CN110318084A - For reducing the implementation method of black line material line after the oxidation of aircraft aluminum part anode - Google Patents
For reducing the implementation method of black line material line after the oxidation of aircraft aluminum part anode Download PDFInfo
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- CN110318084A CN110318084A CN201910748527.5A CN201910748527A CN110318084A CN 110318084 A CN110318084 A CN 110318084A CN 201910748527 A CN201910748527 A CN 201910748527A CN 110318084 A CN110318084 A CN 110318084A
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- aluminum part
- aircraft aluminum
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- implementation method
- black line
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- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
- C25D11/02—Anodisation
- C25D11/04—Anodisation of aluminium or alloys based thereon
- C25D11/06—Anodisation of aluminium or alloys based thereon characterised by the electrolytes used
- C25D11/08—Anodisation of aluminium or alloys based thereon characterised by the electrolytes used containing inorganic acids
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
- C25D11/02—Anodisation
- C25D11/04—Anodisation of aluminium or alloys based thereon
- C25D11/16—Pretreatment, e.g. desmutting
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
- C25D11/02—Anodisation
- C25D11/04—Anodisation of aluminium or alloys based thereon
- C25D11/18—After-treatment, e.g. pore-sealing
- C25D11/24—Chemical after-treatment
- C25D11/246—Chemical after-treatment for sealing layers
Abstract
The present invention provides a kind of implementation method of black line material line after aoxidizing for reducing aircraft aluminum part anode, comprising the following steps: step S1 configures oil removing tank liquor using degreaser, carries out oil removal treatment to aircraft aluminum part；Step S2, configuration caustic corrosion tank liquor carry out caustic corrosion processing to aircraft aluminum part, and the time of caustic corrosion processing is 5s ~ 10s；Step S3 configures light tank liquor and carries out out light processing to aircraft aluminum part；Step S4 requires and is set according to film thickness the time of the requirement control anodic oxidation of voltage under 11 DEG C ~ 13 DEG C of operation temperature, carry out anodic oxidation to aircraft aluminum part；Step S5, configures liquor of hole- sealing tank using sealer, carries out sealing pores to aircraft aluminum part.The present invention aircraft aluminum part for aero seat is optimized after anodized, enable the aircraft aluminum part significantly to reduce the bad ratio of its black line, improve product appearance, reduce waste of material probability.
Description
Technical field
The present invention relates to a kind of implementation methods of anodic oxidation, more particularly to one kind is for reducing aircraft aluminum part anode
The implementation method of black line material line after oxidation.
Background technique
7 series alloys belong to Al-Zn-Mg-Cu series high strength aluminium alloy, and there are many prominent advantages, are widely used in navigating
The components such as vacant seat chair, but since in roll forming, the process is not controlled properly or the influence of exogenous impurity, it is easy in anodic oxidation
It is bad that the material line such as black lines is formed afterwards.When being used for aero seat, it is easy along rolling direction after conventional anodization
Existing black line material line, due to the second phase Al in matrix structure there are more enrichment6(FeMnSi), Al6(FeMn), according to tradition
When anode oxidation process processing, black line material line is especially apparent；This apparent black line is bad, both influences appearance, can not be
Client is received, and will cause serious waste of material, increases production cost.
Summary of the invention
The technical problem to be solved by the present invention is to need to provide one kind to can be effectively reduced aircraft aluminum after anodic oxidation
The implementation method of the bad orders probabilities such as black line material line and material blackspot that piece surface occurs.
In this regard, the present invention provides a kind of implementation method of black line material line after aoxidizing for reducing aircraft aluminum part anode,
The following steps are included:
Step S1, configures oil removing tank liquor using degreaser, carries out oil removal treatment to aircraft aluminum part；
Step S2, configuration caustic corrosion tank liquor to aircraft aluminum part carry out caustic corrosion processing, caustic corrosion processing time be 5s ~
10s；
Step S3 configures light tank liquor and carries out out light processing to aircraft aluminum part；
Step S4 requires according to film thickness and sets the requirement control anodic oxidation of voltage under 11 DEG C ~ 13 DEG C of operation temperature
Time carries out anodic oxidation to aircraft aluminum part；
Step S5, configures liquor of hole- sealing tank using sealer, carries out sealing pores to aircraft aluminum part.
