CN115354317A - Method for repairing serious corrosion of piston rod base body and chromium layer of airplane actuator cylinder - Google Patents
Method for repairing serious corrosion of piston rod base body and chromium layer of airplane actuator cylinder Download PDFInfo
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- CN115354317A CN115354317A CN202210931965.7A CN202210931965A CN115354317A CN 115354317 A CN115354317 A CN 115354317A CN 202210931965 A CN202210931965 A CN 202210931965A CN 115354317 A CN115354317 A CN 115354317A
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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
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B27/00—Other grinding machines or devices
- B24B27/033—Other grinding machines or devices for grinding a surface for cleaning purposes, e.g. for descaling or for grinding off flaws in the surface
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
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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
- C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
- C23F1/00—Etching metallic material by chemical means
- C23F1/10—Etching compositions
- C23F1/14—Aqueous compositions
- C23F1/32—Alkaline compositions
- C23F1/38—Alkaline compositions for etching refractory metals
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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
- C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
- C23F1/00—Etching metallic material by chemical means
- C23F1/44—Compositions for etching metallic material from a metallic material substrate of different composition
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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
- C25D3/00—Electroplating: Baths therefor
- C25D3/02—Electroplating: Baths therefor from solutions
- C25D3/04—Electroplating: Baths therefor from solutions of chromium
- C25D3/06—Electroplating: Baths therefor from solutions of chromium from solutions of trivalent chromium
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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
- C25D5/00—Electroplating characterised by the process; Pretreatment or after-treatment of workpieces
- C25D5/67—Electroplating to repair workpiece
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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
- C25D7/00—Electroplating characterised by the article coated
Abstract
The invention relates to the field of hydraulic actuating cylinders, in particular to a method for repairing serious corrosion of a piston rod base body and a chromium layer of an airplane actuating cylinder, which comprises the following specific steps: s1, checking and representing corrosion defects; s2, determining the corrosion morphology; s3, measuring the size before recovery; s4, removing chromium from the piston rod; s5, grinding and repairing the piston rod; s6, measuring the size after grinding and repairing; s7, removing corrosive foreign matters; s8, laser cladding repair; s9, grinding and repairing to remove welding high points; s10, performing low-temperature tempering for the first time; s11, carrying out primary magnetic powder inspection; s12, flattening the diamond for the first time; s13, thickening and plating chromium; s14, grinding and repairing to restore the size; s15, tempering at low temperature for the second time; s16, magnetic secondary powder flaw detection; s17, flattening the diamond for the second time; s18, testing and verifying; s19, final inspection, compared with the prior art, the method has the following improvement points: the surface oxide layer of the corrosion point part is removed by adopting a handheld electric grinder and a carborundum grinding needle, so that the matrix strength of the piston rod is improved.
Description
Technical Field
The invention relates to the field of hydraulic actuating cylinders, in particular to a method for repairing serious corrosion of a piston rod base body and a chromium layer of an airplane actuating cylinder.
Background
The hydraulic actuator cylinder on the airplane is used for controlling the flight attitude of a control surface, the retraction and release of an undercarriage and the retraction and release of a cabin door, after long-time flight use, corrosion points can be generated on a piston rod of the actuator cylinder, a 500-time magnifier is used for detecting that the corrosion depth reaches a base body deeply, and the surface of a chromium layer of the piston rod is a sealing ring matching part, so that the high-pressure sealing performance is ensured, and the hydraulic actuator cylinder cannot be used for stepping down. The original corrosion repairing method only aims at slight scratch of the chromium layer, the slight scratch is removed after the polishing by using oilstone, then the chromium is scraped, and the chromium is plated after the polishing to repair the surface. However, when the corrosion is deep and reaches the matrix, the matrix is polished by using the oilstone to generate pits, the part of the working surface still has deep defects after the chromium is removed, and if the chromium is directly plated, the pits still exist at the defect positions after the chromium plating because the thickness of the single-side chromium plating is not more than 0.2mm, the sealing effect cannot be realized. In addition, the replacement cost of the piston rod of the actuating cylinder product on the airplane is high, the piston rod is difficult to purchase, the scrapping of a single piece can cause scrapping of a whole set of actuating cylinders, the economic loss is high, damage remanufacturing and repairing are carried out, and the repairing strength and the chromium layer bonding force are evaluated and characterized to ensure the repairing feasibility and the reliability. Therefore, in order to solve the problem of lack of parts of equipment, improve the production efficiency and save the repair cost, a method for repairing the deep corrosion of the piston rod of the aircraft actuator cylinder needs to be researched.
