CN113511346A - Method for repairing composite material of general airplane and method for repairing damaged, unfilled corner and foreign body part - Google Patents
Method for repairing composite material of general airplane and method for repairing damaged, unfilled corner and foreign body part Download PDFInfo
- Publication number
- CN113511346A CN113511346A CN202110596809.5A CN202110596809A CN113511346A CN 113511346 A CN113511346 A CN 113511346A CN 202110596809 A CN202110596809 A CN 202110596809A CN 113511346 A CN113511346 A CN 113511346A
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- 239000002131 composite material Substances 0.000 title claims abstract description 62
- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000004140 cleaning Methods 0.000 claims abstract description 11
- 230000008439 repair process Effects 0.000 claims abstract description 11
- 238000007689 inspection Methods 0.000 claims abstract description 6
- 239000004744 fabric Substances 0.000 claims description 39
- 239000011347 resin Substances 0.000 claims description 23
- 229920005989 resin Polymers 0.000 claims description 23
- 239000000428 dust Substances 0.000 claims description 21
- 239000000835 fiber Substances 0.000 claims description 21
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 18
- 239000002390 adhesive tape Substances 0.000 claims description 18
- 238000005498 polishing Methods 0.000 claims description 15
- 239000000853 adhesive Substances 0.000 claims description 14
- 230000001070 adhesive effect Effects 0.000 claims description 14
- 238000009966 trimming Methods 0.000 claims description 10
- 238000000227 grinding Methods 0.000 claims description 8
- 239000000945 filler Substances 0.000 claims description 6
- 238000003892 spreading Methods 0.000 claims description 6
- 230000007480 spreading Effects 0.000 claims description 6
- 238000009941 weaving Methods 0.000 claims description 6
- 230000001680 brushing effect Effects 0.000 claims description 5
- 238000005520 cutting process Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 claims description 3
- 238000007598 dipping method Methods 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 claims description 3
- 230000000717 retained effect Effects 0.000 claims description 3
- 238000007790 scraping Methods 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 abstract description 11
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 230000009897 systematic effect Effects 0.000 abstract description 2
- 230000002950 deficient Effects 0.000 abstract 1
- 239000003795 chemical substances by application Substances 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000011109 contamination Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
-
- 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
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B55/00—Safety devices for grinding or polishing machines; Accessories fitted to grinding or polishing machines for keeping tools or parts of the machine in good working condition
- B24B55/06—Dust extraction equipment on grinding or polishing machines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Polishing Bodies And Polishing Tools (AREA)
Abstract
The invention discloses a method for overhauling a composite material of a general airplane and a method for repairing damaged, unfilled corner and foreign body parts, wherein the overhauling method comprises the following steps: pre-cleaning the produced composite material; inspecting each part of the composite material and marking the part with problems; performing treatment analysis on the part with the problem; repairing according to the result of the treatment analysis; and checking the repair result, pre-assembling the composite material, and warehousing the qualified composite material. The repairing method of the damaged, unfilled corner and foreign body part mainly comprises the steps of cleaning, repairing, curing and finishing the defective part. The invention provides a streamlined maintenance and inspection method, which defines the specific maintenance link and strictly controls the maintenance link. The maintenance is more systematic, so that the product quality and the production efficiency of the composite material of the general airplane are effectively improved.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a maintenance method of a composite material of a general airplane.
Background
With the development of general aviation becoming an important strategy for economic development in China, the social value of general aircrafts is increasingly shown. The composite material has the advantages of high strength and hardness, easy integral forming, high fatigue resistance, corrosion resistance and the like, and is widely applied to general airplanes. The high-quality composite material is produced efficiently, and is a key factor for improving the competitiveness of airplane manufacturing enterprises.
The prior general airplane composite material is manufactured to ensure the product quality, and the process flow is complicated and long. Strict inspection and maintenance of the composite material is also required after its production is complete.
Disclosure of Invention
The technical problems solved by the invention are as follows: provides a method for overhauling the composite material after the production is finished.
In order to solve the technical problems, the invention provides the following technical scheme: a method for overhauling a composite material of a general-purpose airplane comprises the following steps:
step 1: pre-cleaning the produced composite material;
step 2: inspecting each part of the composite material and marking the part with problems;
and step 3: performing treatment analysis on the part with the problem;
and 4, step 4: repairing according to the result of the treatment analysis;
and 5: and checking the repair result, pre-assembling the composite material, and warehousing the qualified composite material.
In the step 1, filling the part with larger holes or gaps with an adhesive prepared by mixing a specified proportion of filler, resin and curing agent, then placing the composite material into a pre-curing room, and pre-curing the adhesive for 12 hours; thereafter, a file, a sandpaper or a polishing machine is used to remove excess adhesive and trim possible edges, and then a vacuum cleaner is used to clean the dust.
In the step 2, the inspection mirror, the flashlight and the ruler are matched to inspect each part of the composite material one by one, check whether the surfaces of all the parts are smooth, and check whether the trimmed appearance, the trimmed size and the drilled hole meet design data or not, and check whether the cleaned adhesive and the redundant edges and corners exist or not; checking the bonding condition between the parts, whether the gaps are reasonable or not and whether holes exist or not; checking whether a broken unfilled corner exists or not; whether foreign matter is present; the problematic sites are marked.
And 3, performing treatment analysis on the part with the problem in the step 2, namely determining the type of the filler, the type, the weaving direction, the size and the number of layers of the fiber cloth and the repairing position of the part with the problem according to the drawing of the part.
In step 4, repairs are made according to the treatment analysis in step 3: the surface of a damaged part with a unfilled corner is properly polished by a grinder and abrasive paper according to treatment analysis, residual dust after polishing is removed by a dust collector, the part is cleaned once by wiping paper soaked in acetone, the surface is wiped to be dry by another piece of dry wiping paper, a paper adhesive tape is pasted around a repaired surface for protection treatment, then a layer of resin is brushed on the surface to be repaired, the prepared repaired patch is repaired on a corresponding position, a bearing film on the repaired patch is carefully removed, a layer of tearing cloth is laid, the repaired patch is placed in a pre-curing room for pre-curing treatment for 12 hours, and finally the paper adhesive tape and the tearing cloth are removed, and trimming and polishing are carried out.
In step 4, repairs are made according to the treatment analysis in step 3: analyzing the part with foreign matters according to treatment, and removing the foreign matters by using a grinder and abrasive paper if the foreign matters are attached to the surface of the composite material; if the foreign matter is in the composite material, the foreign matter is removed by a grinder and abrasive paper, so that the surface of the composite material is damaged, then the surface of the composite material is properly ground by the grinder and the abrasive paper, dust remained after grinding is removed by a dust collector, the composite material is cleaned once by wiping paper soaked in acetone, the surface is wiped by another piece of dry wiping paper, a paper adhesive tape is pasted on the periphery of a repaired surface for protection treatment, then a layer of resin is brushed on the surface to be repaired, the prepared repaired piece is repaired on the corresponding position, a bearing film on the repaired piece is carefully removed, a layer of tearing cloth is laid, then the repaired piece is placed in a pre-curing room for pre-curing treatment for 12 hours, and finally the paper adhesive tape and the tearing cloth are removed, and trimming and grinding are carried out.
The preparation method of the repairing sheet comprises the following steps: cutting the fiber cloth with corresponding type, size, weaving direction and number of layers according to the position and size of the damaged or unfilled corner, arranging the fiber cloth in sequence, spreading a bearing film with proper size on a workbench, brushing a layer of resin on the bearing film, spreading a layer of fiber cloth, dipping a proper amount of resin by using a brush or a scraper to remove the retained air, ensuring that the fiber cloth is completely soaked, spreading a layer of fiber cloth, repeating the method until all the cut fiber cloth is spread, and scraping the excessive resin by using the scraper.
The invention provides a streamlined maintenance and inspection method, which defines the specific maintenance link and strictly controls the maintenance link. The maintenance is more systematic, so that the product quality and the production efficiency of the composite material of the general airplane are effectively improved. The manufacture of the repair patch allows easy control and correction of the lamination process, and at the same time allows for a clean repair work with reduced contamination outside the repair area.
The invention provides a method for repairing damaged and unfilled corner parts of a general airplane composite material, which specifically comprises the following steps: properly polishing the surfaces of damaged and unfilled corners by using a grinder and abrasive paper, cleaning residual dust after polishing by using a dust collector, cleaning the surfaces once by using wiping paper soaked with acetone, wiping the surfaces by using another piece of dry wiping paper, attaching a paper adhesive tape around the repaired surface for protection treatment, brushing a layer of resin on the surface to be repaired, repairing the prepared repaired sheet to a corresponding position, carefully removing a bearing film on the repaired sheet, laying a layer of tearing cloth, then putting the repaired sheet into a pre-curing room for pre-curing treatment for 12 hours, finally removing the paper adhesive tape and the tearing cloth, and trimming and polishing.
The invention provides a method for repairing a foreign body part of a general airplane composite material, which specifically comprises the following steps of (4) repairing the foreign body part: if the foreign matters are attached to the surface of the composite material, removing the foreign matters by using a grinder and abrasive paper; if the foreign matter is in the composite material, the foreign matter is removed by a grinder and abrasive paper, so that the surface of the composite material is damaged, then the surface of the composite material is properly ground by the grinder and the abrasive paper, dust remained after grinding is removed by a dust collector, the composite material is cleaned once by wiping paper soaked in acetone, the surface is wiped by another piece of dry wiping paper, a paper adhesive tape is pasted on the periphery of a repaired surface for protection treatment, then a layer of resin is brushed on the surface to be repaired, the prepared repaired piece is repaired on the corresponding position, a bearing film on the repaired piece is carefully removed, a layer of tearing cloth is laid, then the repaired piece is placed in a pre-curing room for pre-curing treatment for 12 hours, and finally the paper adhesive tape and the tearing cloth are removed, and trimming and grinding are carried out.
Detailed Description
A maintenance method of a general airplane composite material by using an airplane wing composite material comprises the following steps:
step 1: the method comprises the steps of pre-cleaning the wings, filling corresponding parts of the wings by adopting an adhesive prepared by mixing a specified proportion of a filler, resin and a curing agent into a hole or a larger gap area, and then putting the wings into a pre-curing room to pre-cure the adhesive for 12 hours. Excess resin, adhesive and leftover materials possibly generated by trimming are removed by a file, ground by No. 120 sandpaper or polished by a polishing machine, and then the wings are cleaned by a dust collector.
Step 2: all parts of the wing are inspected, and the upper cover shell, the lower cover shell, the front rib, the middle end, the rear rib, the rear web plate, the end rib and the like of the wing are inspected one by matching with an inspection mirror, a flashlight and a ruler, so that whether the surfaces of all parts are flat or not is checked, and whether the trimmed appearance, the trimmed size and the drilled hole accord with design data or not is checked. Checking whether the resin, the adhesive and the redundant edges and corners are cleaned; checking the bonding condition between the parts, whether the gaps are reasonable or not and whether holes exist or not; checking whether a broken unfilled corner exists or not; whether or not foreign matter is present. The problematic sites are marked.
And step 3: performing treatment analysis on the corresponding problems and the field conditions, including classifying the corresponding problems: (1) cleaning a leak; (2) holes exist or gaps are large; (3) breakage and unfilled corner; (4) the existence of foreign matters, and the types of the fillers, the types, the weaving directions, the sizes and the layers of the fiber cloth and the repairing positions thereof are determined according to the drawing of the wing according to the problems.
And 4, step 4: repair is performed according to the disposal analysis in step 3:
(1) and (4) cleaning the parts which are not cleaned according to the step 1.
(2) And filling corresponding parts of the areas with larger holes or gaps by adopting an adhesive prepared by mixing the filler, the resin and the curing agent in a specified proportion, and then putting the areas into a pre-curing room to perform pre-curing treatment on the adhesive for 12 hours.
(3) According to the treatment analysis, the surface of a damaged part with a unfilled corner is properly polished by a grinder and abrasive paper, the residual dust after polishing is removed by a dust collector, the part is cleaned once by wiping paper soaked in acetone, the surface is wiped to be dry by another piece of dry wiping paper, a paper adhesive tape is pasted around the repaired surface for protection treatment, then a layer of resin is brushed on the surface to be repaired, the prepared repaired patch is repaired to a corresponding position, a bearing film on the repaired patch is carefully removed, a layer of tearing cloth is laid, the repaired patch is placed in a pre-curing room for pre-curing treatment for 12 hours, and finally the paper adhesive tape and the tearing cloth are removed, and trimming and polishing are carried out.
The preparation method of the repairing sheet comprises the following steps: cutting the fiber cloth with corresponding type, size, weaving direction and number of layers according to requirements, arranging the fiber cloth in sequence, laying a bearing film with proper size on a workbench, brushing a layer of resin on the bearing film, laying a layer of fiber cloth, dipping a proper amount of resin by using a brush or a scraper to remove the retained air, ensuring that the fiber cloth is completely soaked, laying the next layer of fiber cloth, repeating the method until all the cut fiber cloth is laid, and scraping the excessive resin by using the scraper.
(4) For the part with the foreign matter, according to the treatment analysis, if the foreign matter is attached to the surface of the wing, the foreign matter is removed by a grinder and abrasive paper; and (4) if the foreign matters are in the wing composite material, removing the foreign matters by using a grinder and abrasive paper, and repairing the generated damaged positions according to the repairing scheme in the step (3) in the step (4).
And 5: checking the rectification result, pre-installing the wings, and warehousing the obtained qualified wings.
The above description is only a preferred embodiment of the present invention, and for those skilled in the art, the present invention should not be limited by the description herein, since various changes and modifications can be made in the details of the embodiment and the application range according to the spirit of the present invention.
Claims (9)
1. A method for overhauling a composite material of a general airplane is characterized by comprising the following steps:
step 1: pre-cleaning the produced composite material;
step 2: inspecting each part of the composite material and marking the part with problems;
and step 3: performing treatment analysis on the part with the problem;
and 4, step 4: repairing according to the result of the treatment analysis;
and 5: and checking the repair result, pre-assembling the composite material, and warehousing the qualified composite material.
2. A method of servicing a general purpose aircraft composite material as claimed in claim 1, wherein: in the step 1, the part with larger holes or gaps is filled with an adhesive, and then the composite material is placed in a pre-curing room, and the adhesive is subjected to pre-curing treatment for 12 hours; thereafter, a file, a sandpaper or a polishing machine is used to remove excess adhesive and trim possible edges, and then a vacuum cleaner is used to clean the dust.
3. A method of servicing a general purpose aircraft composite material as claimed in claim 2, wherein: in the step 2, the inspection mirror, the flashlight and the ruler are matched to inspect each part of the composite material one by one, check whether the surfaces of all the parts are smooth, and check whether the trimmed appearance, the trimmed size and the drilled hole meet design data or not, and check whether the cleaned adhesive and the redundant edges and corners exist or not; checking the bonding condition between the parts, whether the gaps are reasonable or not and whether holes exist or not; checking whether a broken unfilled corner exists or not; whether foreign matter is present; the problematic sites are marked.
4. A method of servicing a general purpose aircraft composite material as claimed in claim 1 or 3, wherein: and 3, performing treatment analysis on the part with the problem in the step 2, namely determining the type of the filler, the type, the weaving direction, the size and the number of layers of the fiber cloth and the repairing position of the part with the problem according to the drawing of the part.
5. A method of servicing a general purpose aircraft composite material as claimed in claim 1 or 3, wherein: in step 4, repairs are made according to the treatment analysis in step 3: the surface of a damaged part with a unfilled corner is properly polished by a grinder and abrasive paper according to treatment analysis, residual dust after polishing is removed by a dust collector, the part is cleaned once by wiping paper soaked in acetone, the surface is wiped to be dry by another piece of dry wiping paper, a paper adhesive tape is pasted around a repaired surface for protection treatment, then a layer of resin is brushed on the surface to be repaired, the prepared repaired patch is repaired on a corresponding position, a bearing film on the repaired patch is carefully removed, a layer of tearing cloth is laid, the repaired patch is placed in a pre-curing room for pre-curing treatment for 12 hours, and finally the paper adhesive tape and the tearing cloth are removed, and trimming and polishing are carried out.
6. A method of servicing a general purpose aircraft composite material as claimed in claim 5, wherein: in step 4, repairs are made according to the treatment analysis in step 3: analyzing the part with foreign matters according to treatment, and removing the foreign matters by using a grinder and abrasive paper if the foreign matters are attached to the surface of the composite material; if the foreign matter is in the composite material, the foreign matter is removed by a grinder and abrasive paper, so that the surface of the composite material is damaged, then the surface of the composite material is properly ground by the grinder and the abrasive paper, dust remained after grinding is removed by a dust collector, the composite material is cleaned once by wiping paper soaked in acetone, the surface is wiped by another piece of dry wiping paper, a paper adhesive tape is pasted on the periphery of a repaired surface for protection treatment, then a layer of resin is brushed on the surface to be repaired, the prepared repaired piece is repaired on the corresponding position, a bearing film on the repaired piece is carefully removed, a layer of tearing cloth is laid, then the repaired piece is placed in a pre-curing room for pre-curing treatment for 12 hours, and finally the paper adhesive tape and the tearing cloth are removed, and trimming and grinding are carried out.
7. A method of servicing a general purpose aircraft composite material as claimed in claim 5, wherein: the preparation method of the repairing sheet comprises the following steps: cutting the fiber cloth with corresponding type, size, weaving direction and number of layers according to the position and size of the damaged or unfilled corner, arranging the fiber cloth in sequence, spreading a bearing film with proper size on a workbench, brushing a layer of resin on the bearing film, spreading a layer of fiber cloth, dipping a proper amount of resin by using a brush or a scraper to remove the retained air, ensuring that the fiber cloth is completely soaked, spreading a layer of fiber cloth, repeating the method until all the cut fiber cloth is spread, and scraping the excessive resin by using the scraper.
8. A method for repairing damaged and unfilled corner parts of a general-purpose aircraft composite material is characterized by comprising the following steps: properly polishing the surfaces of damaged and unfilled corners by using a grinder and abrasive paper, cleaning residual dust after polishing by using a dust collector, cleaning the surfaces once by using wiping paper soaked with acetone, wiping the surfaces by using another piece of dry wiping paper, attaching a paper adhesive tape around the repaired surface for protection treatment, brushing a layer of resin on the surface to be repaired, repairing the prepared repaired sheet to a corresponding position, carefully removing a bearing film on the repaired sheet, laying a layer of tearing cloth, then putting the repaired sheet into a pre-curing room for pre-curing treatment for 12 hours, finally removing the paper adhesive tape and the tearing cloth, and trimming and polishing.
9. A method of repairing a foreign body site of a versatile aircraft composite material, characterized by: if the foreign matters are attached to the surface of the composite material, removing the foreign matters by using a grinder and abrasive paper; if the foreign matter is in the composite material, the foreign matter is removed by a grinder and abrasive paper, so that the surface of the composite material is damaged, then the surface of the composite material is properly ground by the grinder and the abrasive paper, dust remained after grinding is removed by a dust collector, the composite material is cleaned once by wiping paper soaked in acetone, the surface is wiped by another piece of dry wiping paper, a paper adhesive tape is pasted on the periphery of a repaired surface for protection treatment, then a layer of resin is brushed on the surface to be repaired, the prepared repaired piece is repaired on the corresponding position, a bearing film on the repaired piece is carefully removed, a layer of tearing cloth is laid, then the repaired piece is placed in a pre-curing room for pre-curing treatment for 12 hours, and finally the paper adhesive tape and the tearing cloth are removed, and trimming and grinding are carried out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110596809.5A CN113511346A (en) | 2021-05-31 | 2021-05-31 | Method for repairing composite material of general airplane and method for repairing damaged, unfilled corner and foreign body part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110596809.5A CN113511346A (en) | 2021-05-31 | 2021-05-31 | Method for repairing composite material of general airplane and method for repairing damaged, unfilled corner and foreign body part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113511346A true CN113511346A (en) | 2021-10-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110596809.5A Pending CN113511346A (en) | 2021-05-31 | 2021-05-31 | Method for repairing composite material of general airplane and method for repairing damaged, unfilled corner and foreign body part |
Country Status (1)
| Country | Link |
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| CN (1) | CN113511346A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116619784A (en) * | 2023-07-24 | 2023-08-22 | 江苏亨睿航空工业有限公司 | Method for rapidly repairing and reinforcing external field of aircraft |
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| CN111055518A (en) * | 2019-12-09 | 2020-04-24 | 中航复合材料有限责任公司 | Composite material gluing and repairing method suitable for vacuum bag pressing process |
| CN112848417A (en) * | 2020-11-27 | 2021-05-28 | 黄冈格罗夫氢能汽车有限公司 | Crack repair method for carbon fiber composite product of hydrogen fuel cell automobile |
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2021
- 2021-05-31 CN CN202110596809.5A patent/CN113511346A/en active Pending
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| US20140295124A1 (en) * | 2013-03-28 | 2014-10-02 | Mitsubishi Aircraft Corporation | Repair method of repair target portion, and repaired product obtained from repairing |
| CN104340378A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Repair method of composite main paddle with hinge moment variance |
| US20180273207A1 (en) * | 2015-09-16 | 2018-09-27 | Short Brothers Plc | Method of repairing a composite material |
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| CN116619784A (en) * | 2023-07-24 | 2023-08-22 | 江苏亨睿航空工业有限公司 | Method for rapidly repairing and reinforcing external field of aircraft |
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