CN110318084B - Implementation method for reducing black line material lines after anodic oxidation of aviation aluminum parts - Google Patents
Implementation method for reducing black line material lines after anodic oxidation of aviation aluminum parts Download PDFInfo
- Publication number
- CN110318084B CN110318084B CN201910748527.5A CN201910748527A CN110318084B CN 110318084 B CN110318084 B CN 110318084B CN 201910748527 A CN201910748527 A CN 201910748527A CN 110318084 B CN110318084 B CN 110318084B
- Authority
- CN
- China
- Prior art keywords
- anodic oxidation
- mins
- aviation aluminum
- treatment
- time
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Cleaning And De-Greasing Of Metallic Materials By Chemical Methods (AREA)
Abstract
The invention provides a realization method for reducing black line material lines of an anodized aviation aluminum part, which comprises the following steps: step S1, preparing an oil removing tank solution by using an oil removing agent, and performing oil removing treatment on the aviation aluminum parts; step S2, preparing an alkali corrosion bath solution to carry out alkali corrosion treatment on the aviation aluminum parts, wherein the time of the alkali corrosion treatment is 5-10S; step S3, preparing light-emitting tank liquid to carry out light-emitting treatment on the aviation aluminum parts; step S4, controlling the time of anodic oxidation according to the requirement of film thickness and the requirement of set voltage at the operating temperature of 11-13 ℃ to carry out anodic oxidation on the aviation aluminum parts; and step S5, preparing hole sealing bath solution by using a sealing agent, and carrying out hole sealing treatment on the aviation aluminum part. According to the invention, the optimized anodic oxidation treatment is carried out on the aviation aluminum parts for the aviation seat, so that the bad proportion of black lines of the aviation aluminum parts can be obviously reduced, the product appearance is improved, and the material waste probability is reduced.
Description
Technical Field
The invention relates to an implementation method of anodic oxidation, in particular to an implementation method for reducing black line material lines of an anodized aviation aluminum part.
Background
The 7 series aluminum alloy metal Al-Zn-Mg-Cu series high-strength aluminum alloy has a plurality of outstanding advantages, is widely applied to parts such as aviation seats and the like, but is easy to form poor texture such as black lines and the like after anodic oxidation due to improper process control or the influence of foreign impurities during roll forming. When the alloy is used for aviation seats, black wire material grains are easy to appear along the rolling direction after traditional anodic oxidation, and second-phase Al which is more enriched exists in the base material tissue6(FeMnSi), Al6(FeMn), when treated according to the traditional anodic oxidation process, the black line material has particularly obvious lines; this apparent black line defect, which affects the appearance and is not acceptable to the customer, can result inThe material waste is serious, and the production cost is increased.
Disclosure of Invention
The invention aims to solve the technical problem of providing an implementation method capable of effectively reducing appearance bad probabilities of black wire material lines, material black spots and the like appearing on the surface of an aviation aluminum part after anodic oxidation.
To the contrary, the invention provides a realization method for reducing black line material marks of an anodized aviation aluminum part, which comprises the following steps:
step S1, preparing an oil removing tank solution by using an oil removing agent, and performing oil removing treatment on the aviation aluminum parts;
step S2, preparing an alkali corrosion bath solution to carry out alkali corrosion treatment on the aviation aluminum parts, wherein the time of the alkali corrosion treatment is 5-10S;
step S3, preparing light-emitting tank liquid to carry out light-emitting treatment on the aviation aluminum parts;
step S4, controlling the time of anodic oxidation according to the requirement of film thickness and the requirement of set voltage at the operating temperature of 11-13 ℃ to carry out anodic oxidation on the aviation aluminum parts;
and step S5, preparing hole sealing bath solution by using a sealing agent, and carrying out hole sealing treatment on the aviation aluminum part.
The further improvement of the method is that in the step S2, an alkali corrosion bath solution is prepared according to the concentration of 40-60 g/l of sodium hydroxide, and the aviation aluminum parts are subjected to alkali corrosion treatment, wherein the operating temperature of the alkali corrosion treatment is 40-60 ℃.