A further improvement of the present invention is that being that sodium hydroxide 40g/l ~ 60g/l matches according to concentration in the step S2
Caustic corrosion tank liquor has been set, caustic corrosion processing has been carried out to aircraft aluminum part, the operation temperature of the caustic corrosion processing is 40 DEG C ~ 60
℃。
A further improvement of the present invention is that being required according to the film thickness of 9um ~ 10um with 12V ~ 16V's in the step S4
The requirement for setting voltage, the time for controlling the anodic oxidation is 45mins ~ 65mins, carries out anodic oxygen to aircraft aluminum part
Change.
A further improvement of the present invention is that the sulfuric acid for the use of concentration being 98%, being configured to concentration is in the step S4
The anodic oxidation solution of 190g/l ~ 200g/l realizes the anodic oxidation of the aircraft aluminum part, the sun in setting voltage
The time of pole oxidation is set as 50mins ~ 60mins.
A further improvement of the present invention is that when it is described set voltage as 12V when, the anodizing time is set as 61
mins~65mins；When it is described set voltage as 13V when, the anodizing time is set as 56mins ~ 60mins；When described
When setting voltage as 14V, the anodizing time is set as 51 mins ~ 55mins；When it is described set voltage as 15V when, institute
It states anodizing time and is set as 48 mins ~ 50mins；When it is described set voltage as 16V when, anodizing time setting
For 45mins ~ 47mins.
A further improvement of the present invention is that when it is described set voltage as 12V when, the anodizing time is set as
63mins；When it is described set voltage as 13V when, the anodizing time is set as 58mins；When the voltage that sets is 14V
When, the anodizing time is set as 53mins；When it is described set voltage as 15V when, the anodizing time is set as
49mins；When it is described set voltage as 16V when, the anodizing time is set as 46mins.
A further improvement of the present invention is that being that 40g/l ~ 60g/l is configured according to degreaser concentration in the step S1
Oil removing tank liquor carries out oil removal treatment to aircraft aluminum part, and the operation temperature of the oil removal treatment is 50 DEG C ~ 70 DEG C, described to remove
The operating time of oil processing is 3mins ~ 10mins.
A further improvement of the present invention is that in the step S3, by nitric acid and photo etching out, according to the concentration of nitric acid
For 50g/l ~ 100g/l, it is described go out photo etching concentration be that 120g/l ~ 150g/l has configured light output groove liquid, to aircraft aluminum part into
Row goes out light processing, and the operation temperature of the light processing out is room temperature.
A further improvement of the present invention is that the operating time of the light processing out is 30s ~ 120s.
A further improvement of the present invention is that being configured to concentration by sealer is 8g/l ~ 10g/l in the step S5
Liquor of hole- sealing tank realize sealing pores, the operation temperatures of the sealing pores is 85 DEG C ~ 95 DEG C, when the sealing of hole of the sealing pores
Between be 10mins ~ 30mins.
Compared with prior art, the beneficial effects of the present invention are: by the aircraft aluminum part for aero seat
Anodized after optimizing enables the aircraft aluminum part significantly to reduce the bad ratio of its black line, mentions
While high product appearance, the probability of waste of material is also reduced, production cost is thereby reduced, improves the production of product
Speed and efficiency.
Detailed description of the invention
Fig. 1 is the workflow schematic diagram of an embodiment of the present invention；
Fig. 2 is to carry out anodized to aircraft aluminum part using an embodiment of the present invention and carried out using traditional handicraft
The effect contrast figure of anodized.
Specific embodiment
With reference to the accompanying drawing, preferably embodiment of the invention is described in further detail.
As shown in Figure 1, this example provides a kind of realization side of black line material line after aoxidizing for reducing aircraft aluminum part anode
Method, comprising the following steps:
Step S1, configures oil removing tank liquor using degreaser, carries out oil removal treatment to aircraft aluminum part；
Step S2, configuration caustic corrosion tank liquor to aircraft aluminum part carry out caustic corrosion processing, caustic corrosion processing time be 5s ~
10s；
Step S3 configures light tank liquor and carries out out light processing to aircraft aluminum part；
Step S4 requires according to film thickness and sets the requirement control anodic oxidation of voltage under 11 DEG C ~ 13 DEG C of operation temperature
Time carries out anodic oxidation to aircraft aluminum part；
Step S5, configures liquor of hole- sealing tank using sealer, carries out sealing pores to aircraft aluminum part.
