CN110877006A - Repair process for surface defects of aircraft skin - Google Patents
Repair process for surface defects of aircraft skin Download PDFInfo
- Publication number
- CN110877006A CN110877006A CN201811031563.1A CN201811031563A CN110877006A CN 110877006 A CN110877006 A CN 110877006A CN 201811031563 A CN201811031563 A CN 201811031563A CN 110877006 A CN110877006 A CN 110877006A
- Authority
- CN
- China
- Prior art keywords
- putty
- curing
- repaired
- standing
- surface defects
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007547 defect Effects 0.000 title claims abstract description 31
- 230000008439 repair process Effects 0.000 title claims abstract description 14
- 238000000034 method Methods 0.000 claims abstract description 25
- 229910052751 metal Inorganic materials 0.000 claims abstract description 10
- 239000002184 metal Substances 0.000 claims abstract description 10
- 238000005498 polishing Methods 0.000 claims abstract description 10
- 239000004593 Epoxy Substances 0.000 claims abstract description 9
- 239000011248 coating agent Substances 0.000 claims abstract description 8
- 238000000576 coating method Methods 0.000 claims abstract description 8
- 238000004381 surface treatment Methods 0.000 claims abstract description 7
- 230000001680 brushing effect Effects 0.000 claims abstract description 4
- 238000007493 shaping process Methods 0.000 claims abstract description 4
- 238000002360 preparation method Methods 0.000 claims abstract description 3
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 12
- 238000004140 cleaning Methods 0.000 claims description 12
- 244000137852 Petrea volubilis Species 0.000 claims description 9
- 239000003973 paint Substances 0.000 claims description 9
- 239000002904 solvent Substances 0.000 claims description 9
- 239000002932 luster Substances 0.000 claims description 6
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 9
- 239000011152 fibreglass Substances 0.000 abstract description 4
- 229910000838 Al alloy Inorganic materials 0.000 abstract description 2
- 238000010438 heat treatment Methods 0.000 abstract 1
- 239000000758 substrate Substances 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 6
- 239000002131 composite material Substances 0.000 description 4
- 239000003292 glue Substances 0.000 description 4
- 238000012938 design process Methods 0.000 description 2
- 238000007711 solidification Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D5/00—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
- B05D5/005—Repairing damaged coatings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/02—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by baking
- B05D3/0254—After-treatment
Landscapes
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
A repair process for surface defects of an aircraft skin comprises the following steps: (1) surface treatment of parts, (2) preparation of epoxy putty; (3) coating putty: uniformly brushing or blade-coating the prepared epoxy putty on the to-be-repaired part of the cleaned metal part by using a soft brush or a scraper; (4) and (3) curing: curing the metal part coated with the epoxy putty at room temperature or heating; (5) shaping: and after the putty is cured, polishing the repaired part of the part. The aircraft skin surface defect repairing process can well solve the problem of surface defects of substrates such as aluminum alloy, glass fiber reinforced plastic and the like, is simple and convenient to operate, can effectively avoid the problems of reworking, scrapping and the like of parts, reduces the production cost, shortens the delivery cycle, improves the product quality, and is suitable for popularization and application.
Description
Technical Field
The invention relates to a repair process of surface defects of an aircraft skin, in particular to repair of defects such as pits and step differences of metal parts and poor glue of glass fiber reinforced plastics.
Background
In the field of aeronautical manufacturing, in order to ensure the flight performance of an aircraft, strict requirements are placed on gaps and step differences among parts during the design and manufacturing processes. The assembly process of the prior third generation and the following airplanes adopts a sheet metal riveting process, the sizes of parts of the airplanes are large, the structural shapes and the assembly relationship are complex, and the sheet metal parts are easy to deform and generate pits and the like in the assembly process, so that the gaps and the step differences among the parts assembled by a plurality of parts exceed the design tolerance, the conditions are difficult to solve in the assembly process, the manufacturing quality and the production progress of the airplanes are directly influenced, particularly the involution step differences of the airplane skin are directly influenced if the treatment is not good, and the aerodynamic layout of the airplanes is directly influenced.