For example, in the laser welding repair method of the piston rod with the Chinese patent number of 201010594584.1, the repair method mainly comprises the steps of removing the base metal layer by lathe turning, then using a laser welding layer as a surface layer, and then machining to a specified size, but the repair method can reduce the strength of the base body of the piston rod and is not suitable for repairing the piston rod of the aircraft actuator cylinder.
Disclosure of Invention
In order to solve the problems, the invention provides a method for repairing serious corrosion of a piston rod base body and a chromium layer of an airplane actuator cylinder.
A method for repairing serious corrosion of a piston rod substrate and a chromium layer of an airplane actuator cylinder comprises the following specific steps:
s1, checking and representing corrosion defects;
s2, determining the corrosion morphology;
s3, measuring the size before recovery;
s4, removing chromium from the piston rod;
s5, grinding and repairing a piston rod: a rotating center tool is used for positioning, grinding and repairing are carried out according to a grinding mode before plating, and grinding and repairing are not carried out on a deep corrosion part; grinding and repairing the outer circle of the outer cylinder by a grinding and repairing process method in a matching way, so that scratches and corrosion point traces are eliminated, and the single side of the grinding and repairing size is controlled within 0.15 mm;
s6, size measurement after grinding and repairing: measuring the inner diameter sizes of the matching surface of the piston rod and the matching part of the outer cylinder by adopting an outer micrometer, and recording measurement data;
s7, removing corrosive foreign matters: removing corrosion substances from the corrosion points by using a handheld electric grinder and a diamond sanding machine, and cleaning the surface by using acetone;
s8, laser cladding repair: the method comprises the following steps of utilizing a laser cladding welding mode to polish and build up weld the corrosion, recovering the size of a defect position by adopting a 600-micron laser fiber laser powder filling repair method, and reserving a machining allowance of about 0.5 mm;
s9, grinding and repairing to remove welding high points: after the welding high points of the piston rod are removed in a grinding mode, grinding and repairing are carried out according to the recorded data in the step S3, and the grinding and repairing control size is used for ensuring that the strength of the piston rod base body is not reduced and the corroded part is filled and leveled;
s10, first low-temperature tempering: stress relief heat treatment is carried out on the piston rod, stress relief low-temperature tempering is carried out, the temperature is 180-200 ℃, and the time t is more than or equal to 4 hours;
s11, magnetic particle inspection for the first time: the magnetic particle inspection detection technology is adopted to inspect the laser repair area, and no crack or unfused defect is required;
s12, flattening the diamond for the first time: diamond flattening is carried out on the grinding surface;
s13, thickening and chromium plating: thickening and chromium plating the grinding surface, wherein the thickness delta of a chromium plating layer of a piston rod of the actuating cylinder is less than or equal to 0.20mm;
s14, grinding and repairing to recover the size: grinding and repairing the size of the part by using a rotating center tool according to the design pattern or the assembly requirement of the piston rod, and recovering the size and the surface roughness of the part;
s15, secondary low-temperature tempering: stress relief treatment is carried out on the piston rod after grinding and repairing, the low-temperature tempering temperature is 180-200 ℃, and t is more than or equal to 4 hours;
s16, magnetic particle inspection for the second time: the chromium-plated surface of the piston rod is inspected by a magnetic powder inspection method, no surface crack is required, and the size of a processed part is inspected to meet the requirement of a drawing;
s17, second diamond flattening: diamond flattening is carried out on the grinding surface;
s18, test verification: the repaired piston rod was assembled into the ram and tested as follows:
a. running-in test: two connecting pipe nozzles of the actuating cylinder are respectively connected with a supply pipeline and an exhaust pipeline of a test bed, hydraulic pressure of 9.8 +/-1.96 MPa is supplied, the piston rod is subjected to 50 times of reciprocating circulation under the condition of no load, and the piston rod is rotated for 90 degrees after 25 times of circulation;
b. and (3) performance test: respectively extending the filler neck from the piston rod to pressurize and retracting the filler neck from the piston rod to pressurize for pressure observation;
and S19, final inspection.
The specific process conditions of the chromium stripping in the step S4 are as follows: and (3) removing chromium from the piston rod at room temperature by using industrial-grade sodium hydroxide with the content of 80-150g/L, and removing the chromium to a steel plate state.
