CN103451583B - The method producing aircraft wing stringer section bar - Google Patents
The method producing aircraft wing stringer section bar Download PDFInfo
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- CN103451583B CN103451583B CN201310415627.9A CN201310415627A CN103451583B CN 103451583 B CN103451583 B CN 103451583B CN 201310415627 A CN201310415627 A CN 201310415627A CN 103451583 B CN103451583 B CN 103451583B
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
Abstract
The present invention relates to a kind of method producing aircraft wing stringer aluminium alloy extrusions, it is characterised in that described method comprises determining that the composition of aluminium alloy, and al alloy component determined by foundation calculates the consumption of raw material；Melt and refine described raw material, to form molten aluminium alloy material；Reaction-injection moulding is carried out, to form billet in twin-jet nozzle jet shaper；And after forming described billet, in indirect extrusion machine, described billet is carried out reverse extrusion, to form aluminium alloy extrusions.The section bar that aircraft wing stringer requires is met by means of the invention it is also possible to produce with such as 7055 aluminium alloys.
Description
Technical field
The present invention relates to a kind of production method for the section bar of aircraft wing stringer, more particularly, the present invention relates to
The method producing wing stringer with the aluminium alloy of such as 7055 aluminium alloys etc.
Background technology
Wing stringer is load-bearing structure part crucial in aircraft wing, therefore, to selecting to be used for manufacturing wing stringer
Material have higher requirement, involved index to include comprehensive mechanical property, fatigue behaviour, etch resistant properties etc..
7055 aluminium alloys are the alloys that in current wrought aluminium alloy, intensity is the highest, therefore at many occasion 7055 aluminium alloys
Produce wing stringer.And to be used for producing wing stringer, then need 7055 aluminium alloy extrusions to have bigger thickness.7055 aluminium
Being mainly characterized by of alloy, intensity is high, fracture toughness is good, fatigue crack extended capability is strong, and this kind of alloy is to intercrystalline failure
Preferable resistivity is had with corrosion.
The technological process of production of the section bar being presently used for wing stringer is: first pass through casting technique to produce section bar
Ingot casting；Then, by forward extrusion technique, the section bar with regulation shape and specification is produced.
But, for 7055 aluminium alloys, owing to it has the highest intensity, therefore above-mentioned production technology is being applied
Can come into question when 7055 aluminium alloy.
First, from casting aluminium ingot technological angle for, due to 7055 alloy contents in existing high-strength aluminum alloy its
Intensity is the highest, therefore can there is the tissue defects caused by slow solidification at casting process, easily produce serious gross segregation,
Thick crystal grain and alloy phase, tearing tendency is serious.Therefore, the Foundry Production difficulty of 7055 aluminium alloys is in all of aluminium alloy
It is maximum.Further, the defect produced in casting process can affect follow-up moulding processability and mechanical property；
Secondly, for extrusion forming process angle, when forward extrusion, there are bigger between ingot casting and recipient
Frictional force, and this frictional force can cause metal flow and unhomogeneity of deformation, thus it is difficult to ensure that the consistent of product tissue
Property.Meanwhile, the detrusion when flow of metal of ingot casting top layer is fierce, easily forms bigger coarse grain ring.
At present, for domestic, not yet grasp the Composition Control of 7055 aluminium alloy extrusions, founding, profile extrusion and
The key technology of each side such as Technology for Heating Processing, the section bar produced by traditional processing technology cannot meet and is applied to aircraft wing
The demand of stringer.And in the world, the most only Alcoa can produce this kind of aluminium alloy extrusions.But, by 7055 aluminium alloys
Being difficult to the restriction cast, yield rate and the stability aspect of its product all have problems.
Therefore, in aircraft manufacturing field, need the production wing stringer of a kind of improvement, especially come with 7055 aluminium alloys
The method producing wing stringer.
Summary of the invention
The present invention makes to solve the problems referred to above of the prior art, its object is to provide a kind of production to fly
The method of machine wing stringer section bar, especially produces this section bar with 7055 aluminium alloys, and the method can reduce casting ingot blank
Homogenization operation, save production time and cost, and solve serious coarse grain ring and the mechanical property that forward extrusion process is brought
Inconsistence problems, makes the combination property of material reach the technology requirement of wing stringer.