The further improvement of the invention is that in the step S4, according to the film thickness requirement of 9-10 um and the requirement of the set voltage of 12-16V, the time of anodic oxidation is controlled to be 45-65 mins, and the aviation aluminum part is anodized.
The further improvement of the invention is that in the step S4, sulfuric acid with the concentration of 98% is used to prepare an anodic oxidation solution with the concentration of 190 g/l-200 g/l, the anodic oxidation of the aviation aluminum material part is realized in a set voltage, and the time of the anodic oxidation is set to be 50 mins-60 mins.
The further improvement of the invention is that when the set voltage is 12V, the anodic oxidation time is set to be 61 mins-65 mins; when the set voltage is 13V, the anodic oxidation time is set to be 56 mins-60 mins; when the set voltage is 14V, the anodic oxidation time is set to be 51-55 mins; when the set voltage is 15V, the anodic oxidation time is set to be 48 mins-50 mins; and when the set voltage is 16V, the anodic oxidation time is set to be 45 mins-47 mins.
A further improvement of the present invention is that when the set voltage is 12V, the anodic oxidation time is set to 63 mins; when the set voltage is 13V, the anodic oxidation time is set to 58 mins; when the set voltage is 14V, the anodic oxidation time is set to 53 mins; when the set voltage is 15V, the anodic oxidation time is set to 49 mins; when the set voltage is 16V, the anodization time is set to 46 mins.
The further improvement of the invention is that in the step S1, the degreasing bath solution is prepared according to the concentration of the degreasing agent of 40-60 g/l, and the aviation aluminum product parts are degreased, wherein the operating temperature of the degreasing treatment is 50-70 ℃, and the operating time of the degreasing treatment is 3-10 mins.
The further improvement of the invention is that in the step S3, a light-emitting bath solution is prepared by nitric acid and a light-emitting agent according to the concentration of the nitric acid being 50 g/l-100 g/l and the concentration of the light-emitting agent being 120 g/l-150 g/l, and the aviation aluminum material part is subjected to light-emitting treatment, wherein the operation temperature of the light-emitting treatment is room temperature.
The invention is further improved in that the operation time of the light emitting treatment is 30-120 s.
The invention is further improved in that in the step S5, a sealing agent is used for preparing a sealing groove liquid with the concentration of 8-10 g/l to realize the hole sealing treatment, the operation temperature of the hole sealing treatment is 85-95 ℃, and the hole sealing time of the hole sealing treatment is 10-30 mins.
Compared with the prior art, the invention has the beneficial effects that: through anodic oxidation treatment after optimizing the aviation aluminum product part for the aviation seat, make the bad proportion of its black line that reduces that aviation aluminum product part can be obvious has improved product appearance, has still reduced the extravagant probability of material, and then has reduced manufacturing cost, has improved the production speed and the efficiency of product.
Drawings
FIG. 1 is a schematic workflow diagram of one embodiment of the present invention;
FIG. 2 is a graph showing the comparison of the effects of anodizing an aircraft aluminum part using one embodiment of the present invention and anodizing using a conventional process.
Detailed Description
Preferred embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
As shown in fig. 1, the present example provides an implementation method for reducing black line streak after anodic oxidation of an aviation aluminum part, which includes the following steps:
step S1, preparing an oil removing tank solution by using an oil removing agent, and performing oil removing treatment on the aviation aluminum parts;
step S2, preparing an alkali corrosion bath solution to carry out alkali corrosion treatment on the aviation aluminum parts, wherein the time of the alkali corrosion treatment is 5-10S;
step S3, preparing light-emitting tank liquid to carry out light-emitting treatment on the aviation aluminum parts;
step S4, controlling the time of anodic oxidation according to the requirement of film thickness and the requirement of set voltage at the operating temperature of 11-13 ℃ to carry out anodic oxidation on the aviation aluminum parts;
and step S5, preparing hole sealing bath solution by using a sealing agent, and carrying out hole sealing treatment on the aviation aluminum part.