In addition, with the increasing use of composite materials in airplanes, higher requirements are put on the performance of the composite materials in the design and manufacturing processes of airplanes, but in the actual production process, due to the complex forming process of the composite materials, different types of manufacturing defects occur more or less, the most common defect is poor glue, but the defect is a non-fatal defect, the problem that parts are scrapped too much due to the defect is solved, and a feasible and effective solution is not provided for the defect.
Disclosure of Invention
In order to effectively solve the problems, the invention provides a process method for repairing the surface of skin defects such as pits, step differences, poor glue of glass fiber reinforced plastics and the like of metal parts by using putty.
A repair process for surface defects of an aircraft skin comprises the following steps: (1) surface treatment of parts: polishing the paint layer of the area to be repaired by using sand paper to remove exposed metallic luster, cleaning the area to be repaired by using gasoline and acetone respectively, and airing for 10-20 minutes each time; (2) preparing putty: taking epoxy putty and a curing agent according to the proportion of 100: 10, fully and uniformly mixing; (3) coating putty: uniformly brushing or blade-coating the prepared putty on the to-be-repaired part of the cleaned metal part by using a soft brush or a scraper; (4) and (3) curing: standing at room temperature for 0.5-1 hour, transferring the putty into an oven after the surface of the putty is dried, and then starting the oven to heat to 50-70 ℃ for baking for 6-10 hours for curing; (5) shaping: and after the putty is cured, polishing the repaired part of the part to a paint spraying state by using sand paper.
Further, the step (4) of the aircraft skin surface defect repairing process is solidified: standing for 0.5-1 hour at room temperature, transferring the putty into an oven after the surface of the putty is dried, and then, baking for 2-6 hours for curing under the condition that the temperature of the oven is raised to 70-90 ℃.
Further, the step (4) of the aircraft skin surface defect repairing process is solidified: standing for 0.5-1 hour at room temperature, and standing for 24 hours for curing at 23-26 ℃ after the surface of the putty is dried.
4. The process for repairing surface defects in aircraft skins as claimed in claim 1, wherein: and (4) curing: standing for 0.5-1 hour at room temperature, and standing for 30 hours for curing at 23-26 ℃ after the surface of the putty is dried.
Further, the repairing process of the surface defects of the aircraft skin comprises the following steps of (1) part surface treatment: and (3) polishing the paint layer of the area to be repaired by using 280-mesh sand paper to expose the metallic luster, respectively cleaning the area to be repaired by using gasoline and acetone, airing for 10-20 minutes each time, wiping the solvent by using dry and clean fine plain cloth after cleaning and wiping each time, and not allowing the solvent to naturally dry on the surface of the part and not allowing the solvent to drip in the cleaning process.
Further, the putty in the step (2) of the repair process of the surface defects of the aircraft skin is H07-1780 epoxy putty.
Compared with the prior art, the repair process for the surface defects of the aircraft skin has the advantages that the apparent defects of the aircraft skin are eliminated by using the putty, the repair process is suitable for repairing the defects of step differences, pits, poor glue of glass fiber reinforced plastics and the like on the surface of an aluminum alloy part, and the repair effect is good. The invention has simple construction process and convenient curing process (can be cured at room temperature), can effectively avoid the problems of rework, scrap and the like of parts, saves the production cost, shortens the delivery cycle, and has wide application prospect and practical application value.
Detailed Description
In the actual situation, the repair of the formed metal part or the composite material part is extremely difficult in the assembly process, so that the repair process is significant. The inventor often verifies the invention through long-term experiments, summarizes the invention, and describes the principle and the characteristics of the invention with the examples.