Aircraft aluminum part described in this example is preferably used for realizing the aircraft aluminum part of aero seat, that is, is used for aero seat
The aluminum alloy part of chair；It is that 40g/l ~ 60g/l has configured oil removing tank liquor according to degreaser concentration, to aviation in the step S1
Aluminium part carries out oil removal treatment, and the operation temperature of the oil removal treatment is 50 DEG C ~ 70 DEG C, when the operation of the oil removal treatment
Between be 3mins ~ 10mins.
S1 described in this example is oil removing process, mainly uses SF-514 degreaser, is that 40g/l ~ 60g/l matches according to concentration
Oil removing tank liquor is set, concentration is that the oil removing tank liquor effect of 50g/l is more preferable, carries out oil removal treatment, operation temperature to aircraft aluminum part
Degree is 50 DEG C ~ 70 DEG C, and the time is 3mins ~ 10mins, and the purpose that can reach is the grease for removing aircraft aluminum piece surface
With the pollutants such as dust.It is washed again after the aircraft aluminum part oil removing, it is rotten subsequently into realization alkali in the step S2
Lose process.Wherein, mins is chronomere, indicates minute, can also be indicated with min.
It is that sodium hydroxide 40g/l ~ 60g/l has configured caustic corrosion tank liquor according to concentration, to boat in step S2 described in this example
Empty aluminium part carries out caustic corrosion processing, and the operation temperature of the caustic corrosion processing is 40 DEG C ~ 60 DEG C.
It is preferable to use sodium hydroxides for the processing of caustic corrosion described in this example, are sodium hydroxide 40g/l ~ 60g/l configuration according to concentration
Good caustic corrosion tank liquor, concentration are that the caustic corrosion tank liquor effect of 50g/l is more preferable, carry out caustic corrosion processing, behaviour to aircraft aluminum part
Making temperature is 40 DEG C ~ 60 DEG C, and the time is 5s ~ 10s.The purpose is to further remove the dirty of aircraft aluminum piece surface, thoroughly
Remove the natural oxide film of aircraft aluminum part.
This example is directed to the particularity of the aircraft aluminum part for reducing aero seat, is guaranteeing to remove aircraft aluminum part
Under the premise of the natural oxide film on surface, by the reaction time for shortening caustic corrosion, it is possible to reduce lye is to aircraft aluminum part
Aluminum alloy base material corrosion, when substrate surface has more second phase deposition, such as Al6(FeMnSi) and Al6(FeMn) etc.,
Be anode relative to aluminum alloy base material, preferentially corrode with caustic corrosion solution, and the elements such as Fe and Mn in sedimentary facies not with
Caustic corrosion solution reaction, the time is longer, and this non-uniform corrosion more be easy to cause aluminum alloy surface material black stripes occur.Institute
With in order to reduce black line, this example is directed to the time for shortening its caustic corrosion for reducing the aircraft aluminum part of aero seat.Alkali is rotten
It after erosion, is washed, enters back into step S3 and realize out light process.
It is 50g/l ~ 100g/l, institute according to the concentration of nitric acid by nitric acid and photo etching out in step S3 described in this example
Stating out photo etching concentration is that 120g/l ~ 150g/l has configured light output groove liquid, carries out out light processing, the light out to aircraft aluminum part
The operation temperature of processing is room temperature, and the operating time of the light processing out is 30s ~ 120s.
Step S3 described in this example for realizing light process out, it is preferable to use be nitric acid and photo etching B-516 out, according to nitric acid
Concentration be 50g/l ~ 100g/l, out photo etching B-516 concentration be 120g/l ~ 150g/l configured tank liquor, to aircraft aluminum part into
Row goes out light processing, and operation temperature is room temperature, and the time is 30s ~ 120s.The purpose that light process is provided in this example is after removing caustic corrosion
The dust of generation, further activates aluminium surface.Out after light, washed, enter back into three step S4 anodic oxidation process.By
If being not usually required to carry out chemical polishing in the lackluster requirement of aircraft aluminum part for reducing aero seat, because
Chemical polishing and a kind of sour corrosion, this corrosion are also easy to appear material black line line.