The method producing aircraft wing stringer aluminium alloy extrusions according to the present invention comprises the steps: that a. determines that aluminium closes
The composition of gold, and according to determined by al alloy component calculate the consumption of raw material；B. fusing refinery feedstock, melted to be formed
Aluminum alloy materials；C. in twin-jet nozzle jet shaper, reaction-injection moulding is carried out, to form billet；And d. formed billet it
After, in indirect extrusion machine, billet is carried out reverse extrusion, to form aluminium alloy extrusions.
By the optimization of alloying component and employing spray deposition processing being produced the billet of aluminium alloy, make the micro-of billet
See tissue fine homogeneous, thus improve the combination property of section bar.Additionally, utilize reversal extrusion technique, material structure can be reduced
Coarse grain ring defect, improves the surface quality of section bar, and can improve the head of extrudate, the uniformity of tail mechanical property.
It is preferred that at least one during method is further comprising the steps of: e. is between step c and step d, billet is carried out
Turnery processing and pre-extrusion；F., after step d, aluminium alloy extrusions is carried out solution heat treatment and stress elimination；G. in step d
Afterwards, aluminium alloy extrusions is carried out two-stage time effect process；And h. is after step d, aluminium alloy extrusions is aligned.
In the present invention, optimized al alloy component is as follows: Si≤0.08%, Fe≤0.12%, Cu2.2～2.5%,
Mn≤0.5%, Mg1.8～2.1%, Cr≤0.4%, Zn7.8～8.2%, Ti≤0.06%, Zr0.10～0.13%, other
Impurity adds up to and is not more than 0.15%, and surplus is aluminium.
It is preferred that twin-jet nozzle jet shaper includes: settling chamber, settling chamber is provided with rotatable and liftable receipts
Storage, collector has sediment pan；And bottom pour ladle, bottom pour ladle accommodates molten aluminium alloy material, and bottom pour ladle is provided with at least one
Nozzle；Wherein, at least one nozzle sprays molten aluminium alloy material to the sediment pan of collector, and molten aluminium alloy material is in deposition
Solidify on dish, and, while injection, collector rotates and declines, thus forms billet on the sediment pan of collector.
During reverse extrusion, the recipient temperature of extruder is 380～420 DEG C, and reverse extrusion speed be 3～
5mm/ minute.
In stage of spray forming process, at least one in following parameter can be included: the injection temperation of molten aluminium alloy material
In the range of 685～710 DEG C, bottom pour ladle liquid level controls 200～540mm, and the diameter of jet hole can be 5～10mm,
The jetting height of nozzle is 350～700mm, and the rotary speed of the sediment pan of collector is 35～200rpm, the decline of collector
Speed is 10～60mm/min, and the pendulum angle of nozzle can be 4～10 °, and its hunting frequency is 2～20HZ, and is sprayed
The atomizing pressure of aluminium alloy be 0.5～1.5MPa.
It is preferred that described solution heat treatment includes: 2 hours used times, sectional material blank is risen to 400～460 DEG C from room temperature, this
Rear insulation 0.5 hour；Then, 0.5 hour used time, sectional material blank temperature is risen to 460～480 DEG C, and is incubated 1 at this temperature
Hour；Then, sectional material blank is carried out water hardening；Finally, by blank enter water before temperature control at 460～480 DEG C, quenching
Water temperature 40～45 DEG C, 0.5 hour cool time.
It is preferred that two-stage time effect process include: 1.5 hours used times, make section bar from room temperature to 110～130 DEG C, at this
At a temperature of be incubated 6 hours；Then, 1 hour used time, making section bar temperature rise to 150～170 DEG C, and insulation is 6.5 little at this temperature
Time.After insulation terminates, section bar is cooled to room temperature.
By solution heat treatment, two-stage time effect process and the optimization to prestretched, can effectively eliminate material stress, improve
The etch resistant properties of material.
Accompanying drawing explanation
Fig. 1 shows in the method producing aircraft wing stringer section bar of the present invention for forming the double of aluminium alloy billet
Nozzle jet shaper.
Fig. 2 A shows the heterogeneous microstructure of the billet that reaction-injection moulding formed.
Fig. 2 B shows the heterogeneous microstructure of the billet that casting technique formed.
Fig. 3 A and 3B respectively illustrates the schematic diagram that in two kinds of indirect extrusion machines and extrusion process thereof, billet material flows to.
