CN111996523A - Deformation-preventing repair method for thin-wall shell of aircraft control handle - Google Patents
Deformation-preventing repair method for thin-wall shell of aircraft control handle Download PDFInfo
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- CN111996523A CN111996523A CN202010682301.2A CN202010682301A CN111996523A CN 111996523 A CN111996523 A CN 111996523A CN 202010682301 A CN202010682301 A CN 202010682301A CN 111996523 A CN111996523 A CN 111996523A
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- 239000011248 coating agent Substances 0.000 claims abstract description 30
- 238000000576 coating method Methods 0.000 claims abstract description 30
- 238000010288 cold spraying Methods 0.000 claims abstract description 17
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- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 6
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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
-
- 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
- B24B1/00—Processes of grinding or polishing; Use of auxiliary equipment in connection with such processes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
- B24C1/06—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for producing matt surfaces, e.g. on plastic materials, on glass
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The invention relates to an anti-deformation repairing method for a thin-wall shell of an aircraft control handle, which comprises the following specific steps: various electrical components, switches and wires arranged in the thin-wall shell of the control handle are taken out, redundant structures which are not repaired are removed, and the damaged handle shell is reserved; and sequentially removing a surface paint layer and a sulfuric acid anodized layer from the damaged part on the thin-wall shell of the control handle, polishing defects, and manufacturing the polished damaged part into a U-shaped groove convenient to spray. The invention provides a low-temperature open-fire-free cold spraying technology, which can realize the deformation-prevention repair of the aluminum alloy thin-wall shell at a lower temperature, effectively solves the problems that the traditional welding repair process has large heat input, causes the deformation of the shell to influence the installation, causes the thermal damage of an external coating 5860 sizing material and the like, reduces the generation of secondary repair defects, improves the repair qualification rate and the repair reliability, and has obvious repair effect.
Description
Technical Field
The invention relates to the technical field of aircraft part accessory repair, in particular to an anti-deformation repairing method for a thin-wall shell of an aircraft control handle.
Background
The shell of the airplane control handle is integrally formed by adopting a casting process, the wall thickness of the shell is 3mm, the shell is made of cast aluminum ZL101A, the holding part of the handle is covered by adopting rubber 5860HG6-407-79, various cables and electric components are arranged in the shell, the shell is used for providing protection and supporting various components to be installed, and the requirement on shape and position precision is high. The control handle is an important component of an aircraft control system for operating the aircraft and performing predetermined control functions. Because the main body material of the handle is cast aluminum, the strength and the hardness are not high, and the handle is easy to be damaged by knocking, abrasion or even cracks at the positions of a threaded hole, a mounting hole, a positioning pin and the like in the daily use and regular maintenance process of an airplane, so that the operation and use reliability of the handle is influenced, and the damage needs to be repaired.
For the damage repair, a welding repair method is generally adopted at present, but for the thin-wall shell, the following problems mainly exist by adopting the conventional repair method: firstly, the wall thickness of the shell is only 3mm, the welding heat input is large, the shell is easy to deform under heat, and the mounting and positioning precision of internal components is influenced; secondly, the rubber material 5860 covered on the handle holding part is normal temperature nitrile rubber, is pressed and formed, cannot be decomposed during repair, has the maximum use temperature not exceeding 100 ℃, and is easy to cause rubber material damage and generate repair secondary defects if the defects are repaired and welded by a conventional method.
Disclosure of Invention
Aiming at the damages such as gouges, abrasion, cracks and the like of the thin-wall shell of the airplane control handle, the invention provides the deformation-preventing repair method of the thin-wall shell of the airplane control handle, which utilizes a low-temperature cold spraying technology without open fire to control the repair temperature to be below 100 ℃, realizes the low-temperature repair of the control handle, avoids the deformation of parts and the heating damage of rubber materials, reduces the generation of the secondary repair defects, and improves the repair qualification rate and the repair reliability.