And S5, grinding and repairing process parameters:
the rotating speed of the grinding wheel is as follows: 36m/s;
piston rod rotational speed: 50r/min;
feeding speed: 0.3m/min;
radial feed per week: less than or equal to 0.01mm.
In the step S8, the thickness of the laser cladding single layer is less than 1.0mm, the temperature rise of the cylinder body is controlled within 150 ℃, and a contact temperature measuring instrument is adopted for measuring the temperature.
The laser cladding process parameters in the step S8 are specifically as follows:
power: 400W-600W;
speed: 500 mm/min-700 mm/min;
powder feeding speed: 3.5 r/min-25.0 r/min;
gun head shielding gas: 15L/min;
powder loading gas: 5L/min.
The grinding parameters in the step S9 are as follows:
the rotating speed of the grinding wheel is as follows: 36m/s;
rotating speed of the piston rod: 50r/min;
feeding speed: 0.3m/min;
radial feed per week: less than or equal to 0.01mm.
The specific process parameters of diamond flattening in the step S12 are as follows:
rotating speed of the piston rod: 300r/min;
longitudinal feeding: 0.05mm/r;
pressing force: (150-2) kgf [ (1500-20) N ].
The specific process parameters of diamond flattening in the step S17 are as follows:
piston rod rotational speed: 300r/min;
longitudinal feeding: 0.05mm/r;
pressing force: (150-2) kgf [ (1500-20) N ].
In step S18, the running-in test requires that the piston rod assembly moves smoothly without shaking and jamming during running-in, the fixed seal allows droplets that are invisible to the naked eye but can be found by filter paper, and the movable seal allows accumulation that is visible to the naked eye but does not drop.
In the step (S18), the filler neck is extended out from the piston rod to pressurize, the minimum pressure required by the movement of the piston rod is 0.0196-0.98 MPa, and the pressure change is not more than 0.196MPa; the filler neck is withdrawn from the piston rod to pressurize, the minimum pressure required by the movement of the piston rod is 0.0196-2.45 MPa, and the pressure change is not more than 0.98MPa.
The beneficial effects of the invention are: compared with the prior art, the invention has the following improvement points: the invention adopts the hand-held sander and the carborundum grinding needle to remove the surface oxide layer of the corrosion point part, thereby ensuring the strength of the matrix; the invention removes the welding high points through laser cladding repair and regrinding, improves the matrix strength of the piston rod, and effectively controls the reliability of the corrosion repair technology.
Drawings
The invention is further illustrated by the following examples in conjunction with the drawings.
FIG. 1 is a schematic view of a flow structure of the present invention;
fig. 2 is a schematic structural diagram of the piston rod of the present invention.
Detailed Description
The present invention will be further described in order to make the technical means, the creation characteristics, the achievement purposes and the effects of the present invention easy to understand.
As shown in fig. 1 and fig. 2, a method for repairing severe corrosion of a piston rod substrate and a chromium layer of an aircraft actuator cylinder specifically comprises the following steps:
s1, checking and representing corrosion defects;
s2, determining the corrosion morphology;
s3, measuring the size before recovery;
s4, removing chromium from the piston rod;
s5, grinding and repairing a piston rod: a rotating center tool is used for positioning, grinding and repairing are carried out according to a grinding mode before plating, and grinding and repairing are not carried out on a deep corrosion part; grinding and repairing the outer circle of the outer cylinder by using a grinding and repairing process method in a matching way, eliminating scratches and corrosion point traces, and controlling the grinding and repairing size within 0.15mm on one side;
s6, measuring the size after grinding and repairing: measuring the inner diameter sizes of the matching surface of the piston rod and the matching part of the outer cylinder by adopting an outer micrometer, and recording measurement data;
s7, removing corrosive foreign matters: removing corrosion substances from the corrosion points by using a handheld electric grinder and a diamond sanding machine, and cleaning the surface by using acetone;
s8, laser cladding repair: the method comprises the following steps of utilizing a laser cladding welding mode to polish and build up weld the corrosion, recovering the size of a defect position by adopting a 600-micron laser fiber laser powder filling repair method, and reserving a machining allowance of about 0.5 mm;
s9, grinding and repairing to remove welding high points: after the welding high points of the piston rod are removed in a grinding mode, grinding and repairing are carried out according to the recorded data in the step S3, and the grinding and repairing control size is used for ensuring that the strength of the piston rod base body is not reduced and the corroded part is filled and leveled;
