CN111996524A - Method for repairing damage of wear-resistant layer of aluminum alloy piston rod of airplane hydraulic system - Google Patents
Method for repairing damage of wear-resistant layer of aluminum alloy piston rod of airplane hydraulic system Download PDFInfo
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- CN111996524A CN111996524A CN202010703222.5A CN202010703222A CN111996524A CN 111996524 A CN111996524 A CN 111996524A CN 202010703222 A CN202010703222 A CN 202010703222A CN 111996524 A CN111996524 A CN 111996524A
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 89
- 238000000034 method Methods 0.000 title claims abstract description 70
- 230000008569 process Effects 0.000 claims abstract description 26
- 239000011248 coating agent Substances 0.000 claims abstract description 20
- 238000000576 coating method Methods 0.000 claims abstract description 20
- 238000007789 sealing Methods 0.000 claims abstract description 20
- 238000010288 cold spraying Methods 0.000 claims abstract description 17
- 230000007797 corrosion Effects 0.000 claims abstract description 16
- 238000005260 corrosion Methods 0.000 claims abstract description 16
- 238000002048 anodisation reaction Methods 0.000 claims abstract description 13
- 238000005507 spraying Methods 0.000 claims abstract description 13
- 239000000654 additive Substances 0.000 claims abstract description 8
- 230000000996 additive effect Effects 0.000 claims abstract description 8
- 239000003513 alkali Substances 0.000 claims abstract description 8
- 239000000758 substrate Substances 0.000 claims abstract description 8
- 238000005299 abrasion Methods 0.000 claims abstract description 5
- 230000000007 visual effect Effects 0.000 claims abstract description 4
- 238000004140 cleaning Methods 0.000 claims description 15
- 239000000463 material Substances 0.000 claims description 11
- 238000007743 anodising Methods 0.000 claims description 10
- SOCTUWSJJQCPFX-UHFFFAOYSA-N dichromate(2-) Chemical compound [O-][Cr](=O)(=O)O[Cr]([O-])(=O)=O SOCTUWSJJQCPFX-UHFFFAOYSA-N 0.000 claims description 10
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 10
- HEMHJVSKTPXQMS-UHFFFAOYSA-M Sodium hydroxide Chemical compound [OH-].[Na+] HEMHJVSKTPXQMS-UHFFFAOYSA-M 0.000 claims description 9
- 239000003795 chemical substances by application Substances 0.000 claims description 9
- 238000005488 sandblasting Methods 0.000 claims description 9
- 239000007921 spray Substances 0.000 claims description 8
- 239000008367 deionised water Substances 0.000 claims description 7
- 229910021641 deionized water Inorganic materials 0.000 claims description 7
- QAOWNCQODCNURD-UHFFFAOYSA-N Sulfuric acid Chemical compound OS(O)(=O)=O QAOWNCQODCNURD-UHFFFAOYSA-N 0.000 claims description 6
- 239000000203 mixture Substances 0.000 claims description 6
- KMUONIBRACKNSN-UHFFFAOYSA-N potassium dichromate Chemical compound [K+].[K+].[O-][Cr](=O)(=O)O[Cr]([O-])(=O)=O KMUONIBRACKNSN-UHFFFAOYSA-N 0.000 claims description 6
- 239000000843 powder Substances 0.000 claims description 6
- 239000000565 sealant Substances 0.000 claims description 6
- JHWIEAWILPSRMU-UHFFFAOYSA-N 2-methyl-3-pyrimidin-4-ylpropanoic acid Chemical compound OC(=O)C(C)CC1=CC=NC=N1 JHWIEAWILPSRMU-UHFFFAOYSA-N 0.000 claims description 3
- 229910001250 2024 aluminium alloy Inorganic materials 0.000 claims description 3
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 3
- 230000001680 brushing effect Effects 0.000 claims description 3
- 239000012159 carrier gas Substances 0.000 claims description 3
- 229910052593 corundum Inorganic materials 0.000 claims description 3
- 239000010431 corundum Substances 0.000 claims description 3
- 239000002173 cutting fluid Substances 0.000 claims description 3
- 239000010730 cutting oil Substances 0.000 claims description 3
- 238000001035 drying Methods 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 239000001307 helium Substances 0.000 claims description 3
- 229910052734 helium Inorganic materials 0.000 claims description 3
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 3
- 239000002245 particle Substances 0.000 claims description 3
- 239000011347 resin Substances 0.000 claims description 3
- 229920005989 resin Polymers 0.000 claims description 3
- 239000004576 sand Substances 0.000 claims description 3
- 238000002791 soaking Methods 0.000 claims description 3
- 230000003746 surface roughness Effects 0.000 claims description 3
- 238000005406 washing Methods 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 abstract description 4
- 238000011084 recovery Methods 0.000 abstract description 4
- 238000005549 size reduction Methods 0.000 abstract description 3
- 239000011159 matrix material Substances 0.000 description 8