The technical problem to be solved by the invention is realized by adopting the following technical scheme:
an anti-deformation repairing method for a thin-wall shell of an aircraft control handle comprises the following specific steps:
taking out various electrical components, switches and wires arranged in the thin-wall shell of the control handle, removing redundant structures which are not repaired, and reserving the damaged handle shell;
sequentially removing a surface paint layer and a sulfuric acid anodized layer from the damaged part on the thin-wall shell of the control handle, polishing the defects, and manufacturing the polished damaged part into a U-shaped groove convenient to spray;
thirdly, shielding and protecting a non-spraying area and an internal cavity on the thin-wall shell of the control handle, cleaning the damage to be sprayed by absolute ethyl alcohol, and wiping and drying;
fourthly, carrying out surface sand blasting and texturing pretreatment on the to-be-sprayed damage part by adopting 46-mesh brown corundum sand;
within 2h after the sand blasting pretreatment, cold spraying material increase is carried out on the damage to be sprayed by using cold spraying equipment;
processing and finishing the coating at the damaged part on the thin-wall shell of the control handle after spraying according to the pattern requirement;
(VII) performing dye penetrant inspection on the repaired damage position on the thin-wall shell of the control handle, checking whether the defect is existed in the damage position on the thin-wall shell of the control handle and the transition area around the damage position, if the defect is existed, performing reworking repeatedly to perform the steps (two) to (six) until the defect is detected;
cleaning, wiping, drying and visually inspecting the damage position on the trimmed thin-wall shell of the control handle, and painting two layers of polyurethane primer and one layer of gray matt enamel paint on the damage position on the trimmed thin-wall shell of the control handle for surface treatment;
(ninthly) recovering the installation of the operating handle, and checking whether the insulation resistance between the operating handle shell and the internal electronic components is less than 20M omega by using a 500V megohmmeter under the environment that the humidity is not more than 70%;
if the insulation resistance of the lead wire is less than 20 MOmega, the operating handle is disassembled, whether the surface states of the interior of the shell, the lead wire and the electronic component are damaged or not and residual metal scraps are visually checked, and whether the insulation resistance of the lead wire reaches the qualified standard of 20 MOmega or not is detected;
and (eleventh) if the problem in the step (ten) does not exist, repeating the step (nine) until the insulation resistance between the shell of the operating handle and the internal electronic component is not less than 20M omega, and if the problem in the step (ten) exists, correspondingly clearing residual metal chips and replacing the lead, and then repeating the step (nine) until the insulation resistance between the shell of the operating handle and the internal electronic component is not less than 20M omega.
Further, the specific process of removing the paint layer and the sulfuric acid anodized layer on the surface of the damaged part in the step (II) is as follows: firstly, roughly polishing by using 80-120-mesh abrasive paper, then finely polishing by using 320-mesh abrasive paper until no paint layer or golden yellow oxide layer is formed at the damaged part and the metal luster of the matrix is exposed.
Further, the polishing of the defects at the damaged part in the step (II) comprises the polishing of corrosion defects, the polishing of crack defects, the polishing of gouge defects and the polishing of abrasion defects, wherein the defects need to be completely removed by the corrosion defects and the crack defects, and the polishing of the gouge defects and the abrasion defects only need to level peripheral burrs and uneven areas.
Further, the process parameters during the cold spraying of the damage part in the step (five) are as follows:
(a) coating materials: mixing Al + Al2O3 mixed powder by a mechanical method, wherein the content of Al2O3 is 20-30%, and the particle size of the powder is 5-45 μm;
(b) spraying carrier gas: 99.99% nitrogen;
(c) spraying distance: 15-25 mm;
(d) pressure of the spray gun: 200-220 psi;
(e) heating temperature: 300-350 ℃;
(f) powder feeding amount: 30-40 g/min.
Further, the concrete process of the cold spraying of the damage part in the step (five) is as follows:
(A) spraying the damaged part on the thin-wall shell of the control handle in a control mode that the thickness of a single layer is not more than 0.1mm and spraying is stopped for 2-3 min when every two layers are deposited, and cooling by using compressed air in the spraying process;
(B) when the temperature of the damage part on the thin-wall shell of the control handle is overhigh, the spraying stopping time is prolonged, and the spraying stopping time for one time cannot exceed 10 min;
(C) monitoring the temperature of the sprayed damage part and controlling the temperature below 100 ℃;
(D) and reserving 1-2 mm of coating machining allowance according to machining requirements.
