimate and uniformly
Change is handled, working chamber vacuum degree >=2 × 10-3Pa；
(5) homogenization heat treatment：Blank obtained by step (4) is protected in nitrogen atmosphere protection stove under the conditions of 450~700 DEG C
Temperature 2~5h of annealing, then cool to less than 100 DEG C with the furnace and come out of the stove.
(6) multiway forging cogging：By blank heating obtained by step (5) to 300~600 DEG C, one layer of profit is applied in blank surface
Blank temperature (is heated to 150 degree, be lubricated agent smearing) by lubrication prescription, and multiway forging, single forging are carried out on 75000kN forging hammers
Ratio >=2.5 are made, forging times 3~6 times are stripped off the skin by vehicle base, and sawing prepares copper rod base；The copper rod base can be
φ (90~210) × 250mm；
(7) dynamic recrystallization treatment：Copper rod base obtained by step (6) is subjected to oil removing and removing surface, is put into nitrogen protection stove
Middle carry out dynamic recrystallization treatment, 280~520 DEG C, 60~90min of soaking time of heat treatment temperature carry out water cooling processing, to obtain
It obtains and uniformly organizes.
Copper powder, zinc powder, aluminium powder in the step (1), are business dusty material, and purity reaches 99.9%.
Certain ingredients match in the step (2), and three kinds are determined according to Metal Material Science, shaped charge material density design etc.
Proportioning components, while consider the scaling loss and volatilization loss of Zn.Copper content 65~72%, Zn content 15-25%, aluminium content 10-
15%, by percentage to the quality.
Single forging ratio >=2.5 in the step (6) refer to copper blank forging anterior and posterior height dimension ratio；Forging times 3~
It 6 times, is completed along 3 direction (X/Y/Z) forgings as 1 time, processing must be reheated by carrying out forging next time.
Advantageous effect
The present invention carries out blank preparation using powder metallurgy process first, then using vacuum electron beam melting, by more
To hammer cogging ingot blank different directions is made to obtain large plastometric set, then carry out dynamic recrystallization treatment.The present invention is containing Cu, Zn, Al
Ternary copper-alloy uniform ingredients, remove blank in part metals, nonmetallic inclusion element, effectively remove S, P, Pb, Bi, 0, H
Impurity elements are waited, degree of purity is improved, and obtains individual event alloy structure；Broken solidification strip and boundling tissue, improve the equal of tissue
Even property and consistency of performance；Obtain uniform fine grained texture；Definite shape component is obtained by follow-up preparation process, with pure copper material
The contrast experiment of component draws, under the conditions of similary penetration depth, aperture increases more than 20%.
The present invention overcomes business with impurities of materials content height, tissue odds, anisotropy seriously etc. technical barrier, together
When can according to cavity liner structure design and properties of product requirement, carry out material component design, disclosure satisfy that Diversified Products and
The requirement of different target.
(1) material purity is high.Impurity content≤0.01%.
(2) material property is stablized.Tensile strength >=350MPa, elongation >=55%.
(3) material recovery rate is high.Recovery rate reaches 88%.
(4) material grains fine microstructures.Average grain size≤25 μm.
Description of the drawings
Institutional framework before Fig. 1 copper alloy multiway forgings
Institutional framework after Fig. 2 copper alloy multiway forgings
Specific embodiment
Below in conjunction with specific embodiment, the invention will be further described.
Embodiment 1
(1) powder prepares：Using commercial electrolytic copper powder (650 mesh), zinc powder (325 mesh), aluminium powder (200 mesh), powder purity
Reach 99.9%.
(2) powder and green compact are mixed：(mass fraction, such as table 1) is matched according to certain ingredients, three kinds of powder are uniformly mixed, into
Row suppresses specification as φ 90 × 500mm blanks.
1 copper alloy powder proportioning components (wt.%) of table
| Powder title | Copper powder | Zinc powder | Aluminium powder | Remarks |
| Mass fraction | 68% | 20% | 12% |
(3) it is pre-sintered：Using nitrogen atmosphere protection stove, 2h is sintered under the conditions of 520 DEG C, then cools to 80 DEG C with the furnace and goes out
Stove obtains the preform of some strength.