- 230000008439 repair process Effects 0.000 description 5
- 238000003487 electrochemical reaction Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
- C23C24/045—Impact or kinetic deposition of particles by trembling using impacting inert media
-
- 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
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Electrochemistry (AREA)
- Mechanical Engineering (AREA)
- General Chemical & Material Sciences (AREA)
- Inorganic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The invention relates to a method for repairing damage of an aluminum alloy piston rod wear-resistant layer of an aircraft hydraulic system, which comprises the following specific steps: removing the old film layer on the aluminum alloy piston rod by an alkali corrosion method; whether the surface of the aluminum alloy piston rod substrate has damages such as corrosion, gouge, scratch, abrasion and the like is checked in a visual mode, and the existing damages are eliminated; and measuring the size of the outer circular surface of the piston rod, calculating the thickness size, and adding a spraying coating thickness of 1-2 mm to the thickness size. According to the invention, on the basis of the existing repairing method, the repairing process and flow are optimized, a cold spraying additive process is added, the size recovery of the piston rod is realized through cold additive forming, the hard anodization of the coating is carried out on the basis, and then the sealing technology is utilized to seal the film layer, so that the sealing performance of the film layer is further improved. The problem of the size reduction of the piston rod after the old film layer is removed by adopting alkaline corrosion and hard anodization is carried out again in the traditional repairing process is solved.
Description
Technical Field
The invention relates to the technical field of repair of accessories of an airplane part, in particular to a method for repairing damage of an aluminum alloy piston rod wear-resistant layer of an airplane hydraulic system.
Background
The piston rod is an important force transmission component in an airplane hydraulic system, frequent reciprocating motion and load bearing are needed, and in order to improve the wear resistance of the aluminum alloy piston rod, a hard anodizing process is often adopted in the part machining process, a compact and wear-resistant gray black oxide protective film is generated on the surface of the part through electrochemical reaction, the thickness is about 50-60 mu m, and the wear resistance of the part can be obviously improved. Along with the increase of part live time, faults such as wearing and tearing, fish tail can appear in the anodization layer, lead to the fit clearance too big, sealing performance descends, appear oil leak scheduling problem, influence the use reliability, need restore the piston rod.
The common fault repairing method comprises the following steps: removing hard anodized old film → removing substrate damage (if necessary, if and only if there is damage to the substrate after the film is removed) → re-hard anodizing, but the above-described process has the following problems: the hard anodized old film layer is removed by mainly adopting an alkali corrosion method, a part of matrix size can be lost in the removing process, the anodized new film layer is generated by mainly depending on the electrochemical reaction between the matrix and bath solution, a part of size can be lost due to the participation of the matrix in the reaction in the new film layer generating process, namely when the matrix is not damaged and removed, the unilateral size of the piston rod can be reduced by about 30 mu m by re-anodizing, and if the piston rod matrix is damaged, the piston rod size can be smaller after the damage is removed. After anodizing for 1-2 times, the piston rod can be completely unrepairable due to the over-small size and the serious fit clearance.
Disclosure of Invention
Aiming at the problems, the invention provides a method for repairing the damage of an aluminum alloy piston rod wear-resistant layer of an airplane hydraulic system, which optimizes a repairing process and a flow on the basis of the existing repairing method, adds a cold spraying material increase process after the damage of a matrix is eliminated, realizes the size recovery of the piston rod through cold material increase forming, develops hard anodization of a coating on the basis, and then seals the film layer by using a hole sealing technology to further improve the sealing performance of the film layer and finish the repairing of the piston rod.
