CN113928576B - Helicopter composite material lightning protection capability repairing method - Google Patents
Helicopter composite material lightning protection capability repairing method Download PDFInfo
- Publication number
- CN113928576B CN113928576B CN202111391750.2A CN202111391750A CN113928576B CN 113928576 B CN113928576 B CN 113928576B CN 202111391750 A CN202111391750 A CN 202111391750A CN 113928576 B CN113928576 B CN 113928576B
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- China
- Prior art keywords
- helicopter
- lightning
- copper
- composite material
- structural member
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- 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.)
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- 239000002131 composite material Substances 0.000 title claims abstract description 51
- 238000000034 method Methods 0.000 title claims abstract description 18
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 55
- 229910052802 copper Inorganic materials 0.000 claims abstract description 54
- 239000010949 copper Substances 0.000 claims abstract description 54
- 239000002313 adhesive film Substances 0.000 claims abstract description 17
- 238000005192 partition Methods 0.000 claims abstract description 17
- 239000003365 glass fiber Substances 0.000 claims abstract description 10
- 239000003292 glue Substances 0.000 claims abstract description 5
- 239000000853 adhesive Substances 0.000 claims description 2
- 230000001070 adhesive effect Effects 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 238000000465 moulding Methods 0.000 claims description 2
- 239000012528 membrane Substances 0.000 claims 2
- APTZNLHMIGJTEW-UHFFFAOYSA-N pyraflufen-ethyl Chemical compound C1=C(Cl)C(OCC(=O)OCC)=CC(C=2C(=C(OC(F)F)N(C)N=2)Cl)=C1F APTZNLHMIGJTEW-UHFFFAOYSA-N 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 12
- 238000012360 testing method Methods 0.000 description 11
- 208000025274 Lightning injury Diseases 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 238000012942 design verification Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 239000000084 colloidal system Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000010408 sweeping Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/02—Lightning protectors; Static dischargers
-
- 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)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Laminated Bodies (AREA)
- Elimination Of Static Electricity (AREA)
Abstract
The application provides a helicopter composite material lightning protection capability restoration method, which comprises the following steps: fixing a diversion copper strip on a composite structural member of a lightning zone of the helicopter; laying a copper net with a glue film on the composite structural member of the lightning partition of the helicopter; covering glass fibers on the copper mesh with the adhesive film; the application provides a method for repairing lightning protection capability of a helicopter composite material, which can effectively repair a composite material structural member which does not have the lightning protection capability until the lightning protection design requirement is met.
Description
Technical Field
The application belongs to the technical field of lightning protection of helicopters, and particularly relates to a method for repairing lightning protection capability of a helicopter composite material.
Background
Lightning is the most complex natural phenomenon generated by charge discharge in rain clouds, is the most common strong electromagnetic interference source in the atmosphere, and comprises inter-cloud discharge, cloud-to-ground discharge, aircraft induced discharge and the like. Because of the fact that composite materials are increasingly adopted to replace metal materials in modern aircraft design, the resistance of the aircraft body to external severe electromagnetic environments is reduced, and various measuring, controlling and radio precision electronic and electric equipment are applied, once the aircraft is struck by lightning, the electronic and electric equipment are extremely easy to damage, the functions of the system are affected by light persons, and the heavy persons destroy the aircraft.
In order to ensure the safety of the helicopter and the airborne electronic and electrical equipment thereof, the helicopter must be subjected to lightning protection design protection and lightning protection design verification, so that the influence of lightning stroke on the flight safety of the helicopter is reduced to the greatest extent.
In 90 th learning European and American advanced technology tides, china also successively establishes a series of aircraft lightning standards, but the lightning standards cannot be well absorbed and applied due to the weakness of basic industry and aviation technology. With the increase of helicopter demands, china also begins to pay attention to research and assessment of helicopter lightning protection design, and in 2011, airworthiness evidence of full-model lightning protection design verification is finished on an AC313 helicopter for the first time.
With the increasing demand, the produced composite lightning protection measures may not meet the design requirement and need to be repaired due to various principles, but the research on repairing the composite lightning protection design measures of the helicopter is not involved.
Disclosure of Invention
Aiming at the technical problems, the application provides a helicopter composite material lightning protection capability repairing method, which comprises the following steps:
fixing a diversion copper strip on a composite structural member of a lightning zone of the helicopter;
laying a copper net with a glue film on the composite structural member of the lightning partition of the helicopter;
and covering glass fibers on the copper mesh with the adhesive film.