In step S4 described in this example, the requirement with the setting voltage of 12V ~ 16V, control are required according to the film thickness of 9um ~ 10um
The time of the anodic oxidation is 45mins ~ 65mins, carries out anodic oxidation to aircraft aluminum part；It is excellent in the step S4
The sulfuric acid that choosing is 98% using concentration is configured to the anodic oxidation solution that concentration is 190g/l ~ 200g/l, real in setting voltage
The anodic oxidation of the existing aircraft aluminum part, the time of the anodic oxidation is set as 50mins ~ 60mins, at this point, with institute
After stating oil removal treatment, caustic corrosion processing and anodic oxidation collocation, for the aircraft aluminum part for reducing aero seat
Anodic oxidation effect is especially good, the effect of anodic oxidation be technical staff institute it is not expected that.
It is noted that requirement of this example also according to film thickness, controls the time, under normal circumstances, according to MIL-A-
8625 military standard requirement, this example preferably control the anodic oxidation film thickness of the aircraft aluminum part in 10um or so,
Voltage is set as 12V ~ 16V, and anodizing time is set within the scope of 50mins ~ 60mins.When the voltage that sets is 12V
When, the anodizing time is set as 61 mins ~ 65mins；When it is described set voltage as 13V when, when the anodic oxidation
Between be set as 56mins ~ 60mins；When it is described set voltage as 14V when, the anodizing time be set as 51 mins ~
55mins；When it is described set voltage as 15V when, the anodizing time is set as 48 mins ~ 50mins；When the setting
When voltage is 16V, the anodizing time is set as 45mins ~ 47mins.
More preferably, this example when it is described set voltage as 12V when, the anodizing time is set as 63mins；When
Described when setting voltage as 13V, the anodizing time is set as 58mins；When it is described set voltage as 14V when, the sun
Pole oxidization time is set as 53mins；When it is described set voltage as 15V when, the anodizing time is set as 49mins；When
Described when setting voltage as 16V, the anodizing time is set as 46mins, and effect at this time will become apparent from.
This example integrates further preferably by being maintained at the anodic oxidation of 11 DEG C ~ 13 DEG C of low-temperature operation temperature, can
To be substantially reduced the bad ratio of material black line of aircraft aluminum part.It is well known that in anode oxidation process, part electric energy meeting
It is converted to thermal energy, is an exothermic reaction, temperature is higher, and reaction speed is faster, while higher temperature will cause the oxygen of generation
Change film to dissolve faster.The aerolite of aircraft aluminum part rolls or the center portion of extrded material, especially material, is easy richness
Collect the second phase, such as Si of the element in some alloying components, or film formation reaction is not involved in for main second phase with Si etc., also not
It can be oxidized anodically tank liquor dissolution, the other impurity elements concentrated in center portion then participate in film forming with complicated film formation reaction, and
This example reduces the temperature of its anodic oxidation for aircraft aluminum part, and controlling is 11 DEG C ~ 13 DEG C, can slow down anode oxidation groove liquid pair
The dissolution of the oxidation film of generation reduces the impurity element for not forming a film or being difficult to form a film because that cannot be oxidized anodically tank liquor dissolution due to heap
Product, to apparent material black line or blackspot occur.After anodic oxidation, washed.It does not need such as to carry out dyeing processing, then water
The sealing of hole process of the step S5 is directly entered after washing.
In step S5 described in this example, the liquor of hole- sealing tank that concentration is 8g/l ~ 10g/l is configured to by sealer and is realized at sealing of hole
Reason, the operation temperature of the sealing pores are 85 DEG C ~ 95 DEG C, and the sealing of hole time of the sealing pores is 10mins ~ 30mins.
Step S5 sealing of hole described in this example mainly uses SF-558 sealer, is configured to the slot that concentration is 8g/l ~ 10g/l
Liquid.Operation temperature is 90 DEG C ± 5 DEG C, and this example controls the sealing of hole time in 20mins ± 10mins according to above-mentioned thicknesses of layers.Sealing of hole
Purpose be reduce anode oxide film porosity and adsorption capacity, improve the corrosion resistance and stain resistance energy of anode oxide film
Power.It after sealing of hole, is washed, then after moisture is dried, the good aircraft aluminum part of anodic oxidation carries out lower extension.