s10, first low-temperature tempering: stress relief heat treatment is carried out on the piston rod, stress relief low-temperature tempering is carried out, the temperature is 180-200 ℃, and the time t is more than or equal to 4 hours;
s11, magnetic particle inspection for the first time: the magnetic particle inspection detection technology is adopted to inspect the laser repair area, and no crack or unfused defect is required;
s12, flattening the diamond for the first time: diamond flattening is carried out on the grinding and trimming surface;
s13, thickening and chromium plating: thickening and chrome-plating the grinding surface, wherein the thickness delta of the chrome-plating layer of the piston rod of the actuating cylinder is less than or equal to 0.20mm;
s14, grinding and repairing to restore the size: grinding and repairing the size of the part by using a rotating center tool according to the design pattern or the assembly requirement of the piston rod, and recovering the size and the surface roughness of the part;
s15, secondary low-temperature tempering: stress relieving treatment is carried out on the piston rod after grinding and repairing, the low-temperature tempering temperature is 180-200 ℃, and t is more than or equal to 4 hours;
s16, magnetic particle inspection for the second time: the chromium-plated surface of the piston rod is inspected by a magnetic powder inspection method, no surface crack is required, the size of a processed part is inspected, and the requirement meets the requirement of a drawing;
s17, flattening the diamond for the second time: diamond flattening is carried out on the grinding surface;
s18, test verification: the repaired piston rod was assembled into the actuator cylinder and tested as follows:
a. running-in test: two connecting pipe nozzles of the actuating cylinder are respectively connected with a supply pipeline and an exhaust pipeline of a test bed, hydraulic pressure of 9.8 +/-1.96 MPa is supplied, the piston rod is subjected to 50 times of reciprocating circulation under the condition of no load, and after 25 times of circulation, the piston rod is rotated by 90 degrees, and the piston rod can move stably without impulse and clamping stagnation;
b. performance test: respectively extending the filler neck from the piston rod to pressurize and retracting the filler neck from the piston rod to pressurize for pressure observation;
and S19, final inspection.
The corrosion repairing method for the piston rod successfully solves the problem that parts such as the piston rod of the airplane actuator cylinder are deep in local corrosion and cannot be repaired, ensures that the strength and the sealing property of the repaired piston rod are not reduced, and fills up the blank of the technology for repairing the piston rod of the airplane actuator cylinder; by successfully repairing the corrosion defects of the piston rods of the multiple airplane actuator cylinders, the method effectively solves the problem of part shortage of equipment, improves the production efficiency and saves the repair cost.
The specific process conditions of the chromium stripping in the step S4 are as follows: the piston rod is subjected to chromium stripping at room temperature by using 80-150g/L industrial sodium hydroxide, and the chromium stripping is in a steel plate state, and the specific requirements are as shown in the following table 1:
TABLE 1 alkaline chromium stripping solution composition, content and technological conditions for steel parts
And in the step S5, the grinding and repairing tool adopts a handheld grinding machine and a carborundum grinding needle to remove an oxide layer on the surface of the corrosion point part, so that the strength of the matrix is ensured.
And S5, grinding and repairing process parameters:
the rotating speed of the grinding wheel is as follows: 36m/s;
piston rod rotational speed: 50r/min;
feeding speed: 0.3m/min;
weekly radial feed: less than or equal to 0.01mm.
In the step S8, the thickness of the laser cladding single layer is less than 1.0mm, the temperature rise of the cylinder body is controlled within 150 ℃, and a contact temperature measuring instrument is adopted for measuring the temperature.
The laser cladding process parameters in the step S8 are specifically as follows:
power: 400W-600W;
speed: 500 mm/min-700 mm/min;
powder feeding speed: 3.5 r/min-25.0 r/min;
gun head protection gas: 15L/min;
powder loading gas: 5L/min.
The grinding parameters in the step S9 are as follows:
the rotating speed of the grinding wheel is as follows: 36m/s;
rotating speed of the piston rod: 50r/min;
feeding speed: 0.3m/min;
radial feed per week: less than or equal to 0.01mm.
The specific process parameters of diamond flattening in the step S12 are as follows:
rotating speed of the piston rod: 300r/min;
longitudinal feeding: 0.05mm/r;
pressing force: (150-2) kgf [ (1500-20) N ].