The aviation aluminum part is preferably an aviation aluminum part for realizing an aviation seat, namely an aluminum alloy part for realizing the aviation seat; in the step S1, an oil removing tank solution is prepared according to the concentration of an oil removing agent of 40-60 g/l, oil removing treatment is carried out on the aviation aluminum parts, the operating temperature of the oil removing treatment is 50-70 ℃, and the operating time of the oil removing treatment is 3-10 mins.
S1 in the embodiment is an oil removing process, SF-514 oil removing agent is mainly used, oil removing tank liquid is prepared according to the concentration of 40-60 g/l, the oil removing tank liquid with the concentration of 50g/l is better in effect, the aviation aluminum product parts are subjected to oil removing treatment, the operation temperature is 50-70 ℃, the time is 3-10 mins, and the purpose of removing pollutants such as grease, dust and the like on the surfaces of the aviation aluminum product parts can be achieved. And (4) after the aviation aluminum part is deoiled, washing with water, and then performing an alkali corrosion procedure in the step S2. Where mins is a unit of time and is expressed in minutes, min may be used.
In the step S2, an alkali corrosion bath solution is prepared according to the concentration of 40-60 g/l of sodium hydroxide, and the alkali corrosion treatment is carried out on the aviation aluminum parts, wherein the operating temperature of the alkali corrosion treatment is 40-60 ℃.
The sodium hydroxide is preferably used in the alkali corrosion treatment, the alkali corrosion tank liquor is prepared according to the concentration of 40-60 g/l of the sodium hydroxide, the alkali corrosion tank liquor with the concentration of 50g/l is better in effect, and the alkali corrosion treatment is carried out on the aviation aluminum parts at the operation temperature of 40-60 ℃ for 5-10 s. The method aims to further remove the dirt on the surface of the aviation aluminum part and thoroughly remove the natural oxidation film of the aviation aluminum part.
The embodiment aims at reducing the specificity of aviation aluminum parts for aviation seats, can reduce the corrosion of alkali liquor to aluminum alloy base materials of the aviation aluminum parts by shortening the reaction time of alkali corrosion on the premise of ensuring the removal of natural oxide films on the surfaces of the aviation aluminum parts, and when more second phases are deposited on the surfaces of the base materials, such as Al6(FeMnSi) and Al6(FeMn) and the like, which preferentially corrode an alkali etching solution with respect to an aluminum alloy substrate serving as an anode, and Fe, Mn and the like in a deposition phase do not react with the alkali etching solution, and the longer the time is, the more likely this uneven corrosion causes black line streaks of the material on the surface of the aluminum alloy. Therefore, in order to reduce the black lines, the present example aims at shortening the time of the alkali corrosion of the aircraft aluminum parts for reducing the aircraft seat. And (4) after the alkali corrosion, washing with water, and then performing a light emitting process in step S3.
In the step S3, a light-emitting groove solution is prepared by nitric acid and a light-emitting agent according to the nitric acid concentration of 50g/l to 100g/l and the light-emitting agent concentration of 120g/l to 150g/l, light-emitting treatment is performed on the aviation aluminum product part, the operating temperature of the light-emitting treatment is room temperature, and the operating time of the light-emitting treatment is 30S to 120S.
In the embodiment, the step S3 is used for realizing the light extraction process, preferably, nitric acid and a light extraction agent B-516 are used, a bath solution is prepared according to the concentration of the nitric acid being 50 g/l-100 g/l and the concentration of the light extraction agent B-516 being 120 g/l-150 g/l, and the aviation aluminum parts are subjected to light extraction treatment, wherein the operation temperature is room temperature and the time is 30S-120S. The purpose of the glazing process in this example is to remove the ash formed after the alkaline etching and further activate the aluminum surface. After the light emission, the resultant is washed with water and then subjected to the anodization step of step S4. Since aircraft aluminum parts used to reduce aircraft seating do not typically require chemical polishing if there is no gloss requirement, such chemical polishing is also an acidic etch which is also prone to material black lines.
In the step S4, according to the film thickness requirement of 9-10 um and the requirement of the set voltage of 12-16V, the time of anodic oxidation is controlled to be 45-65 mins, and the aviation aluminum parts are subjected to anodic oxidation; in the step S4, sulfuric acid with a concentration of 98% is preferably used to prepare an anodizing solution with a concentration of 190g/l to 200g/l, and the anodizing of the aircraft aluminum material part is realized at a set voltage, and the anodizing time is set to 50mins to 60 mins.
