CN102335804A - Method for repairing metal skin by using composite material - Google Patents
Method for repairing metal skin by using composite material Download PDFInfo
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- CN102335804A CN102335804A CN2010102315652A CN201010231565A CN102335804A CN 102335804 A CN102335804 A CN 102335804A CN 2010102315652 A CN2010102315652 A CN 2010102315652A CN 201010231565 A CN201010231565 A CN 201010231565A CN 102335804 A CN102335804 A CN 102335804A
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- glass cloth
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- metal skin
- epoxy resin
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Abstract
The invention discloses a method for repairing a metal skin by using a composite material. The method comprises the following steps of: 1, cleaning a region to be repaired by using a cleaning agent; 2, brushing or spraying an adhesive first coating agent on the region to be repaired; 3, brushing or spraying a sealing agent on the surface of the region to be repaired; 4, spreading and laying glass cloth on the surface of the metal skin; 5, repeating the step 4 until the layering thickness meets the repairing requirement; 6, grinding the surface of the EW200 glass cloth to ensure that the surface is rough to be convenient for adhering a paint layer; and 7, spraying paint on the surface of the glass cloth to ensure that the color of the region to be repaired is consistent with the surrounding color. The invention simplifies process procedures, reduces spare parts, and has the characteristics of higher repairing speed, lower cost and the like.
Description
Technical field
the present invention relates to a kind of restorative procedure of metal skin, particularly approach the method for metal skin with the composite reparation.
Background technology
generally speaking, identical or close sheet metal material is mostly adopted in the reparation of aircraft metal skin.The defective of this method is to carry out a series of complicated technology engineerings such as machine-shaping, heat treatment, surface anticorrosive processing to sheet material, is difficult to repair in the short time, and then causes the cycle long, can't satisfy schedule requirement.Use though can prepare the difform material of heat treatment, surface-treated in advance,, be difficult to accomplish exhaustive, and the manufacturing of a large amount of spare parts, store the rising that has also caused cost because aircraft skin is complex-shaped.
Summary of the invention
technical problem to be solved by this invention is to provide a kind of rapid speed speed and lower-cost method with composite reparation metal skin, thereby overcomes the deficiency of prior art.
For solving the problems of the technologies described above technical scheme of the present invention: with the method that composite is repaired metal skin, this method may further comprise the steps;
(1), use cleaning agent to clean district to be repaired;
(2), after to be cleaned dose of drying, brush or the spraying and adhesive bonding silane coupling agent in district to be repaired;
(3), brush or the spraying sealant on surface, district to be repaired;
(4), after to be sealed dose of drying, on glass cloth, brush the epoxy resin that mixes curing agent, then glass cloth is applied at skin-surface by the smooth shop of surface configuration, district to be repaired;
(5), repeated for (4) step, the satisfied reparation of layer thickness requirement up to the shop;
(6), at room temperature wait for 12～24 hours, treat that E51 epoxy resin solidifies the surface of back polishing EW200 glass cloth fully, make its rough surface, be convenient to enamelled coating and adhere to;
(7), in glass cloth surface japanning, make that to repair district's color consistent with ambient color.
The method that
are above-mentioned with composite reparation metal skin, in step (1), used cleaning agent is 93# gasoline and acetone; Before cleaning district to be repaired, remove the breakage burr earlier, and prevent ceasma at main crackle latter end.
aforesaid method of repairing metal skin with composite, in step (5), every shop is waited for 15～20 minutes after applying 3 layers of glass cloth, and the inner layer ring epoxy resins is solidified slightly, avoids newly spreading pull-up and falls.
aforesaid method of repairing metal skin with composite, described bonding silane coupling agent is the bonding silane coupling agent of QS-7, and epoxy resin is E51 epoxy resin, and sealant is the XM22B sealant, and glass cloth is the EW200 glass cloth.
beneficial effect of the present invention: compared with prior art; Major advantage of the present invention is: first does not need mould molding, simplifies technological process, has accelerated the repair progress; Need not return the repair in shop reason to the delivered consumer products, not need the new workpieces of producer; Second environment requires low, can construct in ordinary plant, hangar; The 3rd reduces spare part, reduces the aircraft maintenance cost.
Description of drawings
Fig. 1 is damaged covering sketch map;
Fig. 2 is with burr removal and the damaged covering after main crackle latter end is prevented ceasma.
are further described the present invention below in conjunction with the accompanying drawing and the specific embodiment.