A repair process for surface defects of an aircraft skin comprises the following steps: (1) surface treatment of parts: polishing the paint layer of the area to be repaired by using sand paper to remove exposed metallic luster, cleaning the area to be repaired by using gasoline and acetone respectively, and airing for 10-20 minutes each time; (2) preparing putty: taking epoxy putty and a curing agent according to the proportion of 100: 10, fully and uniformly mixing; (3) coating putty: uniformly brushing or blade-coating the prepared putty on the to-be-repaired part of the cleaned metal part by using a soft brush or a scraper; (4) and (3) curing: standing at room temperature for 0.5-1 hour, transferring the putty into an oven after the surface of the putty is dried, and then starting the oven to heat to 50-70 ℃ for baking for 6-10 hours for curing; (5) shaping: and after the putty is cured, polishing the repaired part of the part to a paint spraying state by using sand paper.
To provide multiple curing effects. The aircraft skin surface defect repairing process is characterized by comprising the following steps: and (4) curing: standing for 0.5-1 hour at room temperature, transferring the putty into an oven after the surface of the putty is dried, and then, baking for 2-6 hours for curing under the condition that the temperature of the oven is raised to 70-90 ℃.
To provide multiple curing effects. The step (4) is solidification: standing for 0.5-1 hour at room temperature, and standing for 24 hours for curing at 23-26 ℃ after the surface of the putty is dried.
To provide multiple curing effects. The step (4) is solidification: standing for 0.5-1 hour at room temperature, and standing for 30 hours for curing at 23-26 ℃ after the surface of the putty is dried.
In order to make the treatment effect better. The step (1) of surface treatment of the part system: and (3) polishing the paint layer of the area to be repaired by using 280-mesh sand paper to expose the metallic luster, respectively cleaning the area to be repaired by using gasoline and acetone, airing for 10-20 minutes each time, wiping the solvent by using dry and clean fine plain cloth after cleaning and wiping each time, and not allowing the solvent to naturally dry on the surface of the part and not allowing the solvent to drip in the cleaning process.
In order to make the repairing effect better. The putty in the preparation of the putty in the step (2) is H07-1780 epoxy putty.
The technical solutions described above only represent the preferred technical solutions of the present invention, and some possible modifications to some parts of the technical solutions by those skilled in the art all represent the principles of the present invention, and fall within the protection scope of the present invention.
Claims (6)
1. A repair process for surface defects of an aircraft skin is characterized by comprising the following steps: the process comprises the following steps: (1) surface treatment of parts: polishing the paint layer of the area to be repaired by using sand paper to remove exposed metallic luster, cleaning the area to be repaired by using gasoline and acetone respectively, and airing for 10-20 minutes each time;
(2) preparing putty: taking epoxy putty and a curing agent according to the proportion of 100: 10, fully and uniformly mixing;
(3) coating putty: uniformly brushing or blade-coating the prepared putty on the to-be-repaired part of the cleaned metal part by using a soft brush or a scraper;
(4) and (3) curing: standing at room temperature for 0.5-1 hour, transferring the putty into an oven after the surface of the putty is dried, and then starting the oven to heat to 50-70 ℃ for baking for 6-10 hours for curing;
(5) shaping: and after the putty is cured, polishing the repaired part of the part to a paint spraying state by using sand paper.
2. The process for repairing surface defects in aircraft skins as claimed in claim 1, wherein: and (4) curing: standing for 0.5-1 hour at room temperature, transferring the putty into an oven after the surface of the putty is dried, and then, baking for 2-6 hours for curing under the condition that the temperature of the oven is raised to 70-90 ℃.
3. The process for repairing surface defects in aircraft skins as claimed in claim 1, wherein: and (4) curing: standing for 0.5-1 hour at room temperature, and standing for 24 hours for curing at 23-26 ℃ after the surface of the putty is dried.
4. The process for repairing surface defects in aircraft skins as claimed in claim 1, wherein: and (4) curing: standing for 0.5-1 hour at room temperature, and standing for 30 hours for curing at 23-26 ℃ after the surface of the putty is dried.
5. The process for repairing surface defects of aircraft skins as claimed in any one of claims 1 to 4, wherein: the step (1) of surface treatment of the parts: and (3) polishing the paint layer of the area to be repaired by using 280-mesh sand paper to expose the metallic luster, respectively cleaning the area to be repaired by using gasoline and acetone, airing for 10-20 minutes each time, wiping the solvent by using dry and clean fine plain cloth after cleaning and wiping each time, and not allowing the solvent to naturally dry on the surface of the part and not allowing the solvent to drip in the cleaning process.