The specific process parameters of the thickening chromium plating in the step S13 are shown in the table 2:
TABLE 2 chromium plating solution composition, content and Process conditions
The specific process parameters of diamond flattening in the step S17 are as follows:
piston rod rotational speed: 300r/min;
longitudinal feeding: 0.05mm/r;
pressing force: (150-2) kgf [ (1500-20) N ].
In step S18, the running-in test requires that the piston rod assembly moves smoothly without shaking and jamming during running-in, the fixed seal allows droplets that are invisible to the naked eye but can be found by filter paper, and the movable seal allows accumulation that is visible to the naked eye but does not drop.
In the step (S18), the filler neck is extended out from the piston rod to pressurize, the minimum pressure required by the movement of the piston rod is 0.0196-0.98 MPa, and the pressure change is not more than 0.196MPa; the filler neck is withdrawn from the piston rod to pressurize, the minimum pressure required by the movement of the piston rod is 0.0196-2.45 MPa, and the pressure change is not more than 0.98MPa.
Compared with the prior art, the invention has the following improvement points: the invention adopts the hand-held electric grinder and the carborundum grinding needle to remove the surface oxide layer of the corrosion point part, thereby ensuring the strength of the matrix; the invention removes the welding high points through laser cladding repair and regrinding, improves the matrix strength of the piston rod, and effectively controls the reliability of the corrosion repair technology.
The foregoing shows and describes the general principles, principal 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 (10)
1. A method for repairing serious corrosion of a piston rod substrate and a chromium layer of an airplane actuator cylinder is characterized by comprising the following steps: the method comprises the following specific steps:
s1, checking and representing corrosion defects;
s2, determining the corrosion morphology;
s3, measuring the size before recovery;
s4, removing chromium from the piston rod;
s5, grinding and repairing a piston rod: a rotating center tool is used for positioning, grinding and repairing are carried out according to a grinding mode before plating, and grinding and repairing are not carried out on a deep corrosion part; grinding and repairing the outer circle of the outer cylinder by a grinding and repairing process method in a matching way, so that scratches and corrosion point traces are eliminated, and the single side of the grinding and repairing size is controlled within 0.15 mm;
s6, size measurement after grinding and repairing: measuring the inner diameter sizes of the matching surface of the piston rod and the matching part of the outer cylinder by adopting an outer micrometer, and recording measurement data;
s7, removing corrosive foreign matters: removing corrosive substances from the corrosion points by using a special electric grinding gun, and cleaning the surface by using acetone;
s8, laser cladding repair: the method comprises the following steps of (1) utilizing a laser cladding welding mode to polish and build up weld the corrosion, recovering the size of a defect position by adopting a 600-micron laser fiber laser and powder filling repair method, and reserving a machining allowance of about 0.5 mm;
s9, grinding and repairing to remove welding high points: after the welding high points of the piston rod are removed in a grinding mode, grinding and repairing are carried out according to the recorded data in the step S3, and the grinding and repairing control size is used for ensuring that the strength of the piston rod base body is not reduced and the corroded part is filled and leveled;
s10, first low-temperature tempering: stress relief heat treatment is carried out on the piston rod, stress relief low-temperature tempering is carried out, the temperature is 180-200 ℃, and the time t is more than or equal to 4h;
s11, magnetic particle inspection for the first time: the magnetic particle inspection detection technology is adopted to inspect the laser repair area, and no crack or unfused defect is required;
s12, first diamond flattening: diamond flattening is carried out on the grinding surface;
s13, thickening and chromium plating: thickening and chromium plating the grinding surface, wherein the thickness delta of a chromium plating layer of a piston rod of the actuating cylinder is less than or equal to 0.20mm;
s14, grinding and repairing to restore the size: grinding and repairing the size of the part by using a rotating center tool according to the design pattern or the assembly requirement of the piston rod, and recovering the size and the surface roughness of the part;
s15, secondary low-temperature tempering: stress relief treatment is carried out on the piston rod after grinding and repairing, the low-temperature tempering temperature is 180-200 ℃, and t is more than or equal to 4 hours;
s16, magnetic particle inspection for the second time: the chromium-plated surface of the piston rod is inspected by a magnetic powder inspection method, no surface crack is required, the size of a processed part is inspected, and the requirement meets the requirement of a drawing;
s17, flattening the diamond for the second time: diamond flattening is carried out on the grinding surface;
s18, test verification: the repaired piston rod was assembled into the actuator cylinder and tested as follows:
a. running-in test: two connecting pipe mouths of the actuating cylinder are respectively connected with a supply pipeline and an exhaust pipeline of the test bed, hydraulic pressure of 9.8 +/-1.96 MPa is supplied, 50 times of reciprocating circulation are carried out on the piston rod under the condition of no load, and the piston rod is rotated for 90 degrees after 25 times of circulation;
b. performance test: respectively extending the filler neck from the piston rod to pressurize and retracting the filler neck from the piston rod to pressurize for pressure observation;
and S19, final inspection.