(4) vacuum electron beam melting：By step (3) preform progress vacuum secondary beam melting sublimate and uniformly
Change is handled, working chamber's vacuum degree 1.5 × 10-3Pa, melting once speed 50kg/h, ingot blank rotation casting speed 2mm/min；It is secondary
Speed of melting 90kg/h, ingot blank rotation casting speed 5mm/min.
(5) homogenization heat treatment：By blank obtained by step (4), heat preservation is moved back under the conditions of 600 DEG C in nitrogen atmosphere protection stove
Fiery 3h, then cool to 80 DEG C with the furnace and come out of the stove (metallographic structure such as Fig. 1).
(6) multiway forging cogging：Blank obtained by step (5) is subjected to 4 multiway forgings.1st 520 DEG C of heating temperature,
One layer of water-base nano graphite lubrication layer is applied in blank surface, multiway forging, single forging ratio 4.5 are carried out on 75000kN forging hammers；
2nd 470 DEG C of heating temperature applies one layer of water-base nano graphite lubrication layer in blank surface, is carried out on 75000kN forging hammers multidirectional
Forging, single forging ratio 3.5；3rd 420 DEG C of heating temperature applies one layer of water-base nano graphite lubrication layer in blank surface,
Multiway forging, single forging ratio 3 are carried out on 75000kN forging hammers；380 DEG C of the 4th heating temperature, it is water base in one layer of blank surface painting
Nano-graphite lubricant layer carries out multiway forging, single forging ratio 2.5 on 75000kN forging hammers.It is stripped off the skin by vehicle base, under sawing
Material, prepares φ 100 × 300mm copper rod bases.
(7) dynamic recrystallization treatment：Copper bar material obtained by step (6) is subjected to oil removing and removing surface, is put into nitrogen protection stove
Middle carry out dynamic recrystallization treatment, 460 DEG C, soaking time 60min of heat treatment temperature carry out water cooling processing, alloy composition such as table 2
It is shown.
2 copper alloy composition (wt.%) of table
| Composition | Copper (Cu) | Zinc (Zn) | Aluminium (Al) | S, the impurity elements such as P, Pb, Bi, 0, H |
| Mass fraction | 70.3% | 18.4% | 11.3% | ≤ 0.01% |
Copper alloy blank obtained above is subjected to tissue, density, mechanics property analysis, using metallographic microanalysis method,
Average grain size 10~20 μm (Fig. 2)；It is tested using Archimedes's drainage, averag density 6.69g/cm3, density variation≤
2%；Using Mechanics Performance Testing, room temperature tensile 372~388MPa of intensity, 284~300MPa of yield strength, elongation 56~
60%, section yield 85~88%.
Using cutting working method, Cu alloy material, pure copper material prepared by the present invention are processed into dimensional accuracy, shape
The sub- hemisphere cavity liner of the identical bias of structure；Under the conditions of identical experimental evaluation, for armored concrete target, present invention system
Standby Cu alloy material eccentric sub- hemisphere cavity liner bore 90nm, average holes aperture >=60nm, than pure copper material reaming aperture
Increase 22.8%.
Embodiment 2
(1) powder prepares：Using commercial electrolytic copper powder (800 mesh), zinc powder (400 mesh), aluminium powder (270 mesh), powder purity
Reach 99.9%.
(2) powder and green compact are mixed：(mass fraction, such as table 3) is matched according to certain ingredients, three kinds of powder are uniformly mixed, into
Row suppresses specification φ 100 × 500mm blanks.
3 copper alloy powder proportioning components (wt.%) of table
| Powder title | Copper powder | Zinc powder | Aluminium powder | Remarks |
| Mass fraction | 65% | 25% | 10% |
(3) it is pre-sintered：Using nitrogen atmosphere protection stove, 2h is sintered under the conditions of 500 DEG C, then cools to 80 DEG C with the furnace and goes out
Stove, to obtain the preform of some strength.