Fig. 4 A is the fracture macrostructure photo of the section bar that reverse extrusion is generated.
Fig. 4 B is the fracture macrostructure photo of the section bar that forward extrusion is generated.
Detailed description of the invention
Below, the preferred embodiment of the present invention is specifically described.It should be understood that the technology people in association area
Details in disclosed embodiment can be made various equivalent transformation by member, and these equivalent transformations are wanted in the present invention equally
Within the protection domain asked.
Below, the method that the present invention produces aircraft wing stringer section bar is specifically described.
＜ raw material melting ＞
First, optimize and revise scheme according to al alloy component and calculate aluminium ingot, intermediate alloy, the consumption of metal alloys,
The smelting furnace of intermediate frequency furnace etc. such as carry out melting to raw material.Wherein, the calculating of al alloy component is based on 7055 al alloy components
Data carry out calculating.7055 al alloy components employed in the present invention are specific as follows: Si≤0.08%, and Fe≤
0.12%, Cu2.2～2.5%, Mn≤0.5%, Mg1.8～2.1%, Cr≤0.4%, Zn7.8～8.2%, Ti≤0.06%,
Zr0.10～0.13%, other impurity adds up to and is not more than 0.15%, and surplus is aluminium.Percentage herein in regard to al alloy component is
Refer to percentage by weight.
After determining the consumption of various raw material, by these melting sources, in case refinery practice afterwards.To raw material
Fusing can be carried out in intermediate frequency furnace, and smelting temperature is such as in the range of 680～750 DEG C.
After fusing is complete and before raw material is refined further, preferably the raw material of fusing can be taken
Sample is analyzed, to guarantee that the composition of aluminium alloy meets the requirements.As analysis result display al alloy component undesirable, then need into
The adjustment of row alloying component, until alloying component meets the requirements.Afterwards, molten aluminium alloy is transferred to centre from intermediate frequency furnace
Bao Zhong.Refine in tundish, degasification, slagging-off.Refining temperature in tundish is in the range of 680～750 DEG C.Permissible
Molten aluminium alloy was enabling aluminum alloy to reach before tundish transferred to by intermediate frequency furnace above-mentioned refining temperature, and in this refining temperature
Under carry out transfer operation, or also can enable aluminum alloy to reach this refining temperature after transferring to tundish.Refining time is permissible
At 5～15 minutes.Then being incubated and stand, holding temperature can be 680～730 DEG C, temperature retention time 10～30 minutes.
＜ reaction-injection moulding ＞
Aluminium alloy stock is melted, refine i.e. insulation after, prepare in jet shaper aluminium alloy (as
7055 aluminium alloys) billet.
Fig. 1 schematically shows the structure of a kind of twin-jet nozzle jet shaper.As it is shown in figure 1, twin-jet nozzle injection
Building mortion 1 has the bottom pour ladle 2 at the top being arranged on settling chamber 8, arranges in the bottom of bottom pour ladle 2 and can arrange at least one nozzle.
Being provided with inner nozzle 3 and outer nozzle 4 in the device shown in Fig. 1, they spray melted aluminium alloy in settling chamber 8.Correspond to
Inner nozzle 3 and outer nozzle 4, be respectively provided with inner nozzle scanning variable-frequency motor 5 and outer nozzle scanning variable-frequency motor 6, with to inner nozzle 3
Action with outer nozzle 4 is controlled.It is internally provided with liftable and rotatable collector 7, inner nozzle 3 in settling chamber 8
The molten aluminium alloy sprayed with outer nozzle 4 will solidify on collector 7 and form billet.
Stage of spray forming process is specific as follows: will transfer in bottom pour ladle 2 through the molten aluminium alloy of refining and insulation.Preferably
Ground, the amount of the molten aluminium alloy in bottom pour ladle 2 can be controlled by bottom pour ladle automatic Control Systems of Liquids Height (not shown).Bottom pour ladle liquid level is relatively
Good scope is 200～540mm.Then, by the inner nozzle 3 bottom bottom pour ladle 2 and outer nozzle 4, molten aluminium alloy is ejected into receipts
On the sediment pan of storage 7.The injection temperation of the molten aluminium alloy sprayed can be in the range of 685～710 DEG C.In injection
During, collector 7 rotates, and declines simultaneously, thus forms the billet of cylinder on the sediment pan of collector 7.Additionally,
During injection, inner nozzle 3 and outer nozzle 4 can be in inner nozzle scanning variable-frequency motor 5 and the causes of outer nozzle scanning variable-frequency motor 6
Swing under action, to adjust the shape of the billet formed.