It should be noted that, in this embodiment, the time is controlled according to the requirement of the film thickness, and generally, according to the military standard requirement of MIL-a-8625, in this embodiment, when the anodic oxidation film thickness of the aviation aluminum material part is controlled to be about 10um, the voltage is preferably set to be 12V to 16V, and the anodic oxidation time is preferably set to be within the range of 50mins to 60 mins. When the set voltage is 12V, the anodic oxidation time is set to be 61 mins-65 mins; when the set voltage is 13V, the anodic oxidation time is set to be 56 mins-60 mins; when the set voltage is 14V, the anodic oxidation time is set to be 51-55 mins; when the set voltage is 15V, the anodic oxidation time is set to be 48 mins-50 mins; and when the set voltage is 16V, the anodic oxidation time is set to be 45 mins-47 mins.
More preferably, in this embodiment, when the set voltage is 12V, the anodization time is set to 63 mins; when the set voltage is 13V, the anodic oxidation time is set to 58 mins; when the set voltage is 14V, the anodic oxidation time is set to 53 mins; when the set voltage is 15V, the anodic oxidation time is set to 49 mins; when the set voltage is 16V, the anodizing time is set to 46mins, and the effect is more remarkable.
The embodiment also preferably adopts the anodic oxidation maintained at the low-temperature operation temperature of 11-13 ℃, so that the poor material black line proportion of the aviation aluminum parts can be obviously reduced. It is known that part of the electric energy is converted into heat energy in the anodic oxidation process, and the reaction is exothermic, and the reaction speed is higher at higher temperature, and the higher temperature causes the generated oxide film to be dissolved more quickly. The aviation aluminum alloy rolling or extruding material of aviation aluminum parts, particularly the core part of the material, is easy to enrich a second phase, elements such as Si in some alloy components or the second phase taking Si and the like as main components do not participate in a film forming reaction and can not be dissolved by an anodic oxidation bath, other impurity elements concentrated in the core part participate in film forming by a complex film forming reaction, and the temperature of anodic oxidation of the aviation aluminum parts is reduced by the embodiment, the temperature is controlled to be 11-13 ℃, the dissolution of the anodic oxidation bath on a generated oxidation film can be slowed down, the accumulation of the impurity elements which do not form the film or are difficult to form the film due to the fact that the impurity elements cannot be dissolved by the anodic oxidation bath is reduced, and therefore obvious black lines or black spots of the material are generated. After the anodic oxidation, water washing was performed. If the dyeing process is not necessary, the step proceeds to the sealing step of step S5 after washing with water.
In the step S5, the hole sealing agent is used to prepare hole sealing groove liquid with the concentration of 8g/l to 10g/l to realize hole sealing treatment, the operation temperature of the hole sealing treatment is 85 ℃ to 95 ℃, and the hole sealing time of the hole sealing treatment is 10mins to 30 mins.
In the step S5, the sealing is mainly performed by using SF-558 sealant, and the sealant is prepared into bath solution with the concentration of 8 g/l-10 g/l. The operation temperature is 90 ℃ plus or minus 5 ℃, and the hole sealing time is controlled to be 20mins plus or minus 10mins according to the thickness of the film layer. The hole sealing aims at reducing the porosity and the adsorption capacity of the anodic oxide film and improving the corrosion resistance and the dirt resistance of the anodic oxide film. And after hole sealing, washing with water, drying water, and hanging the anodized aviation aluminum part.
In order to test the effect of the present example, as shown in fig. 2, the present example also performs a comparative test on the anodizing effect 1 of the aviation aluminum material part by using the conventional process and the anodizing effect 2 of the aviation aluminum material part by using the present application; in fig. 2, the aviation aluminum parts anodized on the left by the conventional process have obvious material black lines, and the aviation aluminum parts anodized on the right by the conventional process have no obvious material black lines, so that the contrast effect is very obvious.