Preferably, the copper diversion strips are used as a lightning active attachment area and a lightning current main diversion channel.
Preferably, the fixing the diversion copper strip on the composite structural member of the lightning partition of the helicopter comprises:
and adhering the diversion copper strips to the composite structural member of the lightning partition of the helicopter by using glue.
Preferably, the laying of the adhesive film copper net on the composite structural member of the lightning zone of the helicopter comprises the following steps:
laying the copper mesh with the adhesive film on the composite structural member of the lightning partition of the helicopter in a partition mode based on secondary hot press molding; the maximum gap between the copper nets with the adhesive films laid in the subareas cannot be larger than 2mm.
Preferably, the diversion copper strips are stuck between the copper meshes with adhesive films laid in the partition mode.
Preferably, the maximum gap between the diversion copper belt and the adhesive film copper net cannot be larger than 2mm.
Preferably, the covering glass fiber on the copper mesh with adhesive film comprises:
solidifying the glass fiber on the copper mesh with the adhesive film; wherein, the glass fiber is used for protecting the copper mesh with the adhesive film.
Preferably, the fixing the diversion copper strip on the composite structural member of the lightning partition of the helicopter comprises:
and adhering the diversion copper strips to the composite structural member of the lightning partition of the helicopter by using conductive adhesive.
The beneficial technical effects of the application are as follows:
the application provides a method for repairing lightning protection capability of a helicopter composite material, which can effectively repair a composite material structural member which does not have the lightning protection capability until the lightning protection design requirement is met.
Drawings
FIG. 1 is a schematic illustration of a lightning strike test provided in accordance with an embodiment of the application;
FIG. 2 is a schematic illustration of a lightning strike test provided by a second embodiment of the application;
fig. 3 is a schematic diagram of a zoned copper mesh according to an embodiment of the present application.
Detailed Description
Referring to fig. 1-3, the application aims at the composite structural member manufactured by the prior helicopter, and performs lightning protection repair on the prior structural member according to the newly added lightning protection design requirement on the basis of not performing the lightning protection design, so that the prior structural member has the required lightning protection capability.
On one hand, the scrapping of the original manufactured composite structural member can be avoided, the unnecessary huge loss is reduced, meanwhile, the possibility of repairing unqualified parts produced by the composite structural member is provided, and the production qualification rate is improved; on the other hand, it is possible to provide technical possibilities for adding lightning protection capability to older helicopters.
The method for repairing the lightning protection capability of the helicopter composite material provided by the application can effectively repair the composite material structural member which does not have the lightning protection capability until the lightning protection design requirement is met.
The helicopter composite structural member is used for a 1-zone, a 2-zone or a 3-zone diversion zone of a lightning zone of a helicopter, and the like, and can be directly attached by lightning, swept and attached or required to bear diversion of lightning current, and the structure is broken down and structural materials are ablated due to the huge electromagnetic force, impact force and the like of the lightning, or colloid in the composite material loses the original function under high temperature and high pressure caused by high current.
Therefore, in order to ensure that the composite structural member of the helicopter is not damaged by lightning strike, thereby protecting the safety of the helicopter, equipment and personnel, the lightning protection capability is restored by adopting the measures of laying a copper net with a rubber film on the composite structural member.
Meanwhile, in order to strengthen the current carrying capacity, according to the difference of the composite structural member in a helicopter area and the difference of lightning diversion channel designs, a diversion copper strip can be properly added to serve as a lightning current diversion strip, and meanwhile, the structural member is protected, so that the possibility of being attached by sweeping is reduced; for the structural member with larger part size, a sectional laying mode can be adopted; the composite structural member is protected by adopting the guide strips and the copper net at the same time, and is repaired by adopting a twice curing process.
In one implementation, taking a helicopter tail beam skin composite material structural member tail beam as an example, making a repair scheme, and making a typical sample of the tail beam structural member after adopting lightning protection repair measures for lightning stroke test verification.
The bottom, the left side wall plate and the right side wall plate of the tail beam of the helicopter are large-size structural members, belong to lightning strike subareas 2 and 3 of the helicopter, are possibly attached by lightning sweep and conduct lightning current, and the tail beam section is of a composite material structure and has no lightning current diversion main channel.