The technical problem to be solved by the invention is realized by adopting the following technical scheme:
a method for repairing damage of an aluminum alloy piston rod wear-resistant layer of an aircraft hydraulic system comprises the following specific steps:
removing the old film layer on the aluminum alloy piston rod by an alkali corrosion method;
secondly, whether the surface of the aluminum alloy piston rod substrate has damages such as corrosion, gouge, scratch, abrasion and the like is checked in a visual mode, and the existing damages are eliminated;
thirdly, measuring the size of the outer circular surface of the piston rod, calculating the thickness size, and adding a spraying coating thickness of 1-2 mm to the thickness size;
fourthly, carrying out sand blasting texturing pretreatment on the surface of the aluminum alloy piston rod;
after the aluminum alloy piston rod is fixedly clamped, the aluminum alloy piston rod is enabled to rotate at a constant speed of 0.8-1 m/s according to the requirement, and the aluminum alloy piston rod is matched with cold spraying equipment to carry out cold spraying material increase on the surface of the aluminum alloy piston rod;
sixthly, after cold spraying and material increasing are finished on the surface of the aluminum alloy piston rod, processing the surface coating of the aluminum alloy piston rod by a turning method, and cleaning the processed coating;
seventhly, hard anodization is carried out on the surface coating of the aluminum alloy piston rod;
(VIII) cleaning the hard anodized aluminum alloy piston rod by using deionized water and filling with dichromate;
and (ninthly), sealing the surface of the aluminum alloy piston rod filled with the dichromate by using a 518 sealant.
Further, the specific process of removing the old film layer on the aluminum alloy piston rod by the alkali corrosion method in the step (I) is as follows:
(a) soaking and removing the old film layer by adopting industrial-grade sodium hydroxide at the temperature of 40-55 ℃, wherein the removing time is about 2 min;
(b) and (3) immersing the part into clean flowing hot water at 40-60 ℃ for cleaning for 1-3 min, and drying the part after cleaning.
Further, in the step (II), the damage on the surface of the aluminum alloy piston rod substrate is eliminated in a turning mode.
And further, carrying out sand blasting and texturing on 46-mesh brown corundum sand in the step (IV), wherein the surface roughness of the aluminum alloy piston rod after sand blasting is controlled to be Ra5.0-7.6 microns.
Further, the parameters during cold spraying additive in the step (five) are as follows:
(A) preheating temperature of the aluminum alloy piston rod: 40-60 ℃;
(B) coating materials: 2024 aluminum alloy powder with the particle size of 5-45 μm;
(C) spraying carrier gas: 99.99% helium;
(D) spraying distance: 10-15 mm;
(E) pressure of the spray gun: 230-250 psi;
(F) heating temperature: 450-500 ℃;
(G) powder feeding amount: 25-35 g/min;
(H) moving speed of the spray gun: 120-150 mm/s.
Further, the cleaning process in the step (six) is as follows:
(S1) removing cutting fluid and oil stains on the surface of the aluminum alloy piston rod by using washing gasoline or industrial alcohol;
(S2) the surface of the aluminum alloy piston rod is cleaned by deionized water.
Further, the parameters of the hard anodizing process in the step (seven) are specifically as follows:
power supply: direct current power supply, anode current density: 2 to 2.5A/dm2；
② solution: industrial grade sulfuric acid;
③ temperature: -8 to 0 ℃;
and fourthly, cathode: pb1, Pb2 lead plate;
anodizing time: 60-80 min.
Further, the dichromate in the step (eight) includes sodium dichromate and potassium dichromate.
Further, the closing process in the step (nine) is specifically as follows:
(I) the resin and the curing agent are mixed according to the proportion of 2: 1, 518 sealant is prepared;
(II) brushing the prepared 518 hole sealing agent to the surface of an anodized film layer to be sealed on the aluminum alloy piston rod by using a brush;
(III) after being uniformly coated, placing the mixture at room temperature for 6-8 h, then placing the mixture into an oven, and preserving heat for 2h at the temperature of 120-150 ℃ to cure the hole sealing agent.
The invention has the beneficial effects that:
compared with the prior art, the method optimizes the repair process and flow on the basis of the existing repair method, adds a cold spraying additive process after the damage of the matrix is eliminated, realizes the size recovery of the piston rod through cold additive forming, develops hard anodization of the coating on the basis, and then seals the film by using a hole sealing technology to further improve the sealing performance of the film. The problem of the size reduction of the piston rod after the old film layer is removed by adopting alkaline corrosion and hard anodization is carried out again in the traditional repairing process is solved.
Drawings
The invention is further illustrated with reference to the following figures and examples:
FIG. 1 is a process flow diagram of the present invention.
Detailed Description
In order to make the technical means, the creation features, the achievement purposes and the effects of the invention easy to understand, the invention is further explained in the following with the accompanying drawings and the embodiments.