The specific embodiment
embodiment 1.Like Fig. 1, shown in 2, in the present embodiment, position to be repaired is the damaged zone of leading edge of a wing bump, and it is following specifically to repair step:
The breakage burr is removed by
(1), elder generation, and prevents ceasma at main crackle latter end, cleans district to be repaired with 93# gasoline and acetone successively then, to remove former enamelled coating and aerofoil surface greasy dirt etc.(2), after to be cleaned dose of drying, evenly brush or the bonding silane coupling agent of spraying QS-7 in district to be repaired.(3), district surface to be repaired brush or the spraying dilution after the XM22B sealant, thickness is between 0.3 ~ 0.5mm.(4), treat XM22B sealant drying after, on the EW200 glass cloth, brush the E51 epoxy resin mix curing agent, then the EW200 glass cloth is applied at skin-surface by the smooth shop of surface configuration, district to be repaired, thickness is between 1 ~ 1.2mm.(5), repeated for (4) step, the satisfied reparation of layer thickness requirement up to the shop; Every shop is waited for 15 minutes after applying 3 layers of glass cloth, and internal layer E51 epoxy resin is solidified slightly, avoids newly spreading pull-up and falls.(6), at room temperature wait for 24 hours, treat that E51 epoxy resin solidifies the surface of the slight polishing in back EW200 glass cloth fully, make its surface slightly coarse, be convenient to enamelled coating and adhere to.(7), at glass cloth surface spraying light gray colored paint, make that to repair district's color consistent with ambient color.
The method of this programme is adopted in
this wing cover reparation, avoids new system covering mould, thereby has accelerated the repair progress, reduces rehabilitation cost simultaneously.Covering after test, the repairing of taking a flight test satisfies instructions for use fully.
embodiment of the present invention is not limited to the foregoing description, and the various variations of under the prerequisite that does not break away from aim of the present invention, making all belong within protection scope of the present invention.
Claims (4)
1. a method of repairing metal skin with composite is characterized in that: may further comprise the steps;
(1), use cleaning agent to clean district to be repaired;
(2), after to be cleaned dose of drying, brush or the spraying and adhesive bonding silane coupling agent in district to be repaired;
(3), brush or the spraying sealant on surface, district to be repaired;
(4), after to be sealed dose of drying, on glass cloth, brush the epoxy resin that mixes curing agent, then glass cloth is applied at skin-surface by the smooth shop of surface configuration, district to be repaired;
(5), repeated for (4) step, the satisfied reparation of layer thickness requirement up to the shop;
(6), at room temperature wait for 12～24 hours, treat that E51 epoxy resin solidifies the surface of back polishing EW200 glass cloth fully, make its rough surface, be convenient to enamelled coating and adhere to;
(7), in glass cloth surface japanning, make that to repair district's color consistent with ambient color.
2. method of repairing metal skin according to claim 1 with composite, it is characterized in that: in the step (1), used cleaning agent is 93# gasoline and acetone; Before cleaning district to be repaired, remove the breakage burr earlier, and prevent ceasma at main crackle latter end.
3. method of repairing metal skin with composite according to claim 1 is characterized in that: in the step (5), every shop is waited for 15～20 minutes after applying 3 layers of glass cloth, and the inner layer ring epoxy resins is solidified slightly, avoids newly spreading pull-up and falls.