Parameter in twin-jet nozzle jet shaper 1 and reaction-injection moulding operating process thereof can be optimized.Such as, spray
The diameter of mouthpiece can be 5～10mm, and the jetting height of nozzle is 350～700mm, and the rotary speed of the sediment pan of collector is
35～200rpm, the decrease speed of collector is 10～60mm/min, and the pendulum angle of nozzle can be 4～10 °, and it swings frequency
Rate is 2～20HZ, and the atomizing pressure of the aluminium alloy sprayed is 0.5～1.5MPa.Under this technological parameter, reaction-injection moulding obtains
The specification of 7055 billets is (Φ 500+30mm) × 1600mm.Above-mentioned technological parameter can enter according to desired billet specification
Row sum-equal matrix.
Compared with 7055 aluminium alloys that casting is formed, by the above-mentioned optimization to alloying component and spray deposition processing,
The heterogeneous microstructure of produced billet is more uniform.Microcosmic to the billet that two kinds of forming technologies are formed in Fig. 2 A and 2B
Metallurgical structure compares.Wherein, Fig. 2 A is illustrated that the heterogeneous microstructure of the billet that reaction-injection moulding formed, and
Fig. 2 B then shows the heterogeneous microstructure of the billet that casting technique (such as semi-continuous casting) formed.By the most visible, spray
The microscopic metallographic structure penetrating the aluminium alloy that shaping is formed is more tiny than the aluminium alloy of casting, and in equiax crystal shape, its
Mean grain size ＜ 30 μm.Such metallurgical structure is more beneficial for solving the sensitive defect with composition segregation of hot tearing, and energy
The combination properties such as the cold and hot working performance of raising material and intensity, toughness, plasticity.By inspection it will be seen that pass through injection
The combination property of the billet that forming technology is formed is beyond the requirement of US Airways material standard (AMS4336).To this in table 1
The combination property of the billet made by invention compares with the standard of AMS4336.It will be seen that the billet of the present invention is respectively
Item parameter aspect has all met or exceeded AMS4336 standard
Table 1
＜ billet turning and pre-extrusion ＞
After forming billet, in order to preferably billet be carried out reverse extrusion, alternatively, billet can carried out reversely
Before extruding, billet is carried out turnery processing.Such as, for the billet of above-mentioned a diameter of Φ 500, can be by its cylindrical
Turning is to Φ 480, and makes its surface roughness be not more than Ra12.5.
After billet is carried out turning, also the billet of turning can be heated, such as, be heated to 400～450 DEG C,
And it is incubated 2～3 hours at this temperature.Then the billet pre-extrusion of heating being become Φ 320mm, extrusion ratio is 5, and extrusion temperature is
430～460 DEG C.
<reverse extrusion>
After forming billet, by indirect extrusion machine, billet is carried out reverse extrusion, be used as wing stringer to be formed
Sectional material blank.
Fig. 3 A and 3B respectively illustrates the schematic diagram that in two kinds of indirect extrusion machines and extrusion process, billet material flows to.As
Shown in Fig. 3 A and 3B, in extrusion process, extrusion axis 20 promotes billet 10, makes billet 10 along direction of extrusion A towards extrusion die
30 advance, thus force metal to flow out from the hole of extrusion die 30 along the direction that extrusion die 30 is contrary, thus form extruded product 40.
In the present invention, the indirect extrusion machine used can be 45MN double-action reverse extruder.
In extrusion process, need billet is heated, to make it have rheological property.It is preferred that the present invention's
In reverse extrusion technique, first billet is heated to 400～460 DEG C, and insulation 2～3 hours at this temperature.Then will add then,
The billet of heat is loaded in indirect extrusion machine, and it is carried out reverse extrusion.The various parameters of extruder can be according to being produced
Specific product and concrete technological requirement and choose.Such as, in a kind of application scenario producing aircraft wing stringer
In, extruder has following technological parameter: recipient a diameter of φ 320mm, recipient temperature is 380～420 DEG C, reverse extrusion
Speed is 3～5mm/ minute.Additionally, the work strip width of extruder mold can be≤5mm.