Also, this example was tested and compared according to the requirements of military Standard MIL-A-8625, Type II, as shown in the following Table.
| Test piece material | Test piece size | Test items | Conventional process | The process | MIL-A-8625, Type II test requirement |
| 7075-T651 | 3*10*0.032(inch) | Salt spray test | No corrosion spot | No corrosion spot | After the salt spray test, the surface has no corrosion point |
| 7075-T651 | 3*3*0.032(inch) | Film weight test | 1681.87 mg/ft2 | 1967.73 mg/ft2 | ≧1000mg/ft2 |
From the test conclusions in the above table, it can be seen that this example was tested according to the military standard MIL-A-8625, Type II, and that the salt spray test and the film weight test were also fully satisfactory.
In conclusion, the optimized anodic oxidation treatment is carried out on the aviation aluminum parts for the aviation seat, so that the bad proportion of black lines of the aviation aluminum parts can be obviously reduced, the appearance of the product is improved, the probability of material waste is reduced, the production cost is reduced, and the production speed and the production efficiency of the product are improved.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (8)
1. An implementation method for reducing black line material marks of an anodized aviation aluminum part is characterized by comprising the following steps:
step S1, preparing an oil removing tank solution by using an oil removing agent, and performing oil removing treatment on the aviation aluminum parts;
step S2, preparing an alkali corrosion bath solution to carry out alkali corrosion treatment on the aviation aluminum parts, wherein the time of the alkali corrosion treatment is 5-10S;
step S3, preparing light-emitting tank liquid to carry out light-emitting treatment on the aviation aluminum parts;
step S4, controlling the time of anodic oxidation according to the requirement of film thickness and the requirement of set voltage at the operating temperature of 11-13 ℃ to carry out anodic oxidation on the aviation aluminum parts;
step S5, preparing hole sealing tank liquor by using a sealing agent, and carrying out hole sealing treatment on the aviation aluminum part;
in the step S2, preparing an alkali corrosion bath solution according to the concentration of 40-60 g/l of sodium hydroxide, carrying out alkali corrosion treatment on the aviation aluminum parts, wherein the operating temperature of the alkali corrosion treatment is 40-60 ℃, washing with water after the alkali corrosion, and then entering the step S3 to realize a light-emitting process;
in the step S4, according to the film thickness requirement of 9 um-10 um and the requirement of the set voltage of 12V-16V, the time of anodic oxidation is controlled to be 45 mins-65 mins, and the anodic oxidation is carried out on the aviation aluminum parts.
2. The method as claimed in claim 1, wherein in step S4, sulfuric acid with a concentration of 98% is used to prepare an anodizing solution with a concentration of 190-200 g/l, and the anodizing of the aviation aluminum material part is performed at a set voltage, and the anodizing time is set to 50-60 mins.
3. An implementation method for reducing black line streak after anodic oxidation of an aviation aluminum part as claimed in claim 1, wherein when the set voltage is 12V, the anodic oxidation time is set to 61 mins-65 mins; when the set voltage is 13V, the anodic oxidation time is set to be 56 mins-60 mins; when the set voltage is 14V, the anodic oxidation time is set to be 51-55 mins; when the set voltage is 15V, the anodic oxidation time is set to be 48 mins-50 mins; and when the set voltage is 16V, the anodic oxidation time is set to be 45 mins-47 mins.
4. An implementation method for reducing black line streak after anodic oxidation of an aircraft aluminum material part according to claim 3, characterized in that when the set voltage is 12V, the anodic oxidation time is set to 63 mins; when the set voltage is 13V, the anodic oxidation time is set to 58 mins; when the set voltage is 14V, the anodic oxidation time is set to 53 mins; when the set voltage is 15V, the anodic oxidation time is set to 49 mins; when the set voltage is 16V, the anodization time is set to 46 mins.
5. The method for reducing the black line material marks of the anodized aviation aluminum product parts as claimed in any one of claims 1 to 4, wherein in the step S1, an oil removing bath solution is prepared according to an oil removing agent concentration of 40-60 g/l, and the aviation aluminum product parts are subjected to oil removing treatment, wherein the oil removing treatment temperature is 50-70 ℃, and the oil removing treatment time is 3-10 mins.