Further, the specific process of processing and finishing the coating at the damage part after spraying in the step (six) is as follows:
(S1) according to the pattern requirement of the shell, re-drilling a threaded hole and a mounting hole in the sprayed damage coating, and tapping by using a screw tap;
(S2) carrying out rough grinding and shape finishing on the positioning pin part on the coating at the sprayed damage part by using an electric grinding tool;
(S3) when polishing, firstly, starting with a coating high point, and when processing is carried out quickly to meet the requirements of the shell pattern, manually polishing and finishing the size and the roughness;
(S4) the polished coating on the sprayed damage part should be smooth and have no edges and corners, and the roughness of the repaired part is not inferior to Ra3.2 mu m.
The invention has the beneficial effects that:
compared with the prior art, the cold spraying technology with low temperature and no open fire provided by the invention can realize deformation-prevention repair of the aluminum alloy thin-wall shell at lower temperature, effectively solves the problems that the traditional welding repair technology has large heat input, the shell deforms to influence installation, the external coating 5860 rubber is heated to be damaged and the like, reduces the generation of secondary repair defects, improves the repair qualification rate and the repair reliability, and has obvious repair effect.
Drawings
The invention is further illustrated with reference to the following figures and examples:
FIG. 1 is a first schematic structural view of an aircraft control handle according to the present invention;
fig. 2 is a schematic structural diagram of an aircraft control handle according to the invention.
In the figure: 1. a handle housing; 2. 5860 rubber material coated on the handle shell; 3. the shell is provided with a threaded hole and a mounting hole which are easy to damage; 4. and the positioning pin hole is easy to damage on the shell.
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.
Referring to fig. 1 and 2, the aircraft control handle to be repaired according to the present invention is mainly repaired at the locations of reference numeral 3 (i.e., vulnerable threaded holes and mounting holes on the housing) and reference numeral 4 (i.e., vulnerable positioning pin holes on the housing) in fig. 1 and 2.
An anti-deformation repairing method for a thin-wall shell of an aircraft control handle comprises the following specific steps:
and (I) taking out various electrical components, switches and wires arranged in the thin-wall shell of the control handle, removing redundant structures which are not repaired, and keeping the damaged handle shell 1.
And (II) removing a surface paint layer and a sulfuric acid anodized layer from the damaged part on the thin-wall shell of the control handle, polishing the defects, and manufacturing the polished damaged part into a U-shaped groove convenient to spray.
Specifically, the process for removing the paint layer and the sulfuric acid anodized layer on the surface of the damaged part on the thin-wall shell of the control handle comprises the following steps: firstly, roughly polishing by using 80-120-mesh abrasive paper, then finely polishing by using 320-mesh abrasive paper until no paint layer or golden yellow oxide layer is formed at the damaged part and the metal luster of the matrix is exposed. Care should be taken during the sanding process to protect the 5860 glue 2 coating the handle shell.
And then, the defect polishing on the thin-wall shell of the control handle comprises corrosion defect polishing, crack defect polishing, gouging defect polishing and abrasion defect polishing, wherein the corrosion defect and the crack defect need to be completely removed, and the gouging defect polishing and the abrasion defect only need to flatten peripheral burrs and uneven areas. After polishing the defects, smooth transition of the polished damaged part and the non-damaged part is ensured to avoid stress concentration.
And finally, the polished damage part is made into a U-shaped groove so as to facilitate subsequent cold spraying and improve the combination effect of the coating and the base material.
And thirdly, shielding and protecting a non-spraying area and an internal cavity on the thin-wall shell of the control handle, cleaning the to-be-sprayed damage part by using absolute ethyl alcohol, and wiping and drying.