Compared with forward extrusion, the coarse grain ring depth of defect of the section bar that reverse extrusion is formed is thick far below forward extrusion
The brilliant ring degree of depth.Fig. 4 A and 4B respectively illustrate reverse extrusion and the fracture photo of section bar that forward extrusion is generated.
Additionally, in table 2 head, the afterbody performance of the section bar that reverse extrusion and forward extrusion are generated is compared
Relatively.There it can be seen that the head of section bar that formed of reverse extrusion, tail Performance comparision are consistent, it has preferable overall performance
Uniformity.As seen from Table 2, the head of the section bar of the present invention, tail force consistency of performance > 94%, meet aircraft wing stringer
Use requirement.
Table 2
<solution heat treatment and stress elimination>
After forming the blank of aluminium alloy extrusions, preferably it can be carried out solution heat treatment and carry out stress and disappear
Remove.Its key step is as follows.
Through 2 hours, sectional material blank is risen to 400～460 DEG C from room temperature, hereafter insulation 0.5 hour.Then, used time 0.5
Hour, sectional material blank temperature is risen to 460～480 DEG C, and insulation 1 hour at this temperature.Then, sectional material blank is carried out water
Cold quenching.By blank enter water before temperature control at 460～480 DEG C, quenching water temperature 40～45 DEG C, 0.5 hour cool time.
Then, in the longitudinal direction sectional material blank is carried out the prestretched that set deformation volume is 0.5～3%, squeeze to eliminate
Produced residual stress in pressure and quenching process.This prestretched can utilize such as 2000T tension flattening machine to perform.
<two-stage time effect process>
Additionally, after processing step disclosed above, the technique of the present invention also includes section bar is carried out twin-stage
The technique of Ageing Treatment.This technical process is as follows: under the conditions of one-level aging temp (110～130 DEG C), section bar is incubated 6
Hour.Then, at two grades of actual effect temperature (150～170 DEG C), section bar is incubated 6.5 hours.Above-mentioned two-stage time effect processes
Detailed process is, 1.5 hours used times, makes section bar from room temperature to 110～130 DEG C, is incubated 6 hours at this temperature；Then,
1 hour used time, make section bar temperature rise to 150～170 DEG C, and at this temperature insulation 6.5 hours.After insulation terminates, by type
Material is cooled to room temperature.
<aligning>
Alternatively, based on the requirement to section bar actual size, after having carried out prestretched and Ageing Treatment, can be to type
Material blank is aligned.This aligning also can be carried out by above mentioned 2000T tension flattening machine.
<effect>
Through inspection, the method for the present invention chemical composition of aluminium alloy (the specially 7055 aluminium alloy) section bar produced,
The performance indications such as the compression of room temperature tensile, room temperature, electrical conductivity, anti-strip corrosion all meet AMS4436 material standard and airplane design
Requirement.Additionally, the performance data of multiple batches of sample is carried out statistical analysis, its tensile yield strength, tensile strength, compression
Yield strength, electrical conductivity meet the requirement of " with the coefficient of variation in heat less than 3%, between heat, the coefficient of variation is less than 5% ".Cause
This, the method for the present invention aluminium alloy extrusions produced meets the requirement of aircraft wing stringer.
Claims (8)
1. the method producing aircraft wing stringer aluminium alloy extrusions, it is characterised in that described method comprises the steps:
A. determine the composition of aluminium alloy, and al alloy component determined by foundation calculates the consumption of raw material；
B. melt and refine described raw material, to form molten aluminium alloy material；
C. in twin-jet nozzle jet shaper, reaction-injection moulding is carried out, to form billet；And
D., after forming described billet, in indirect extrusion machine, described billet is carried out reverse extrusion, to form aluminium alloy type
Material, wherein, the work strip width of the mould of described indirect extrusion machine is≤5mm, and, during described reverse extrusion,
The recipient temperature of described extruder is 380～420 DEG C, and reverse extrusion speed is 3～5mm/ minute.
2. the method for claim 1, it is characterised in that at least one during described method is further comprising the steps of:
E., between step c and step d, billet is carried out turnery processing and pre-extrusion；
F., after step d, described aluminium alloy extrusions is carried out solution heat treatment and stress elimination；
G., after step d, described aluminium alloy extrusions is carried out two-stage time effect process；And
H., after step d, described aluminium alloy extrusions is aligned.