4. method of repairing metal skin with composite according to claim 1, it is characterized in that: described bonding silane coupling agent is the bonding silane coupling agent of QS-7, and epoxy resin is E51 epoxy resin, and sealant is the XM22B sealant, and glass cloth is the EW200 glass cloth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102315652A CN102335804A (en) | 2010-07-21 | 2010-07-21 | Method for repairing metal skin by using composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102315652A CN102335804A (en) | 2010-07-21 | 2010-07-21 | Method for repairing metal skin by using composite material |
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| CN102335804A true CN102335804A (en) | 2012-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2010102315652A Pending CN102335804A (en) | 2010-07-21 | 2010-07-21 | Method for repairing metal skin by using composite material |
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| CN (1) | CN102335804A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103950553A (en) * | 2014-04-25 | 2014-07-30 | 哈尔滨飞机工业集团有限责任公司 | Method for repairing countersunk crossed nest |
| CN104117634A (en) * | 2014-08-09 | 2014-10-29 | 山东理工大学 | Repairing method of casting die |
| CN105269832A (en) * | 2014-07-23 | 2016-01-27 | 中国航天科工集团第六研究院四十一所 | Preparation technology for aviation bomb composite material skin |
| CN105750815A (en) * | 2016-02-25 | 2016-07-13 | 陕西飞机工业（集团）有限公司 | Skin damage repair method for aluminum alloy skin foam sandwich part |
| CN106995036A (en) * | 2016-01-22 | 2017-08-01 | 江南造船(集团)有限责任公司 | The restorative procedure of rhombus independent liquid cargo tank protective layer |
| CN108556088A (en) * | 2017-12-20 | 2018-09-21 | 浙江云峰莫干山装饰建材有限公司 | A kind of method for maintaining of recombinant decorative material irony mold |
| CN109268581A (en) * | 2018-09-06 | 2019-01-25 | 国营芜湖机械厂 | A kind of special-shaped thin wall welding power fuel oil conduit reliability growth method |
| CN109570902A (en) * | 2018-11-23 | 2019-04-05 | 国营芜湖机械厂 | Aircaft configuration fuel tank aluminium alloy main load-bearing part crackle adhesive bonding of composites repair method |
| CN110539895A (en) * | 2019-07-26 | 2019-12-06 | 国营芜湖机械厂 | method for repairing damage of aluminum-sprayed layer on outer surface of composite structure of airplane |
| CN113146142A (en) * | 2021-04-14 | 2021-07-23 | 芜湖创联新材料科技有限公司 | Device and method for rapidly repairing cracks on hole edge of metal skin of airplane by using composite material |
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| CN1727109A (en) * | 2005-07-27 | 2006-02-01 | 广东超华科技股份有限公司 | Method for restoring worn-out pot for smelted copper |
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| CN1727109A (en) * | 2005-07-27 | 2006-02-01 | 广东超华科技股份有限公司 | Method for restoring worn-out pot for smelted copper |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103950553B (en) * | 2014-04-25 | 2016-02-24 | 哈尔滨飞机工业集团有限责任公司 | A kind ofly draw the repair method of nest to immersing oneself in |
| CN103950553A (en) * | 2014-04-25 | 2014-07-30 | 哈尔滨飞机工业集团有限责任公司 | Method for repairing countersunk crossed nest |
| CN105269832A (en) * | 2014-07-23 | 2016-01-27 | 中国航天科工集团第六研究院四十一所 | Preparation technology for aviation bomb composite material skin |
| CN104117634B (en) * | 2014-08-09 | 2018-04-27 | 山东理工大学 | Casting mould restorative procedure |
| CN104117634A (en) * | 2014-08-09 | 2014-10-29 | 山东理工大学 | Repairing method of casting die |
| CN106995036A (en) * | 2016-01-22 | 2017-08-01 | 江南造船(集团)有限责任公司 | The restorative procedure of rhombus independent liquid cargo tank protective layer |
| CN106995036B (en) * | 2016-01-22 | 2018-11-16 | 江南造船(集团)有限责任公司 | The restorative procedure of diamond shape independent liquid cargo tank protective layer |
| CN105750815A (en) * | 2016-02-25 | 2016-07-13 | 陕西飞机工业（集团）有限公司 | Skin damage repair method for aluminum alloy skin foam sandwich part |
| CN108556088A (en) * | 2017-12-20 | 2018-09-21 | 浙江云峰莫干山装饰建材有限公司 | A kind of method for maintaining of recombinant decorative material irony mold |
| CN109268581A (en) * | 2018-09-06 | 2019-01-25 | 国营芜湖机械厂 | A kind of special-shaped thin wall welding power fuel oil conduit reliability growth method |
| CN109570902A (en) * | 2018-11-23 | 2019-04-05 | 国营芜湖机械厂 | Aircaft configuration fuel tank aluminium alloy main load-bearing part crackle adhesive bonding of composites repair method |
| CN110539895A (en) * | 2019-07-26 | 2019-12-06 | 国营芜湖机械厂 | method for repairing damage of aluminum-sprayed layer on outer surface of composite structure of airplane |
| CN113146142A (en) * | 2021-04-14 | 2021-07-23 | 芜湖创联新材料科技有限公司 | Device and method for rapidly repairing cracks on hole edge of metal skin of airplane by using composite material |
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Application publication date: 20120201 |