The repairing scheme adopted by the application is as follows:
1) Solidifying a copper bar on each of the left and right side wall plates as a lightning active attachment area and simultaneously as a lightning current main diversion channel;
2) The bottom of the tail beam, the left and right side wall plates are respectively laid by using LOCTITE EA9845 LC 020-015EARO prepreg copper mesh (or similar products), and a layer of glass fiber is covered on the copper mesh;
3) The copper bar and the copper mesh are repaired by adopting a twice curing process.
In the embodiment of the application, a typical copper mesh laying skin structure and a copper mesh and copper strip laying skin structure are selected for test and examination through using and layering analysis on a helicopter tail beam skin composite material, and the lightning protection capability of a tail beam after lightning protection repair, the reliability of a structural member manufacturing process and the like are verified as shown in table 1.
TABLE 1
And selecting a No. 1 discharge point for test and examination on the laminated board and honeycomb board test piece laid by the copper net, wherein the discharge point is shown in figure 1.
For the laminated board and honeycomb board test piece with copper wire net laid and copper bar protection, two discharge points 1# and 2# are selected for test and examination, and the positions of the discharge points are shown in figure 2.
Wherein, the lightning 2A area waveform is applied to the 1# discharge point, and the lightning 1B area waveform is applied to the 2# discharge point.
According to the method, according to the damage condition analysis of the test piece after the lightning stroke test, the breakdown phenomenon of the test piece does not occur, the composite material structure under the protection of the copper net is relatively intact, and the lightning protection design requirement is met.
Claims (7)
1. A method for repairing lightning protection capability of a helicopter composite material is characterized by comprising the following steps:
fixing a diversion copper strip on a composite structural member of a lightning zone of the helicopter;
laying a copper net with a glue film on the composite structural member of the lightning partition of the helicopter;
covering glass fibers on the copper mesh with the adhesive film;
wherein, lay on helicopter thunderbolt subregion combined material structure and take glued membrane copper mesh, include:
laying the copper mesh with the adhesive film on the composite structural member of the lightning partition of the helicopter in a partition mode based on secondary hot press molding; the diversion copper strips are stuck between the copper nets with the adhesive films laid in the partition mode.
2. The method for repairing lightning protection capability of helicopter composite material according to claim 1, wherein the copper diversion strips are used as active attachment areas of lightning and main diversion channels of lightning current.
3. The method for repairing lightning protection capability of a composite material of a helicopter according to claim 1, wherein the fixing of the guiding copper strip on the composite material structural member of the lightning partition of the helicopter comprises:
and adhering the diversion copper strips to the composite structural member of the lightning partition of the helicopter by using glue.
4. A method of repairing lightning protection capability of a helicopter composite material according to claim 3 wherein the maximum gap between the copper meshes with adhesive films laid in sections is not greater than 2mm.
5. A method for repairing lightning protection capability of helicopter composite material according to claim 1,
the maximum gap between the diversion copper belt and the adhesive film copper net cannot be larger than 2mm.
6. The helicopter composite lightning protection capability restoration method of claim 1, wherein the covering of glass fibers on the glued membrane copper mesh comprises:
solidifying the glass fiber on the copper mesh with the adhesive film; wherein, the glass fiber is used for protecting the copper mesh with the adhesive film.
7. The method for repairing lightning protection capability of a composite material of a helicopter according to claim 1, wherein the fixing of the guiding copper strip on the composite material structural member of the lightning partition of the helicopter comprises:
and adhering the diversion copper strips to the composite structural member of the lightning partition of the helicopter by using conductive adhesive.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111391750.2A CN113928576B (en) | 2021-11-19 | 2021-11-19 | Helicopter composite material lightning protection capability repairing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111391750.2A CN113928576B (en) | 2021-11-19 | 2021-11-19 | Helicopter composite material lightning protection capability repairing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113928576A CN113928576A (en) | 2022-01-14 |
| CN113928576B true CN113928576B (en) | 2023-09-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111391750.2A Active CN113928576B (en) | 2021-11-19 | 2021-11-19 | Helicopter composite material lightning protection capability repairing method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116513473A (en) * | 2023-04-10 | 2023-08-01 | 沪东中华造船(集团)有限公司 | Correcting method for deformation of landing grid of ship helicopter |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US7686905B2 (en) * | 2005-09-06 | 2010-03-30 | The Boeing Company | Copper grid repair technique for lightning strike protection |
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| CN106147703A (en) * | 2015-04-03 | 2016-11-23 | 深圳光启尖端技术有限责任公司 | A kind of Wave suction composite material and preparation method thereof |
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| CN113928576A (en) | 2022-01-14 |
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