Specifically, the shielding adhesive tape is adopted to protect positions such as a non-spraying area and an internal cavity on the thin-wall shell of the control handle, and key protection is carried out on the installation position of an internal electronic component, so that short circuit risk caused by metal dust which is not deposited in the subsequent cold spraying process and enters the thin-wall shell of the control handle is avoided.
The thin-wall shell of the control handle is wiped by clean and fluffy cotton cloth and is dried by clean and dry compressed air, and the part to be sprayed and damaged on the thin-wall shell of the control handle in the step of the invention is not suitable to be cleaned by acetone, because the rubber material 5860 belongs to nitrile rubber, and is easy to swell due to improper protection.
And (IV) carrying out surface sand blasting and texturing pretreatment on the to-be-sprayed damage part by adopting 46-mesh brown corundum sand.
Specifically, the 46-mesh brown corundum sand for sand blasting is dry, free of oil stains and other impurities, uniform in sand blasting, and the retention time of a sand blasting gun on a to-be-sprayed damage part is not allowed to exceed 15 s. After sand blasting, the sand blasting area is required to completely cover the surface of the to-be-sprayed damage, the surface of the to-be-sprayed damage after sand blasting is rough, uniform, dull and dark, and the residual sand grains are blown away by clean and dry compressed air after the sand blasting is finished.
And (V) performing cold spraying material increase on the to-be-sprayed damage part by using cold spraying equipment within 2h after the sand blasting pretreatment.
Specifically, in order to avoid the substrate after pretreatment from being polluted and oxidized again (the aluminum alloy has high activity and is easy to generate an oxide film in the air), the interval time between spraying and pretreatment is not more than 2 h.
The technological parameters when cold spraying is carried out on the damage to be sprayed by using the cold spraying equipment are as follows:
(a) coating materials: mixing Al + Al2O3 mixed powder by a mechanical method, wherein the content of Al2O3 is 20-30%, and the particle size of the powder is 5-45 μm;
(b) spraying carrier gas: 99.99% nitrogen;
(c) spraying distance: 15-25 mm;
(d) pressure of the spray gun: 200-220 psi;
(e) heating temperature: 300-350 ℃;
(f) powder feeding amount: 30-40 g/min.
The spraying process comprises the following steps: in order to control the temperature of the part matrix in the whole repairing process to be below 100 ℃, the preheating temperature before spraying is not too high, namely 40 ℃; during actual spraying, the moving speed of a spray gun is increased, the single deposition thickness is reduced, the single layer thickness is controlled not to exceed 0.1mm, the spray gun is stopped for 2-3 min when 2 layers of the spray gun are deposited, the spray gun is cooled by compressed air, spraying can be carried out again when the base body is cooled to about 40 ℃, if the temperature of the base body of a part is too high, the gun stopping cooling time can be properly prolonged, but the single gun stopping time does not exceed 10min, and the repair is completed after the spray gun is repeatedly carried out for multiple times until the required coating thickness is reached. The temperature of a part substrate is monitored and controlled below 100 ℃ in the whole spraying process, and 1-2 mm coating machining allowance is reserved according to actual machining requirements.
And (VI) processing and finishing the coating at the damaged part on the thin-wall shell of the control handle after spraying according to the pattern requirement.
Specifically, the specific process of processing and finishing the coating at the damage part after spraying is as follows:
(S1) according to the pattern requirement of the shell, re-drilling a threaded hole and a mounting hole in the sprayed damage coating, and tapping by using a screw tap;
(S2) carrying out rough grinding and shape finishing on the positioning pin part on the coating at the sprayed damage part by using an electric grinding tool;
(S3) when polishing, firstly, starting with a coating high point, and when processing is carried out quickly to meet the requirements of the shell pattern, manually polishing and finishing the size and the roughness;
(S4) the polished coating on the sprayed damage part should be smooth and have no edges and corners, and the roughness of the repaired part is not inferior to Ra3.2 mu m.
And (seventhly), performing dye penetrant inspection on the repaired damage position on the thin-wall shell of the control handle, checking whether the defect is existed in the damage position on the thin-wall shell of the control handle and a transition region around the damage position, and if the defect is existed, performing reworking repeatedly to perform the steps from the second step to the sixth step until the defect is detected by the flaw detection.
And (eighthly), cleaning, wiping, drying, visually inspecting the damage position on the trimmed thin-wall shell of the control handle, and painting two layers of polyurethane primer and one layer of gray matt enamel paint on the damage position on the trimmed thin-wall shell of the control handle for surface treatment.
Specifically, the repaired part is cleaned by absolute ethyl alcohol to remove residual metal powder and flaw detection liquid, and is blown clean by clean and dry compressed air, and then the interior of the shell is visually inspected, so that no metal powder and flaw detection liquid are remained.
(ninthly) resuming the installation of the joystick, and checking whether the insulation resistance between the joystick case and the internal electronic components is less than 20M omega by using a 500V megohmmeter under an environment with a humidity of not more than 70%.
And (ten) if the insulation resistance of the lead wire is less than 20 MOmega, disassembling the control handle, visually checking whether the surface states of the inside of the shell, the lead wire and the electronic component are damaged or not and residual metal scraps, and detecting whether the insulation resistance of the lead wire reaches the qualified standard of 20 MOmega or not.
And (eleventh) if the problem in the step (ten) does not exist, repeating the step (nine) until the insulation resistance between the shell of the operating handle and the internal electronic component is not less than 20M omega, and if the problem in the step (ten) exists, correspondingly clearing residual metal chips and replacing the lead, and then repeating the step (nine) until the insulation resistance between the shell of the operating handle and the internal electronic component is not less than 20M omega.
By adopting the process method, the deformation-prevention repair of the aluminum alloy thin-wall shell can be realized at a lower temperature, the problems that the shell is deformed to influence the installation and the external coating 5860 rubber material is damaged by heating and the like due to large heat input in the traditional welding repair process can be effectively avoided, and the repair effect is remarkable.
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 (6)
1. An anti-deformation repairing method for a thin-wall shell of an aircraft control handle is characterized by comprising the following steps: the method comprises the following specific steps:
taking out various electrical components, switches and wires arranged in the thin-wall shell of the control handle, removing redundant structures which are not repaired, and reserving the damaged handle shell;
sequentially removing a surface paint layer and a sulfuric acid anodized layer from the damaged part on the thin-wall shell of the control handle, polishing the defects, and manufacturing the polished damaged part into a U-shaped groove convenient to spray;
thirdly, shielding and protecting a non-spraying area and an internal cavity on the thin-wall shell of the control handle, cleaning the damage to be sprayed by absolute ethyl alcohol, and wiping and drying;
fourthly, carrying out surface sand blasting and texturing pretreatment on the to-be-sprayed damage part by adopting 46-mesh brown corundum sand;
within 2h after the sand blasting pretreatment, cold spraying material increase is carried out on the damage to be sprayed by using cold spraying equipment;
processing and finishing the coating at the damaged part on the thin-wall shell of the control handle after spraying according to the pattern requirement;
(VII) performing dye penetrant inspection on the repaired damage position on the thin-wall shell of the control handle, checking whether the defect is existed in the damage position on the thin-wall shell of the control handle and the transition area around the damage position, if the defect is existed, performing reworking repeatedly to perform the steps (two) to (six) until the defect is detected;
cleaning, wiping, drying and visually inspecting the damage position on the trimmed thin-wall shell of the control handle, and painting two layers of polyurethane primer and one layer of gray matt enamel paint on the damage position on the trimmed thin-wall shell of the control handle for surface treatment;
(ninthly) recovering the installation of the operating handle, and checking whether the insulation resistance between the operating handle shell and the internal electronic components is less than 20M omega by using a 500V megohmmeter under the environment that the humidity is not more than 70%;
if the insulation resistance of the lead wire is less than 20 MOmega, the operating handle is disassembled, whether the surface states of the interior of the shell, the lead wire and the electronic component are damaged or not and residual metal scraps are visually checked, and whether the insulation resistance of the lead wire reaches the qualified standard of 20 MOmega or not is detected;
and (eleventh) if the problem in the step (ten) does not exist, repeating the step (nine) until the insulation resistance between the shell of the operating handle and the internal electronic component is not less than 20M omega, and if the problem in the step (ten) exists, correspondingly clearing residual metal chips and replacing the lead, and then repeating the step (nine) until the insulation resistance between the shell of the operating handle and the internal electronic component is not less than 20M omega.