6. The method for reducing the black lines and the dark stripes of the anodized aviation aluminum parts as claimed in any one of claims 1 to 4, wherein in the step S3, a bright dipping bath solution is prepared by nitric acid and a bright dipping agent according to the concentration of the nitric acid being 50g/l to 100g/l and the concentration of the bright dipping agent being 120g/l to 150g/l, and the bright dipping treatment is performed on the aviation aluminum parts, wherein the operating temperature of the bright dipping treatment is room temperature.
7. The implementation method for reducing the black line material marks of the anodized aviation aluminum part as claimed in claim 6, wherein the operation time of the bright dipping treatment is 30-120 s.
8. The method for reducing the black line streak after the anodic oxidation of the aviation aluminum material part according to any one of claims 1 to 4, wherein in the step S5, a sealing agent is used to prepare a sealing bath solution with a concentration of 8g/l to 10g/l to realize the hole sealing treatment, the operation temperature of the hole sealing treatment is 85 ℃ to 95 ℃, and the hole sealing time of the hole sealing treatment is 10mins to 30 mins.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910748527.5A CN110318084B (en) | 2019-08-14 | 2019-08-14 | Implementation method for reducing black line material lines after anodic oxidation of aviation aluminum parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910748527.5A CN110318084B (en) | 2019-08-14 | 2019-08-14 | Implementation method for reducing black line material lines after anodic oxidation of aviation aluminum parts |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110318084A CN110318084A (en) | 2019-10-11 |
| CN110318084B true CN110318084B (en) | 2021-05-14 |
Family
ID=68126132
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910748527.5A Active CN110318084B (en) | 2019-08-14 | 2019-08-14 | Implementation method for reducing black line material lines after anodic oxidation of aviation aluminum parts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110318084B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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 |
-
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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110318084A (en) | 2019-10-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101205617A (en) | Surface treating method for metal workpieces | |
| US20120217167A1 (en) | Method for painting article to be treated | |
| US11230782B2 (en) | Passivation surface treatment of stainless steel | |
| JP2006513322A (en) | Color finishing method | |
| CN103938251B (en) | Aluminum alloy hub surface anodic oxidation treatment process | |
| WO2012119306A1 (en) | Method for Producing White Anodized Aluminum Oxide | |
| CN110607549A (en) | Anti-static hard anodic oxidation process | |
| CN110318084B (en) | Implementation method for reducing black line material lines after anodic oxidation of aviation aluminum parts | |
| CN109183113A (en) | A kind of processing method of aluminium alloy anode oxide | |
| KR100914858B1 (en) | A method for treating a surface of magnesium alloy with antibacterial activity kepping metallic tone of bare magnesium alloy | |
| CN104988554A (en) | High-low-temperature composite type anodic oxidation hole sealing method | |
| CN112522763A (en) | Aluminum alloy dyeing additive and dyeing method | |
| CN103943277A (en) | Production process of tinned-copper-clad steel | |
| CN107805835A (en) | Aluminium section bar Coloured Anodizing technique | |
| CN112725865A (en) | Surface treatment process of high-strength corrosion-resistant aluminum alloy for wheelchair processing | |
| EP1233084A2 (en) | "Anodizing process, with low environmental impact, for a workpiece of aluminium or aluminium alloys" | |
| US2075623A (en) | Zinc plating | |
| CN102061472A (en) | Surface oxidizing and film coating method for mirror finish aluminum | |
| US2888387A (en) | Electroplating | |
| JPH1171696A (en) | Electrogalvanization of secondary formed article | |
| US2570174A (en) | Metal cleaning and plating process | |
| JP3553288B2 (en) | Vehicle wheels with excellent corrosion resistance and glitter | |
| CN115198255B (en) | Titanium surface electrolytic hydrogen charging activation chemical nickel plating method | |
| CN110195232A (en) | A kind of caustic solution of stroboscopic lamp capacitor anode foils | |
| CN116892047A (en) | White anodic oxidation process for aluminum alloy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |