CN114211784A - Helicopter skin bullet hole repairing process - Google Patents
Helicopter skin bullet hole repairing process Download PDFInfo
- Publication number
- CN114211784A CN114211784A CN202111518379.1A CN202111518379A CN114211784A CN 114211784 A CN114211784 A CN 114211784A CN 202111518379 A CN202111518379 A CN 202111518379A CN 114211784 A CN114211784 A CN 114211784A
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- patch
- skin
- adhesive
- hole
- repaired
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- 238000000034 method Methods 0.000 title claims abstract description 32
- 239000000853 adhesive Substances 0.000 claims abstract description 37
- 230000001070 adhesive effect Effects 0.000 claims abstract description 37
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 9
- 239000004917 carbon fiber Substances 0.000 claims abstract description 9
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 9
- 238000001723 curing Methods 0.000 claims description 12
- 238000005520 cutting process Methods 0.000 claims description 12
- 239000003292 glue Substances 0.000 claims description 11
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 9
- 238000005498 polishing Methods 0.000 claims description 8
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 6
- 239000000835 fiber Substances 0.000 claims description 5
- 238000010438 heat treatment Methods 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 4
- 244000137852 Petrea volubilis Species 0.000 claims description 3
- 238000011049 filling Methods 0.000 claims description 3
- 239000003973 paint Substances 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 claims description 3
- 238000004080 punching Methods 0.000 claims description 2
- 239000007921 spray Substances 0.000 claims description 2
- 239000002994 raw material Substances 0.000 claims 1
- 238000012423 maintenance Methods 0.000 abstract description 4
- 238000005457 optimization Methods 0.000 abstract 1
- 238000007493 shaping process Methods 0.000 abstract 1
- 230000004083 survival effect Effects 0.000 abstract 1
- 238000000227 grinding Methods 0.000 description 17
- 239000002131 composite material Substances 0.000 description 6
- 238000002156 mixing Methods 0.000 description 5
- 238000006073 displacement reaction Methods 0.000 description 4
- 238000000576 coating method Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- NBIIXXVUZAFLBC-UHFFFAOYSA-N Phosphoric acid Chemical compound OP(O)(O)=O NBIIXXVUZAFLBC-UHFFFAOYSA-N 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 229910000147 aluminium phosphate Inorganic materials 0.000 description 1
- 229920006231 aramid fiber Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000003550 marker Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000005488 sandblasting Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 238000009966 trimming Methods 0.000 description 1
- 238000009489 vacuum treatment Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
- B29C73/10—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements using patches sealing on the surface of the article
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/24—Apparatus or accessories not otherwise provided for
- B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/24—Apparatus or accessories not otherwise provided for
- B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
- B29C2073/262—Apparatus or accessories not otherwise provided for for mechanical pretreatment for polishing, roughening, buffing or sanding the area to be repaired
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Adhesives Or Adhesive Processes (AREA)
Abstract
The invention discloses a repairing process for a bullet hole of a helicopter skin, and belongs to the field of emergency repair of the helicopter skin. The process comprises the steps of pretreatment of a bullet hole of a damaged skin part, selection and pretreatment of a carbon fiber patch, selection and proportioning of an adhesive, optimization of a curing process, shaping of a repaired part and the like. The maintenance process can greatly shorten the repair time and repair complexity of the skin, thereby improving the use efficiency of the airplane under special conditions, improving the quality stability of the airplane and increasing the battlefield survival rate of the airplane.
Description
Technical Field
The invention relates to the field of emergency repair of helicopter skins, in particular to a repairing process for a bullet hole of a helicopter skin.
Background
In the war period, emergency repair of various irregular damages on the skin of an airplane generally needs to be carried out after cutting and trimming into round holes and then bonding and repairing. The patch used for repairing is generally made of the same metal material as the aircraft skin material, and the fitting property and the timeliness after repairing are reduced compared with those of the patch made of a composite material. In the aspect of the field, international composite material repair is generally applied to civil aviation aircrafts, the research on the repair of military aircrafts is very limited, the composite material repair is mainly used for crack repair and not suitable for rush repair, and how to better apply the repair technology to the bullet hole repair of military aircrafts is a big problem at present.
Therefore, the invention provides a repairing process for a helicopter skin bullet hole, the process method can apply composite materials to repair the bullet hole left in the helicopter when bullets are in the helicopter, and meanwhile, the process can effectively shorten the repairing time of the traditional process and realize battlefield first-aid repair so as to strive for precious combat time.
Disclosure of Invention
The technical task of the invention is to overcome the defects of the prior art, and the invention provides a repairing process of a helicopter skin bullet hole by applying a composite material repairing technology to helicopter maintenance.
The technical scheme adopted by the invention for solving the technical problems is as follows: a helicopter skin bullet hole repairing process comprises the following steps:
and 4, curing the adhesive: the adhesive is cured by a stepwise curing method.
Further, the step 1 further comprises the following step of performing surface pretreatment on the skin of the domain to be repaired: and (3) selecting 200-1500 meshes of sand paper to spray paint and polish the interior of the skin to be repaired, then protecting the exposed metal part of the area to be repaired, and wiping the metal part with acetone after the protection is finished.
Furthermore, the patch I in the step 2 is a rounded rectangle with the side length being 1.5-2.5 times of the diameter of the cut hole and the center being the center.
Further, the diameter of the second round patch in the step 2 is 2-4 mm smaller than that of the cut hole, and the thickness of the second patch is 80-90% of that of the skin.
Further, the adhesive applied to the outer surface of the patch in the step 3 is a mixed adhesive I in the gap area of the cut hole and the patch II, and the mixed adhesive I is prepared from the following components in a mass ratio of 5-6: 3: 1-2 of a mixture of structural adhesive, carbon fiber short cut yarns and carbon powder; the adhesive coated between the skin to be repaired and the patch I is mixed glue II, and the mass ratio of the mixed glue II is 1: 8-10 of a mixture of carbon powder and structural adhesive.
Further, the structural adhesive is EA9309.3 type structural adhesive.
Further, the step-by-step curing method in the step 4 comprises the following steps: (1) uniformly heating to 55-65 ℃; (2) uniformly heating to 75-85 ℃ within 5 minutes; (3) preserving the heat for 110-130 minutes; (4) and (5) recovering the temperature to room temperature and the pressure to the standard atmospheric pressure within 15-25 minutes.
Furthermore, carbon fiber prepreg is adopted for the first patch and the second patch, and fiber laying is carried out according to the laying angle of 0 degree/45 degree/90 degree.
Compared with the prior art, the invention has the beneficial effects that: the invention provides a repairing process for a helicopter skin bullet hole, which can obviously shorten repairing time, simplify repairing process and improve repairing efficiency.
Drawings
FIG. 1 is a schematic view of a hole cut for skin bullet hole repair;
FIG. 2 is a schematic cross-sectional view of a hole cut after the step 1 treatment;
FIG. 3 is a schematic front view of a first patch;
FIG. 4 is a schematic front view of a second patch;
FIG. 5 is a schematic radial cross-sectional view of patch two;
FIG. 6 is a schematic diagram of hole cutting after applying the adhesive in step 3;
FIG. 7 is an unbroken aircraft skin mother plate tensile load-displacement curve;
FIG. 8 is a broken aircraft skin motherboard tensile load-displacement curve;
FIG. 9 is a tensile load-displacement curve of a damaged aircraft skin motherboard after repair with a rough grinding process;
FIG. 10 is a graph of tensile load versus displacement for a worn aircraft skin mother panel after repair and after finish grinding;
reference numerals: 1-bullet hole; 2-cutting holes; 3, patching one; 4-mixing glue I; 5-patch two; 6-mixing glue II; 7-cutting the skin to be repaired after the outer surface of the hole is pretreated.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Examples
The invention provides a helicopter skin bullet hole repairing process, which comprises the following steps:
firstly, observing a damaged bullet hole 1, finding out a deformed outline of a damaged part, drawing the outline clearly by using a marker pen, marking the deformed part caused by impact into a circular mark by taking the center of a punched hole to the deformed edge as a radius, cutting the marked outline by using tools such as a wind pen, an electric grinder and the like, and cutting a hole 2 as shown in figure 1;
marking a skin region to be repaired, namely the contour of a first patch, by using a pencil to extend outwards outside the cut contour range to 1.5 times of the diameter of a cut hole as the side length, wherein the contour is used for sticking the first patch, and the rounded rectangle is selected in the embodiment because the shearing resistance of the rounded rectangle is better than that of a circle and a rectangle; spraying and polishing the inner side and the outer side of a skin to be repaired by using 1000-mesh sand paper, treating the edge of a cut hole by using an air pen, and then forming an inverted trapezoid (an isosceles trapezoid with the length of the upper bottom surface larger than that of the lower bottom surface) on the section of the outer side of the cut hole; the skin to be repaired is retreated by a sand-blasting gun and then anodized by phosphoric acid for 5 minutes (a chemical treatment such as oxidation or other electrochemical treatment may be used), and the section of the hole is shown in fig. 2 (the upper side is the outer side and the lower side is the inner side).
preparing a first patch 3 (figure 3) according to the size of a region to be repaired of the skin, wherein the first patch is a square with the side length being 1.5 times of the diameter of the cut hole, processing four corners of the square into rounded corners, and finally, the first patch is a rounded square;
preparing a second round patch 5 (figure 4), wherein the diameter of the second patch is 4mm smaller than that of the cut hole, and the thickness of the second patch is 90% of that of the skin;
in the first patch and the second patch, carbon fiber prepreg (CF3011) (boron fiber, aramid fiber and the like can be used according to different use requirements), and in the aspect of laying, the used fiber laying is laid according to 0 degree/45 degrees/90 degrees;
processing the edge tangent plane of the second patch by using an air pen, wherein the section of the second patch after processing is in an inverted trapezoid shape (figure 5); and (3) treating the surface of the patch by using an electric grinder to further improve the connection capacity of the patch with the first patch and the machine body (different grinding angles can be selected according to the grinding condition of the repair body in the grinding direction), and finally cleaning the surface of the patch by using acetone and wiping the surface for later use.
taking the mass ratio of 6: 3: 1, a proper amount of EA9309.3 type structural adhesive is fully mixed with 3-9 mm carbon fiber short cut threads and carbon powder to prepare mixed adhesive I4, and the carbon fiber short cut threads have the characteristics of light weight, high strength, high modulus, corrosion resistance, electric conduction, good shielding performance, high wave absorption and the like, so that the repair quality can be improved by adding a proper amount of fiber threads; taking the mass ratio of 8: the 9309.3 type rubber of 1 is mixed with carbon powder to prepare a mixed rubber II 6, and the carbon powder can increase the fluidity of the mixed rubber II and enable the structural rubber to fully fill gaps.
Coating a second patch with first mixed glue on the surface (close to one side of the first patch) and the side surface, placing the second patch in the cut hole, filling a gap area formed by the second patch and the cut hole with the first mixed glue, and then pasting the first patch on the area to be repaired outside the cut hole through the second mixed glue; the adhesive application followed by hole cutting is shown in figure 6.
And 4, curing the adhesive: in the aspect of a curing process, a hot patching instrument is used for curing and vacuum treatment;
(1) uniformly raising the temperature to 60 ℃ within 8 minutes; (2) uniformly raising the temperature to 80 ℃ between 8 minutes and 13 minutes; (3) this state was maintained until 133 minutes; (4) and recovering the temperature to room temperature and the pressure to the standard atmospheric pressure by 150 minutes.
In the stage (2), the prepreg and the adhesive are cured smoothly; in stage (3), the degree of cure of the prepreg and adhesive is increased by increasing the cure temperature.
The method comprises the steps of firstly carrying out rough grinding by using 200-mesh abrasive paper, carrying out general grinding by using 1000-mesh abrasive paper after the appearance is basically qualified, and finally carrying out fine grinding by using 1500-mesh abrasive paper to finish the finishing and grinding of the surface of the skin. After finishing all the shapes, the finished surface of the skin is subjected to paint spraying and coating processes (the specific processes are processed according to the skin repair requirements) so as to reduce the stealth performance loss caused by maintenance.
Example 2
Example 2 differs from example 1 in that:
the side length of the patch I is 2 times of the diameter of the cut hole; the thickness of the patch II is 80% of that of the skin, and the diameter of the patch II is 2mm smaller than that of the cutting hole; the adhesive I is prepared by mixing EA9309.3 type structural adhesive, carbon fiber short cut threads and carbon powder according to the mass ratio of 5: 3: 2, fully mixing to obtain the product; the adhesive II is prepared from EA9309.3 type structural adhesive and carbon powder according to the mass ratio of 10: 1, fully mixing to obtain the product; the remaining treatment and repair were carried out in the same manner as in example 1.
In addition, the curing process of the embodiment is as follows:
(1) uniformly raising the temperature to 65 ℃ within 8 minutes; (2) uniformly raising the temperature to 85 ℃ between 8 minutes and 13 minutes; (3) this state was maintained until 123 minutes; (4) and the temperature is restored to room temperature and the pressure is restored to the standard atmospheric pressure by 148 minutes.
Before and after the aircraft skin of example 1 is repaired, the tensile test results are shown in fig. 7-10:
as can be seen, the maximum tensile load of the unbroken aircraft skin mother plate is 54017N; the maximum tensile load of the skin after breakage is 18900N; after single-side repairing, roughly grinding the repaired part, wherein the maximum tensile load of a test piece after rough grinding is 53897N and is more than 99% of the strength of the mother board, and the damaged part is a glued joint part; and after coarse grinding, finely grinding the repaired part, wherein the maximum tensile load 35622N of the test piece after fine grinding is 66% of the strength of the mother plate, and the damaged part is a glued joint part. Therefore, the repairing effect of the rough grinding is better than that of the fine grinding, and the rough grinding can be selected in consideration of long-term use and emergency repair.
The technical idea of the present invention is described in the above technical solutions, and the protection scope of the present invention is not limited thereto, and any changes and modifications made to the above technical solutions according to the technical essence of the present invention belong to the protection scope of the technical solutions of the present invention.
Claims (8)
1. A helicopter skin bullet hole repairing process is characterized by comprising the following steps:
step 1, bullet hole pretreatment: cutting off the part deformed by impact in a circular manner by taking the center of the punching hole to the deformed edge as a radius, polishing the edge of the cut hole formed after cutting off, and enabling the section of the cut hole to be in an inverted trapezoid after polishing; determining a skin region to be repaired, wherein the skin region to be repaired is used for pasting a first patch;
step 2, patch preparation: preparing a first patch according to the size of a to-be-repaired area of the skin; preparing a second round patch according to the size of the cut hole, and polishing the edge of the second patch, wherein the cross section of the polished second patch is the same as that of the cut hole;
step 3, placing a second patch with the surface and the side surface coated with the adhesive into the cut hole, filling a gap area formed by the second patch and the cut hole with the adhesive, and then pasting the first patch on the area to be repaired through the adhesive;
and 4, curing the adhesive: the adhesive is cured by a stepwise curing method.
2. The helicopter skin bullet hole repairing process according to claim 1, wherein said step 1 further comprises the step of surface pretreatment of the skin of the area to be repaired: and (3) selecting 200-1500 meshes of sand paper to spray paint and polish the interior of the skin to be repaired, then protecting the exposed metal part of the area to be repaired, and wiping the metal part with acetone after the protection is finished.
3. The helicopter skin bullet hole repairing process according to claim 1, wherein the first patch of step 2 is a rounded rectangle with 1.5-2.5 times of the diameter of the cut hole as a side length and the center of the cut hole as the center.
4. The helicopter skin bullet hole repairing process according to claim 1, wherein the diameter of the second circular patch of step 2 is 2-4 mm smaller than the diameter of the cut hole, and the thickness of the second patch is 80-90% of the thickness of the skin.
5. The helicopter skin bullet hole repairing process according to claim 1, wherein the adhesive applied to the outer surface of the patch in step 3, the gap area of the cut hole and the patch second is a first mixed glue, and the first mixed glue is prepared from the following raw materials in a mass ratio of 5-6: 3: 1-2 of a mixture of structural adhesive, carbon fiber short cut yarns and carbon powder; the adhesive coated between the skin to be repaired and the patch I is mixed glue II, and the mass ratio of the mixed glue II is 1: 8-10 of a mixture of carbon powder and structural adhesive.
6. The helicopter skin bullet hole repairing process of claim 5, wherein said structural adhesive is 9309.3 type structural adhesive.
7. The helicopter skin bullet hole repairing process according to claim 1, wherein the step-by-step curing method of step 4 is as follows: the step-by-step curing method in the step 4 comprises the following steps: (1) uniformly heating to 55-65 ℃; (2) uniformly heating to 75-85 ℃ within 5 minutes; (3) preserving the heat for 110-130 minutes; (4) and (5) recovering the temperature to room temperature and the pressure to the standard atmospheric pressure within 15-25 minutes.
8. The helicopter skin bullet hole repairing process according to claim 1, characterized in that carbon fiber prepregs are adopted for the first patch and the second patch, and fiber layups are laid according to the angle of 0 °/45 °/90 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111518379.1A CN114211784B (en) | 2021-12-13 | 2021-12-13 | Helicopter skin bullet hole repairing process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111518379.1A CN114211784B (en) | 2021-12-13 | 2021-12-13 | Helicopter skin bullet hole repairing process |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114211784A true CN114211784A (en) | 2022-03-22 |
| CN114211784B CN114211784B (en) | 2024-05-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111518379.1A Active CN114211784B (en) | 2021-12-13 | 2021-12-13 | Helicopter skin bullet hole repairing process |
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| CN (1) | CN114211784B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115042458A (en) * | 2022-06-22 | 2022-09-13 | 沈阳飞机工业（集团）有限公司 | Glue joint repairing process for composite material component of airplane box section structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2039655C1 (en) * | 1992-03-16 | 1995-07-20 | Алесковский Сергей Львович | Method of reconditioning the highly charged three-layer structures made of composite material |
| US20090282664A1 (en) * | 2008-04-30 | 2009-11-19 | Deutsches Zentrum Fur Luftund Raumfahrt E.V. | Method for repairing a flight component and patch therefor |
| CN105643962A (en) * | 2014-11-14 | 2016-06-08 | 江西昌河航空工业有限公司 | Method for repairing R corner of tool |
| CN108437497A (en) * | 2018-03-19 | 2018-08-24 | 中国南方航空股份有限公司 | A kind of engine is counter to push away grid typical damage renovation technique |
| CN113734462A (en) * | 2021-06-10 | 2021-12-03 | 江苏航空职业技术学院 | Skin maintenance method for sports aircraft |
| CN114211785A (en) * | 2021-12-13 | 2022-03-22 | 沈阳航空航天大学 | Composite material repairing process for aircraft skin hole-breaking type damage |
-
2021
- 2021-12-13 CN CN202111518379.1A patent/CN114211784B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2039655C1 (en) * | 1992-03-16 | 1995-07-20 | Алесковский Сергей Львович | Method of reconditioning the highly charged three-layer structures made of composite material |
| US20090282664A1 (en) * | 2008-04-30 | 2009-11-19 | Deutsches Zentrum Fur Luftund Raumfahrt E.V. | Method for repairing a flight component and patch therefor |
| CN105643962A (en) * | 2014-11-14 | 2016-06-08 | 江西昌河航空工业有限公司 | Method for repairing R corner of tool |
| CN108437497A (en) * | 2018-03-19 | 2018-08-24 | 中国南方航空股份有限公司 | A kind of engine is counter to push away grid typical damage renovation technique |
| CN113734462A (en) * | 2021-06-10 | 2021-12-03 | 江苏航空职业技术学院 | Skin maintenance method for sports aircraft |
| CN114211785A (en) * | 2021-12-13 | 2022-03-22 | 沈阳航空航天大学 | Composite material repairing process for aircraft skin hole-breaking type damage |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115042458A (en) * | 2022-06-22 | 2022-09-13 | 沈阳飞机工业（集团）有限公司 | Glue joint repairing process for composite material component of airplane box section structure |
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| Publication number | Publication date |
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| CN114211784B (en) | 2024-05-28 |
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