3. the method for claim 1, it is characterised in that described al alloy component is as follows: Si≤0.08%, Fe≤
0.12%, Cu2.2～2.5%, Mn≤0.5%, Mg1.8～2.1%, Cr≤0.4%, Zn7.8～8.2%, Ti≤0.06%,
Zr0.10～0.13%, other impurity adds up to and is not more than 0.15%, and surplus is aluminium.
4. the method for claim 1, it is characterised in that described twin-jet nozzle jet shaper includes:
Settling chamber, is provided with rotatable and liftable collector in described settling chamber, described collector has sediment pan；And
Bottom pour ladle, described bottom pour ladle accommodates described molten aluminium alloy material, and described bottom pour ladle is provided with at least one nozzle；
Wherein, at least one nozzle described sprays described molten aluminium alloy material to the described sediment pan of described collector, described
Molten aluminium alloy material solidifies on described sediment pan, and, while injection, described collector rotates and declines, thus
The described sediment pan of described collector is formed described billet.
5. the method for claim 1, it is characterised in that at least one in step c includes following parameter: described
The injection temperation of molten aluminium alloy material is in the range of 685～710 DEG C, and bottom pour ladle liquid level controls 200～540mm, spray
A diameter of the 5 of mouthpiece～10mm, the jetting height of nozzle is 350～700mm, the rotary speed of the sediment pan of collector be 35～
200rpm, the decrease speed of collector is 10～60mm/min, and the pendulum angle of nozzle is 4～10 °, and its hunting frequency is 2
～20Hz, and the atomizing pressure of the aluminium alloy sprayed is 0.5～1.5MPa.
6. method as claimed in claim 2, it is characterised in that described two-stage time effect processes and includes: 1.5 hours used times, make type
Material, from room temperature to 110～130 DEG C, is incubated 6 hours at this temperature；Then, 1 hour used time, make section bar temperature rise to 150～
170 DEG C, and insulation 6.5 hours at this temperature.After insulation terminates, section bar is cooled to room temperature.
7. method as claimed in claim 2, it is characterised in that described solution heat treatment includes: 2 hours used times, by section bar base
Material rises to 400～460 DEG C from room temperature, hereafter insulation 0.5 hour；Then, 0.5 hour used time, sectional material blank temperature is risen to 460
～480 DEG C, and insulation 1 hour at this temperature；Then, sectional material blank is carried out water hardening；Finally, by blank enter water before
Temperature controls at 460～480 DEG C, quenching water temperature 40～45 DEG C, 0.5 hour cool time.
8. the method as according to any one of claim 1～7, it is characterised in that described aluminium alloy is 7055 aluminium alloys.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310415627.9A CN103451583B (en) | 2013-09-12 | 2013-09-12 | The method producing aircraft wing stringer section bar |
| PCT/CN2014/086114 WO2015035894A1 (en) | 2013-09-12 | 2014-09-09 | Method for producing profile for aircraft wing stringer |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310415627.9A CN103451583B (en) | 2013-09-12 | 2013-09-12 | The method producing aircraft wing stringer section bar |
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| CN103451583B true CN103451583B (en) | 2016-09-07 |
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| CN103898382B (en) * | 2014-03-27 | 2017-01-04 | 北京科技大学 | Superpower high-ductility corrosion Al Zn Mg Cu aluminum alloy materials and preparation method thereof |
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| CN106623935A (en) * | 2016-10-09 | 2017-05-10 | 湖南工业大学 | Spray deposition platform |
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| CN113862588A (en) * | 2021-09-09 | 2021-12-31 | 广东兴发铝业有限公司 | Hot processing technology for increasing strength of aluminum profile |
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| ES2565482T3 (en) * | 2011-08-17 | 2016-04-05 | Otto Fuchs Kg | Heat-resistant Al-Cu-Mg-Ag alloy, as well as a procedure for the manufacture of a semi-finished product or product from such an aluminum alloy |
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| CN101695753A (en) * | 2009-10-23 | 2010-04-21 | 江苏豪然喷射成形合金有限公司 | Method for manufacturing high-strength 7055 aluminum alloy forge piece formed by spraying |
| CN102145387A (en) * | 2011-03-24 | 2011-08-10 | 江苏豪然喷射成形合金有限公司 | Double-nozzle-scanning inclined spray type cylinder blank injection moulding device |
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