2. The method for repairing the thin-walled shell of the aircraft control handle in the deformation prevention manner according to claim 1, is characterized in that: the specific process for removing the paint layer and the sulfuric acid anodized layer on the surface of the damaged part in the step (II) is as follows: firstly, roughly polishing by using 80-120-mesh abrasive paper, then finely polishing by using 320-mesh abrasive paper until no paint layer or golden yellow oxide layer is formed at the damaged part and the metal luster of the matrix is exposed.
3. The method for repairing the thin-walled shell of the aircraft control handle in the deformation prevention manner according to claim 1, is characterized in that: and (2) polishing the defects at the damaged part in the step (II), wherein the polishing comprises the polishing of corrosion defects, the polishing of crack defects, the polishing of gouge defects and the polishing of abrasion defects, the defects are completely removed by the corrosion defects and the crack defects, and the polishing of gouge defects and the abrasion defects only need to level peripheral burrs and uneven areas.
4. The method for repairing the thin-walled shell of the aircraft control handle in the deformation prevention manner according to claim 1, is characterized in that: the technological parameters during cold spraying of the damage part in the step (five) are as follows:
(a) coating materials: mixing Al + Al2O3 mixed powder by a mechanical method, wherein the content of Al2O3 is 20-30%, and the particle size of the powder is 5-45 μm;
(b) spraying carrier gas: 99.99% nitrogen;
(c) spraying distance: 15-25 mm;
(d) pressure of the spray gun: 200-220 psi;
(e) heating temperature: 300-350 ℃;
(f) powder feeding amount: 30-40 g/min.
5. The method for repairing the thin-walled shell of the aircraft control handle in the deformation prevention manner according to claim 1, is characterized in that: the concrete process of the cold spraying of the damage part in the step (five) is as follows:
(A) spraying the damaged part on the thin-wall shell of the control handle in a control mode that the thickness of a single layer is not more than 0.1mm and spraying is stopped for 2-3 min when every two layers are deposited, and cooling by using compressed air in the spraying process;
(B) when the temperature of the damage part on the thin-wall shell of the control handle is overhigh, the spraying stopping time is prolonged, and the spraying stopping time for one time cannot exceed 10 min;
(C) monitoring the temperature of the sprayed damage part and controlling the temperature below 100 ℃;
(D) and reserving 1-2 mm of coating machining allowance according to machining requirements.
6. The method for repairing the thin-walled shell of the aircraft control handle in the deformation prevention manner according to claim 1, is characterized in that: the specific process of processing and finishing the sprayed damage coating in the step (six) is as follows:
(S1) according to the pattern requirement of the shell, re-drilling a threaded hole and a mounting hole in the sprayed damage coating, and tapping by using a screw tap;
(S2) carrying out rough grinding and shape finishing on the positioning pin part on the coating at the sprayed damage part by using an electric grinding tool;
(S3) when polishing, firstly, starting with a coating high point, and when processing is carried out quickly to meet the requirements of the shell pattern, manually polishing and finishing the size and the roughness;
(S4) the polished coating on the sprayed damage part should be smooth and have no edges and corners, and the roughness of the repaired part is not inferior to Ra3.2 mu m.
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| CN202010682301.2A CN111996523A (en) | 2020-07-15 | 2020-07-15 | Deformation-preventing repair method for thin-wall shell of aircraft control handle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114182248A (en) * | 2021-10-28 | 2022-03-15 | 国营芜湖机械厂 | Cold spraying repair and protection method for corrosion of hole bottom of flange plate |
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