(4) vacuum electron beam melting：By step (3) preform progress vacuum secondary beam melting sublimate and uniformly
Change is handled, working chamber's vacuum degree 1.5 × 10-3Pa, melting once speed 60kg/h, ingot blank rotation casting speed 2mm/min；It is secondary
Speed of melting 100kg/h, ingot blank rotation casting speed 5mm/min.
(5) homogenization heat treatment：By blank obtained by step (4), heat preservation is moved back under the conditions of 650 DEG C in nitrogen atmosphere protection stove
Fiery 4h, then cool to 80 DEG C with the furnace and come out of the stove (metallographic structure such as Fig. 1).
(6) multiway forging cogging：Blank obtained by step (5) is subjected to 5 multiway forgings.1st 580 DEG C of heating temperature,
One layer of water-base nano graphite lubrication layer is applied in blank surface, multiway forging, single forging ratio 4 are carried out on 75000kN forging hammers；The
2 550 DEG C of heating temperatures apply one layer of water-base nano graphite lubrication layer in blank surface, multidirectional forging are carried out on 75000kN forging hammers
It makes, single forging ratio 3.6；3rd 520 DEG C of heating temperature applies one layer of water-base nano graphite lubrication layer in blank surface,
Multiway forging, single forging ratio 3.3 are carried out on 75000kN forging hammers；490 DEG C of the 4th heating temperature applies one layer of water in blank surface
Base nano-graphite lubricant layer carries out multiway forging, single forging ratio 3 on 75000kN forging hammers；450 DEG C of the 5th heating temperature,
One layer of water-base nano graphite lubrication layer is applied in blank surface, multiway forging, single forging ratio 2.8 are carried out on 75000kN forging hammers.
It is stripped off the skin by vehicle base, sawing prepares φ 100 × 300mm copper rod bases.
(7) dynamic recrystallization treatment：Copper bar material obtained by step (6) is subjected to oil removing and removing surface, is put into nitrogen protection stove
Middle carry out dynamic recrystallization treatment, 500 DEG C, soaking time 60min of heat treatment temperature carry out water cooling processing, alloy composition such as table 4
It is shown.
4 copper alloy composition (wt.%) of table
| Composition | Copper (Cu) | Zinc (Zn) | Aluminium (A1) | S, the impurity elements such as P, Pb, Bi, 0, H |
| Mass fraction | 66.3% | 23.6% | 11.1% | ≤ 0.01% |
Copper alloy blank obtained above is subjected to tissue, density, mechanics property analysis, using metallographic microanalysis method,
15~25 μm of average grain size；It is tested using Archimedes's drainage, averag density 6.54g/cm3, density variation≤2%；
Using Mechanics Performance Testing, room temperature tensile 386~402MPa of intensity, 290~305MPa of yield strength, elongation 55~60%,
Section yield 86~89%.
Using cutting working method, Cu alloy material, pure copper material prepared by the present invention are processed into dimensional accuracy, shape
The sub- hemisphere cavity liner of the identical bias of structure；Under the conditions of identical experimental evaluation, for armored concrete target, present invention system
Standby Cu alloy material eccentric sub- hemisphere cavity liner bore 90nm, average holes aperture >=65nm, than pure copper material reaming aperture
Increase 25%.
Claims (5)
1. a kind of big reaming cavity liner Cu alloy material and preparation method thereof, raw material is copper powder, zinc powder and aluminium powder, using powder
Green compact be sintered melting, the melting be vacuum electron beam melting, vacuum degree >=2 × 10-3Pa。
2. big reaming cavity liner Cu alloy material as described in claim 1 and preparation method thereof, the vacuum electron beam melts
It refines as secondary beam melting, melting once speed（50~80）Kg/h, ingot blank rotation casting speed（2~4）mm/min；It is secondary
Speed of melting（80~120）Kg/h, ingot blank rotation casting speed（3~6）mm/min.
3. big reaming cavity liner Cu alloy material as claimed in claim 1 or 2 and preparation method thereof, after further including melting
Multiway forging, the multiway forging are that blank heating is carried out to multiway forging to 300~600 DEG C on 75000kN forging hammers, single
Secondary forging ratio >=2.5, forging times 3~6 times.