As shown in FIG. 1, the method for repairing the damage of the wear-resistant layer of the aluminum alloy piston rod of the aircraft hydraulic system comprises the following specific steps:
and (I) removing the old film layer on the aluminum alloy piston rod by an alkali corrosion method.
Specifically, the specific process for removing the old film layer on the aluminum alloy piston rod by the alkali corrosion method is as follows:
(a) soaking and removing the old film layer by adopting industrial-grade sodium hydroxide at the temperature of 40-55 ℃, wherein the removing time is about 2 min;
(b) and (3) immersing the part into clean flowing hot water at 40-60 ℃ for cleaning for 1-3 min, and drying the part after cleaning.
And (II) inspecting whether the surface of the aluminum alloy piston rod substrate has damages such as corrosion, gouge, scratch, abrasion and the like by a visual mode, and removing the existing damages.
Specifically, the surface state of the aluminum alloy piston rod base body is visually inspected under the illumination intensity of not less than 300lx, if the defects such as corrosion, gouge, scratch, abrasion and the like exist, the damaged part of the aluminum alloy piston rod needs to be eliminated, and the elimination mode is as follows: and turning the damaged part on the aluminum alloy piston rod through a lathe and aligning the outer circular surface.
And thirdly, measuring the size of the outer circular surface of the piston rod, calculating the thickness size, and adding a spraying coating thickness of 1-2 mm to the thickness size.
And (IV) carrying out sand blasting texturing pretreatment on the surface of the aluminum alloy piston rod.
Specifically, firstly, a non-spraying area on the surface of the aluminum alloy piston rod is shielded and protected by using an adhesive tape, then, 46-mesh brown corundum sand is used for sand blasting and texturing, and the roughness of the surface of the aluminum alloy piston rod after sand blasting is controlled to be Ra5.0-7.6 microns.
And (V) after the aluminum alloy piston rod is fixedly clamped, enabling the aluminum alloy piston rod to rotate at a constant speed of 0.8-1 m/s according to the requirement, and matching with cold spraying equipment to perform cold spraying material increase on the surface of the aluminum alloy piston rod.
Specifically, the aluminum alloy piston rod is clamped on the rotating mechanism and is tightly pushed by the pneumatic ejector pin, the circumferential runout of the aluminum alloy piston rod is detected by the dial indicator after the aluminum alloy piston rod is tightly pushed, the linear velocity of the outer circular surface of the aluminum alloy piston rod is ensured to be 0.8-1 m/s by setting the motor rotating speed after the aluminum alloy piston rod is qualified, and the calculation formula of the motor rotating speed is as follows: n is v/2 pi R, where v is the linear velocity in m/s and R is the part radius in m.
Then, a spray gun in the cold spraying equipment is clamped by a mechanical arm, the spray gun is used for preheating the aluminum alloy piston rod before spraying, spraying is started after preheating, and the parameters of the cold spraying process are as follows:
(A) preheating temperature of the aluminum alloy piston rod: 40-60 ℃;
(B) coating materials: 2024 aluminum alloy powder with the particle size of 5-45 μm;
(C) spraying carrier gas: 99.99% helium;
(D) spraying distance: 10-15 mm;
(E) pressure of the spray gun: 230-250 psi;
(F) heating temperature: 450-500 ℃;
(G) powder feeding amount: 25-35 g/min;
(H) moving speed of the spray gun: 120-150 mm/s.
And (VI) after cold spraying and material increasing are finished on the surface of the aluminum alloy piston rod, processing the surface coating of the aluminum alloy piston rod by a turning method, and cleaning after processing.
Specifically, the aluminum alloy coating is machined by adopting a turning method, the size and the roughness of the aluminum alloy piston rod are ensured by adopting a rough turning and finish turning mode, the size of the aluminum alloy piston rod after finish machining can be controlled by subtracting the thickness of 1/2 film layers from the pattern size, and the surface roughness of the aluminum alloy piston rod is not lower than Ra1.6 mu m.
The cleaning process of the turned aluminum alloy piston rod is as follows:
(S1) removing cutting fluid and oil stains on the surface of the aluminum alloy piston rod by using washing gasoline or industrial alcohol;
(S2) the surface of the aluminum alloy piston rod is cleaned by deionized water.
And (seventhly), hard anodizing is carried out on the surface coating of the aluminum alloy piston rod.