2. The method for repairing severe corrosion of a base and a chromium layer of a piston rod of an aircraft actuator cylinder according to claim 1, wherein the method comprises the following steps: the specific process conditions of the chromium stripping in the step S4 are as follows: and (3) removing chromium from the piston rod at room temperature by using industrial-grade sodium hydroxide with the content of 80-150g/L, and removing the chromium to a steel plate state.
3. The method for repairing severe corrosion of a base body and a chromium layer of a piston rod of an aircraft actuator cylinder according to claim 1, wherein the method comprises the following steps: the step S5 comprises the following grinding process parameters:
the rotating speed of the grinding wheel is as follows: 36m/s;
piston rod rotational speed: 50r/min;
feeding speed: 0.3m/min;
radial feed per week: less than or equal to 0.01mm.
4. The method for repairing severe corrosion of a base body and a chromium layer of a piston rod of an aircraft actuator cylinder according to claim 1, wherein the method comprises the following steps: in the step S8, the thickness of the laser cladding single layer is less than 1.0mm, the temperature rise of the cylinder body is controlled within 150 ℃, and a contact temperature measuring instrument is adopted for measuring the temperature.
5. The method for repairing severe corrosion of a base body and a chromium layer of a piston rod of an aircraft actuator cylinder according to claim 1, wherein the method comprises the following steps: the laser cladding process parameters in the step S8 are specifically as follows:
power: 400W-600W;
speed: 500 mm/min-700 mm/min;
powder feeding speed: 3.5 r/min-25.0 r/min;
gun head protection gas: 15L/min;
powder loading gas: 5L/min.
6. The method for repairing severe corrosion of a base body and a chromium layer of a piston rod of an aircraft actuator cylinder according to claim 1, wherein the method comprises the following steps: the process parameters of the grinding and repairing in the step S9 are specifically as follows:
the rotating speed of the grinding wheel is as follows: 36m/s;
rotating speed of the piston rod: 50r/min;
feeding speed: 0.3m/min;
radial feed per week: less than or equal to 0.01mm.
7. The method for repairing severe corrosion of a base and a chromium layer of a piston rod of an aircraft actuator cylinder according to claim 1, wherein the method comprises the following steps: the specific process parameters of diamond flattening in the step S12 are as follows:
rotating speed of the piston rod: 300r/min;
longitudinal feeding: 0.05mm/r;
pressing force: (150-2) kgf [ (1500-20) N ].
8. The method for repairing severe corrosion of a base body and a chromium layer of a piston rod of an aircraft actuator cylinder according to claim 1, wherein the method comprises the following steps: the specific process parameters of diamond flattening in the step S17 are as follows:
piston rod rotational speed: 300r/min;
longitudinal feeding: 0.05mm/r;
pressing force: (150-2) kgf [ (1500-20) N ].
9. The method for repairing severe corrosion of a base and a chromium layer of a piston rod of an aircraft actuator cylinder according to claim 1, wherein the method comprises the following steps: in step S18, the running-in test requires that the piston rod assembly moves smoothly without shaking and jamming during running-in, the fixed seal allows droplets that are invisible to the naked eye but can be found by filter paper, and the movable seal allows accumulation that is visible to the naked eye but does not drop.
10. The method for repairing severe corrosion of a base and a chromium layer of a piston rod of an aircraft actuator cylinder according to claim 1, wherein the method comprises the following steps: in the step (S18), the filler neck is extended out from the piston rod to pressurize, the minimum pressure required by the movement of the piston rod is 0.0196-0.98 MPa, and the pressure change is not more than 0.196MPa; the filler neck is withdrawn from the piston rod to pressurize, the minimum pressure required by the movement of the piston rod is 0.0196-2.45 MPa, and the pressure change is not more than 0.98MPa.
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