4. reaming cavity liner Cu alloy material as claimed in claim 3 big and preparation method thereof, in the multiway forging
Blank surface applies lubricant, and lubricant is water-base nano graphite paint or molybdenum disulfide barium sulfate coating.
5. big reaming cavity liner Cu alloy material as described in claim 1 and preparation method thereof, comprises the following steps：
（1）Powder prepares：Using electrolytic copper powder（650~900 mesh）, zinc powder（325~540 mesh）, aluminium powder（200~325 mesh）；
（2）Mixed powder and green compact：Three kinds of powder are uniformly mixed, carry out compacting blank；
（3）It is pre-sintered:Using nitrogen atmosphere protection stove, 2~4h is sintered under the conditions of 420~600 DEG C, then cools to 100 with the furnace
It comes out of the stove below DEG C, to obtain the preform of some strength；
（4）Vacuum electron beam melting：By step（3）Preform is carried out at vacuum secondary beam melting sublimate and homogenization
Reason, working chamber vacuum degree >=2 × 10-3Pa；
（5）Homogenization heat treatment：By step（4）Gained blank in nitrogen atmosphere protection stove move back under the conditions of 450~700 DEG C by heat preservation
2~5h of fire, then cool to less than 100 DEG C with the furnace and come out of the stove；
（6）Multiway forging cogging：By step（5）Gained blank heating applies one layer of lubricant to 300~600 DEG C, in blank surface,
Multiway forging, single forging ratio >=2.5 are carried out on 75000kN forging hammers, forging times 3~6 times are stripped off the skin by vehicle base, sawing
Copper rod base is prepared in blanking；The copper rod base can be φ（90~210）×250mm；
（7）Dynamic recrystallization treatment：By step（6）Gained copper rod base carries out oil removing and removing surface, be put into nitrogen protection stove into
Row dynamic recrystallization treatment, 280~520 DEG C, 60~90min of soaking time of heat treatment temperature carry out water cooling processing, equal to obtain
Even tissue.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111926213A (en) * | 2020-07-23 | 2020-11-13 | 广东合一纳米材料科技有限公司 | Nano copper alloy |
| CN113737011A (en) * | 2021-09-08 | 2021-12-03 | 宁波江丰电子材料股份有限公司 | Preparation method of ultra-pure copper-manganese alloy |
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| CN1954944A (en) * | 2005-08-23 | 2007-05-02 | 贝克休斯公司 | Injection shaped cover of shaped charge |
| CN102069190A (en) * | 2011-01-20 | 2011-05-25 | 中国石油集团川庆钻探工程有限公司 | Preparation method of ultra-deep penetration perforation ammunition type cover |
| CN103160701A (en) * | 2011-12-09 | 2013-06-19 | 北京有色金属研究总院 | Preparation method for high-temperature-resistant Mo-Si-B alloy |
| JP2017186653A (en) * | 2016-03-31 | 2017-10-12 | 三菱電機株式会社 | Three-dimensional shape molded article and manufacturing method therefor |
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| CN1954944A (en) * | 2005-08-23 | 2007-05-02 | 贝克休斯公司 | Injection shaped cover of shaped charge |
| CN102069190A (en) * | 2011-01-20 | 2011-05-25 | 中国石油集团川庆钻探工程有限公司 | Preparation method of ultra-deep penetration perforation ammunition type cover |
| CN103160701A (en) * | 2011-12-09 | 2013-06-19 | 北京有色金属研究总院 | Preparation method for high-temperature-resistant Mo-Si-B alloy |
| JP2017186653A (en) * | 2016-03-31 | 2017-10-12 | 三菱電機株式会社 | Three-dimensional shape molded article and manufacturing method therefor |
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| CN111926213A (en) * | 2020-07-23 | 2020-11-13 | 广东合一纳米材料科技有限公司 | Nano copper alloy |
| CN113737011A (en) * | 2021-09-08 | 2021-12-03 | 宁波江丰电子材料股份有限公司 | Preparation method of ultra-pure copper-manganese alloy |
| CN113737011B (en) * | 2021-09-08 | 2023-11-07 | 宁波江丰电子材料股份有限公司 | Preparation method of ultra-high purity copper-manganese alloy |
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