Specifically, before hard anodization, the non-treated part needs to be protected in an insulating way, and the parameters of the hard anodization process are as follows:
power supply: direct current power supply, anode current density: 2 to 2.5A/dm2；
② solution: industrial grade sulfuric acid;
③ temperature: -8 to 0 ℃;
and fourthly, cathode: pb1, Pb2 lead plate;
anodizing time: 60-80 min.
And (eighthly), cleaning the hard anodized aluminum alloy piston rod with deionized water and carrying out dichromate filling.
Specifically, after anodization, parts are cleaned by deionized water for 2-3 min, and then are filled with dichromate, wherein the dichromate comprises sodium dichromate and potassium dichromate.
And (ninthly), sealing the surface of the aluminum alloy piston rod filled with the dichromate by using a 518 sealant.
Specifically, the sealing treatment comprises the following steps:
(I) the resin and the curing agent are mixed according to the proportion of 2: 1, 518 sealant is prepared;
(II) brushing the prepared 518 hole sealing agent to the surface of an anodized film layer to be sealed on the aluminum alloy piston rod by using a brush;
(III) after being uniformly coated, placing the mixture at room temperature for 6-8 h, then placing the mixture into an oven, and preserving heat for 2h at the temperature of 120-150 ℃ to cure the hole sealing agent.
The method optimizes the repair process and flow on the basis of the existing repair method, adds a cold spraying additive process after the damage of the matrix is eliminated, realizes the size recovery of the piston rod through cold additive forming, develops hard anodization of the coating on the basis, and then seals the film by using a hole sealing technology to further improve the sealing performance of the film. The problem of the size reduction of the piston rod after the old film layer is removed by adopting alkaline corrosion and hard anodization is carried out again in the traditional repairing process is solved.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (9)
1. The method for repairing the damage of the wear-resistant layer of the aluminum alloy piston rod of the aircraft hydraulic system is characterized by comprising the following steps of: the method comprises the following specific steps:
removing the old film layer on the aluminum alloy piston rod by an alkali corrosion method;
secondly, whether the surface of the aluminum alloy piston rod substrate has damages such as corrosion, gouge, scratch, abrasion and the like is checked in a visual mode, and the existing damages are eliminated;
thirdly, measuring the size of the outer circular surface of the piston rod, calculating the thickness size, and adding a spraying coating thickness of 1-2 mm to the thickness size;
fourthly, carrying out sand blasting texturing pretreatment on the surface of the aluminum alloy piston rod;
after the aluminum alloy piston rod is fixedly clamped, the aluminum alloy piston rod is enabled to rotate at a constant speed of 0.8-1 m/s according to the requirement, and the aluminum alloy piston rod is matched with cold spraying equipment to carry out cold spraying material increase on the surface of the aluminum alloy piston rod;
sixthly, after cold spraying and material increasing are finished on the surface of the aluminum alloy piston rod, processing the surface coating of the aluminum alloy piston rod by a turning method, and cleaning the processed coating;
seventhly, hard anodization is carried out on the surface coating of the aluminum alloy piston rod;
(VIII) cleaning the hard anodized aluminum alloy piston rod by using deionized water and filling with dichromate;
and (ninthly), sealing the surface of the aluminum alloy piston rod filled with the dichromate by using a 518 sealant.
2. The method for repairing the damage of the wear-resistant layer of the aluminum alloy piston rod of the aircraft hydraulic system as recited in claim 1, wherein the method comprises the following steps: the specific process for removing the old film layer on the aluminum alloy piston rod by the alkali corrosion method in the step (I) is as follows:
(a) soaking and removing the old film layer by adopting industrial-grade sodium hydroxide at the temperature of 40-55 ℃, wherein the removing time is about 2 min;
(b) and (3) immersing the part into clean flowing hot water at 40-60 ℃ for cleaning for 1-3 min, and drying the part after cleaning.
3. The method for repairing the damage of the wear-resistant layer of the aluminum alloy piston rod of the aircraft hydraulic system as recited in claim 1, wherein the method comprises the following steps: and (II) removing the damage on the surface of the aluminum alloy piston rod substrate in a turning mode.
4. The method for repairing the damage of the wear-resistant layer of the aluminum alloy piston rod of the aircraft hydraulic system as recited in claim 1, wherein the method comprises the following steps: and (IV) carrying out sand blasting and texturing by adopting 46-mesh brown corundum sand, wherein the surface roughness of the aluminum alloy piston rod after sand blasting is controlled to be Ra5.0-7.6 mu m.