6. The process for repairing surface defects in aircraft skins as claimed in claim 5, wherein: the putty in the preparation of the putty in the step (2) is H07-1780 epoxy putty.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811031563.1A CN110877006A (en) | 2018-09-05 | 2018-09-05 | Repair process for surface defects of aircraft skin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811031563.1A CN110877006A (en) | 2018-09-05 | 2018-09-05 | Repair process for surface defects of aircraft skin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110877006A true CN110877006A (en) | 2020-03-13 |
Family
ID=69727684
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811031563.1A Pending CN110877006A (en) | 2018-09-05 | 2018-09-05 | Repair process for surface defects of aircraft skin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110877006A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116408602A (en) * | 2023-04-10 | 2023-07-11 | 祥和科技（珠海）有限公司 | Treatment method for raw material defects of heat dissipation frame |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1096082A (en) * | 1993-05-29 | 1994-12-07 | 唐国定 | Process for making and repairing anticorrosive blade of axial flow fan in cooling tower |
| CN1234301A (en) * | 1999-05-27 | 1999-11-10 | 高德明 | Method for repairing painted surface |
| CA2281360A1 (en) * | 1998-09-04 | 2000-03-04 | Dukeplanning & Co., Inc. | Method for repairing the coated surface of a vehicle |
| US20060165882A1 (en) * | 2005-01-26 | 2006-07-27 | Stropp Juergen P | Process for vehicle repair coating |
| US20130004663A1 (en) * | 2011-06-30 | 2013-01-03 | Iiiinois Tool Works Inc. | Hand sandable fast repair body filler/putty/primer surfacer |
| US20150174707A1 (en) * | 2013-12-19 | 2015-06-25 | Hang Li | Plural layer putty-powder/slurry application method for superalloy component crack vacuum furnace healing |
| CN105860642A (en) * | 2016-06-16 | 2016-08-17 | 广州华润热电有限公司 | Novel special putty |
| CN106181248A (en) * | 2016-07-31 | 2016-12-07 | 上海车功坊汽车服务有限公司 | A kind of aluminium alloy car sheet metal component remanufactures technique |
-
2018
- 2018-09-05 CN CN201811031563.1A patent/CN110877006A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1096082A (en) * | 1993-05-29 | 1994-12-07 | 唐国定 | Process for making and repairing anticorrosive blade of axial flow fan in cooling tower |
| CA2281360A1 (en) * | 1998-09-04 | 2000-03-04 | Dukeplanning & Co., Inc. | Method for repairing the coated surface of a vehicle |
| CN1234301A (en) * | 1999-05-27 | 1999-11-10 | 高德明 | Method for repairing painted surface |
| US20060165882A1 (en) * | 2005-01-26 | 2006-07-27 | Stropp Juergen P | Process for vehicle repair coating |
| US20130004663A1 (en) * | 2011-06-30 | 2013-01-03 | Iiiinois Tool Works Inc. | Hand sandable fast repair body filler/putty/primer surfacer |
| US20150174707A1 (en) * | 2013-12-19 | 2015-06-25 | Hang Li | Plural layer putty-powder/slurry application method for superalloy component crack vacuum furnace healing |
| CN105860642A (en) * | 2016-06-16 | 2016-08-17 | 广州华润热电有限公司 | Novel special putty |
| CN106181248A (en) * | 2016-07-31 | 2016-12-07 | 上海车功坊汽车服务有限公司 | A kind of aluminium alloy car sheet metal component remanufactures technique |
Non-Patent Citations (2)
| Title |
|---|
| 张雨洋: "飞机蒙皮损伤修理研究", 《民营科技》 * |
| 陆刚: "大客车车身蒙皮及骨架的修复", 《城市车辆》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116408602A (en) * | 2023-04-10 | 2023-07-11 | 祥和科技（珠海）有限公司 | Treatment method for raw material defects of heat dissipation frame |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20200313 |