In order to test the effect of this example, as shown in Fig. 2, this example will also realize the sun of aircraft aluminum part using traditional handicraft
Pole oxidation effectiveness 1 and use the application realize that the anodic oxidation effect 2 of aircraft aluminum part has carried out comparative test；It is left in Fig. 2
After side uses the aircraft aluminum part after traditional handicraft anodic oxidation to have apparent material black line, the right to use this example anodic oxidation
Aircraft aluminum part without apparent material black line, contrast effect is obviously.
Meanwhile this example, according further to military standard MIL-A-8625, the requirement of Type II carries out test comparison, such as following table institute
Show.
| Strip materials | Specimen size | Test item | Traditional handicraft | This technique | MIL-A-8625, Type II test request |
| 7075-T651 | 3*10*0.032(inch) | Salt spray test | Corrosion-free point | Corrosion-free point | After salt spray test, the corrosion-free point in surface |
| 7075-T651 | 3*3*0.032(inch) | Film resurveys examination | 1681.87 mg/ft2 | 1967.73 mg/ft2 | ≧1000mg/ft2 |
From the test result of upper table it is found that this example is according to military standard MIL-A-8625, the requirement of Type II is surveyed
It is also to comply fully with requirement that examination, salt spray test and film, which resurvey examination,.
To sum up, this example is made by the anodized after optimizing to the aircraft aluminum part for aero seat
The bad ratio of its black line can significantly be reduced by obtaining the aircraft aluminum part, while improving product appearance, be also reduced
The probability of waste of material, thereby reduces production cost, improves the speed of production and efficiency of product.
The above content is a further detailed description of the present invention in conjunction with specific preferred embodiments, and it cannot be said that
Specific implementation of the invention is only limited to these instructions.For those of ordinary skill in the art to which the present invention belongs, exist
Under the premise of not departing from present inventive concept, a number of simple deductions or replacements can also be made, all shall be regarded as belonging to of the invention
Protection scope.
Claims (10)
1. it is a kind of for reducing aircraft aluminum part anode oxidation after black line material line implementation method, which is characterized in that including with
Lower step:
Step S1, configures oil removing tank liquor using degreaser, carries out oil removal treatment to aircraft aluminum part；
Step S2, configuration caustic corrosion tank liquor to aircraft aluminum part carry out caustic corrosion processing, caustic corrosion processing time be 5s ~
10s；
Step S3 configures light tank liquor and carries out out light processing to aircraft aluminum part；
Step S4 requires according to film thickness and sets the requirement control anodic oxidation of voltage under 11 DEG C ~ 13 DEG C of operation temperature
Time carries out anodic oxidation to aircraft aluminum part；
Step S5, configures liquor of hole- sealing tank using sealer, carries out sealing pores to aircraft aluminum part.
2. the implementation method of black line material line after the oxidation according to claim 1 for reducing aircraft aluminum part anode,
It is characterized in that, is that sodium hydroxide 40g/l ~ 60g/l has configured caustic corrosion tank liquor according to concentration, to aviation aluminium in the step S2
Material part carries out caustic corrosion processing, and the operation temperature of the caustic corrosion processing is 40 DEG C ~ 60 DEG C.
3. the implementation method of black line material line after the oxidation according to claim 1 for reducing aircraft aluminum part anode,
It is characterized in that, in the step S4, is required to control institute with the requirement of the setting voltage of 12V ~ 16V according to the film thickness of 9um ~ 10um
The time for stating anodic oxidation is 45mins ~ 65mins, carries out anodic oxidation to aircraft aluminum part.