5. The method for repairing the damage of the wear-resistant layer of the aluminum alloy piston rod of the aircraft hydraulic system as recited in claim 1, wherein the method comprises the following steps: the parameters in the cold spraying additive in the step (V) are as follows:
(A) preheating temperature of the aluminum alloy piston rod: 40-60 ℃;
(B) coating materials: 2024 aluminum alloy powder with the particle size of 5-45 μm;
(C) spraying carrier gas: 99.99% helium;
(D) spraying distance: 10-15 mm;
(E) pressure of the spray gun: 230-250 psi;
(F) heating temperature: 450-500 ℃;
(G) powder feeding amount: 25-35 g/min;
(H) moving speed of the spray gun: 120-150 mm/s.
6. The method for repairing the damage of the wear-resistant layer of the aluminum alloy piston rod of the aircraft hydraulic system as recited in claim 1, wherein the method comprises the following steps: the cleaning process in the step (six) is as follows:
(S1) removing cutting fluid and oil stains on the surface of the aluminum alloy piston rod by using washing gasoline or industrial alcohol;
(S2) the surface of the aluminum alloy piston rod is cleaned by deionized water.
7. The method for repairing the damage of the wear-resistant layer of the aluminum alloy piston rod of the aircraft hydraulic system as recited in claim 1, wherein the method comprises the following steps: the parameters of the hard anodizing process in the step (VII) are as follows:
power supply: direct current power supply, anode current density: 2 to 2.5A/dm2；
② solution: industrial grade sulfuric acid;
③ temperature: -8 to 0 ℃;
and fourthly, cathode: pb1, Pb2 lead plate;
anodizing time: 60-80 min.
8. The method for repairing the damage of the wear-resistant layer of the aluminum alloy piston rod of the aircraft hydraulic system as recited in claim 1, wherein the method comprises the following steps: the dichromate in the step (eight) comprises sodium dichromate and potassium dichromate.
9. The method for repairing the damage of the wear-resistant layer of the aluminum alloy piston rod of the aircraft hydraulic system as recited in claim 1, wherein the method comprises the following steps: the specific process of the sealing treatment in the step (nine) is as follows:
(I) the resin and the curing agent are mixed according to the proportion of 2: 1, 518 sealant is prepared;
(II) brushing the prepared 518 hole sealing agent to the surface of an anodized film layer to be sealed on the aluminum alloy piston rod by using a brush;
(III) after being uniformly coated, placing the mixture at room temperature for 6-8 h, then placing the mixture into an oven, and preserving heat for 2h at the temperature of 120-150 ℃ to cure the hole sealing agent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010703222.5A CN111996524A (en) | 2020-07-21 | 2020-07-21 | Method for repairing damage of wear-resistant layer of aluminum alloy piston rod of airplane hydraulic system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010703222.5A CN111996524A (en) | 2020-07-21 | 2020-07-21 | Method for repairing damage of wear-resistant layer of aluminum alloy piston rod of airplane hydraulic system |
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| US20060216428A1 (en) * | 2005-03-23 | 2006-09-28 | United Technologies Corporation | Applying bond coat to engine components using cold spray |
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| US20100155251A1 (en) * | 2008-12-23 | 2010-06-24 | United Technologies Corporation | Hard anodize of cold spray aluminum layer |
| CN107904593A (en) * | 2017-11-18 | 2018-04-13 | 四川长江液压天成机械有限公司 | A kind of hydraulic cylinder piston rod pulls renovation technique |
| CN109023211A (en) * | 2018-10-12 | 2018-12-18 | 广东省新材料研究所 | A kind of hydraulic actuator wear resistant friction reducing iron oxide yellow copper coating and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20060216428A1 (en) * | 2005-03-23 | 2006-09-28 | United Technologies Corporation | Applying bond coat to engine components using cold spray |
| CN101220495A (en) * | 2007-09-28 | 2008-07-16 | 四川航空液压机械厂 | Method for processing multiple anodization surface of light metal products |
| US20100155251A1 (en) * | 2008-12-23 | 2010-06-24 | United Technologies Corporation | Hard anodize of cold spray aluminum layer |
| CN107904593A (en) * | 2017-11-18 | 2018-04-13 | 四川长江液压天成机械有限公司 | A kind of hydraulic cylinder piston rod pulls renovation technique |
| CN109023211A (en) * | 2018-10-12 | 2018-12-18 | 广东省新材料研究所 | A kind of hydraulic actuator wear resistant friction reducing iron oxide yellow copper coating and preparation method thereof |
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Application publication date: 20201127 |