4. the implementation method of black line material line after the oxidation according to claim 1 for reducing aircraft aluminum part anode,
It is characterized in that, in the step S4, the sulfuric acid for the use of concentration being 98% is configured to the anodic oxidation that concentration is 190g/l ~ 200g/l
Solution realizes the anodic oxidation of the aircraft aluminum part in setting voltage, and the time of the anodic oxidation is set as
50mins~60mins。
5. the implementation method of black line material line after the oxidation according to claim 3 for reducing aircraft aluminum part anode,
Be characterized in that, when it is described set voltage as 12V when, the anodizing time is set as 61 mins ~ 65mins；It is set when described
When constant voltage is 13V, the anodizing time is set as 56mins ~ 60mins；When it is described set voltage as 14V when, it is described
Anodizing time is set as 51 mins ~ 55mins；When it is described set voltage as 15V when, the anodizing time is set as
48 mins~50mins；When it is described set voltage as 16V when, the anodizing time is set as 45mins ~ 47mins.
6. the implementation method of black line material line after the oxidation according to claim 5 for reducing aircraft aluminum part anode,
Be characterized in that, when it is described set voltage as 12V when, the anodizing time is set as 63mins；When it is described set voltage as
When 13V, the anodizing time is set as 58mins；When it is described set voltage as 14V when, anodizing time setting
For 53mins；When it is described set voltage as 15V when, the anodizing time is set as 49mins；When it is described set voltage as
When 16V, the anodizing time is set as 46mins.
7. the black line material line to after being aoxidized described in 6 any one for reducing aircraft aluminum part anode according to claim 1
Implementation method, which is characterized in that it is that 40g/l ~ 60g/l has configured oil removing tank liquor according to degreaser concentration in the step S1, it is right
Aircraft aluminum part carries out oil removal treatment, and the operation temperature of the oil removal treatment is 50 DEG C ~ 70 DEG C, the behaviour of the oil removal treatment
Making the time is 3mins ~ 10mins.
8. the black line material line to after being aoxidized described in 6 any one for reducing aircraft aluminum part anode according to claim 1
Implementation method, which is characterized in that in the step S3, by nitric acid and photo etching out, according to the concentration of nitric acid be 50g/l ~
100g/l, the photo etching concentration out are that 120g/l ~ 150g/l has configured light output groove liquid, are carried out out at light to aircraft aluminum part
The operation temperature of reason, the light processing out is room temperature.
9. the implementation method of black line material line after the oxidation according to claim 8 for reducing aircraft aluminum part anode,
It is characterized in that, the operating time of the light processing out is 30s ~ 120s.
10. the black line material line to after being aoxidized described in 6 any one for reducing aircraft aluminum part anode according to claim 1
Implementation method, which is characterized in that in the step S5, it is real that the liquor of hole- sealing tank that concentration is 8g/l ~ 10g/l is configured to by sealer
Existing sealing pores, the operation temperature of the sealing pores are 85 DEG C ~ 95 DEG C, the sealing of hole time of the sealing pores be 10mins ~
30mins。
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Cited By (1)
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|---|---|---|---|---|
| CN112695360A (en) * | 2020-12-11 | 2021-04-23 | 苏州龙宇精密机械有限公司 | Surface treatment method for precision parts of aviation seat |
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| CN104032345A (en) * | 2014-06-04 | 2014-09-10 | 张家港市金邦铝业有限公司 | Anodic oxidation device of piping aluminum alloy profile and oxidization process thereof |
| CN104762538A (en) * | 2015-04-09 | 2015-07-08 | 广东欧珀移动通信有限公司 | Aluminum alloy and anodic oxidation method thereof |
| CN107142400A (en) * | 2017-06-02 | 2017-09-08 | 东莞宜安科技股份有限公司 | A kind of anode oxidation method of pack alloy |
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2019
- 2019-08-14 CN CN201910748527.5A patent/CN110318084B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104032345A (en) * | 2014-06-04 | 2014-09-10 | 张家港市金邦铝业有限公司 | Anodic oxidation device of piping aluminum alloy profile and oxidization process thereof |
| CN104762538A (en) * | 2015-04-09 | 2015-07-08 | 广东欧珀移动通信有限公司 | Aluminum alloy and anodic oxidation method thereof |
| CN107142400A (en) * | 2017-06-02 | 2017-09-08 | 东莞宜安科技股份有限公司 | A kind of anode oxidation method of pack alloy |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112695360A (en) * | 2020-12-11 | 2021-04-23 | 苏州龙宇精密机械有限公司 | Surface treatment method for precision parts of aviation seat |
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