CN114180083B - Method for conducting electricity between composite structural members by using copper cups - Google Patents
Method for conducting electricity between composite structural members by using copper cups Download PDFInfo
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- CN114180083B CN114180083B CN202111382487.0A CN202111382487A CN114180083B CN 114180083 B CN114180083 B CN 114180083B CN 202111382487 A CN202111382487 A CN 202111382487A CN 114180083 B CN114180083 B CN 114180083B
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- copper
- fastener
- composite structural
- cup
- structural member
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- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 title claims abstract description 147
- 229910052802 copper Inorganic materials 0.000 title claims abstract description 147
- 239000010949 copper Substances 0.000 title claims abstract description 147
- 239000002131 composite material Substances 0.000 title claims abstract description 78
- 238000000034 method Methods 0.000 title claims abstract description 20
- 230000005611 electricity Effects 0.000 title claims description 11
- 239000004744 fabric Substances 0.000 claims description 27
- 239000011521 glass Substances 0.000 claims description 21
- 239000002313 adhesive film Substances 0.000 claims description 13
- 241001079814 Symphyotrichum pilosum Species 0.000 claims description 8
- 235000004224 Typha angustifolia Nutrition 0.000 claims description 8
- 239000000853 adhesive Substances 0.000 claims description 7
- 230000001070 adhesive effect Effects 0.000 claims description 7
- 238000005498 polishing Methods 0.000 claims description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 239000003973 paint Substances 0.000 claims description 6
- 229910052751 metal Inorganic materials 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 5
- 239000004593 Epoxy Substances 0.000 claims description 4
- NVKTUNLPFJHLCG-UHFFFAOYSA-N strontium chromate Chemical compound [Sr+2].[O-][Cr]([O-])(=O)=O NVKTUNLPFJHLCG-UHFFFAOYSA-N 0.000 claims description 4
- 241000587161 Gomphocarpus Species 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 3
- 238000012856 packing Methods 0.000 claims description 2
- 239000004922 lacquer Substances 0.000 claims 3
- 230000001681 protective effect Effects 0.000 claims 3
- 239000012945 sealing adhesive Substances 0.000 abstract description 5
- 229920000049 Carbon (fiber) Polymers 0.000 abstract description 3
- 239000004917 carbon fiber Substances 0.000 abstract description 3
- 238000012423 maintenance Methods 0.000 abstract description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 abstract description 3
- 238000007789 sealing Methods 0.000 abstract description 3
- 239000003365 glass fiber Substances 0.000 abstract description 2
- 239000000123 paper Substances 0.000 abstract description 2
- 239000002519 antifouling agent Substances 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 238000012546 transfer Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 208000025274 Lightning injury Diseases 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 238000006467 substitution reaction 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
- Laminated Bodies (AREA)
Abstract
The application discloses a conductive treatment method between composite structural members realized by copper cups, which comprises the steps of establishing a conductive path between the composite structural members with connection relation on an aircraft; the parts used by the conductive path comprise a copper net, a copper sheet, a gasket, a fastener, a supporting plate nut, a countersunk self-plugging rivet and a copper cup. The application has the characteristics of simple, direct and effective current conduction path and low impedance; the method can be used at any part of the connecting area of the composite material structure containing glass fiber, carbon fiber and paper honeycomb, which is required to realize circuit conduction; bonding the conductive copper cup at the joint of the fastener; the assembly surface is attached by using an insulating sealing adhesive tape to play a role in sealing; the structure is detachable, and the maintenance is convenient.
Description
Technical Field
The application relates to the field of lightning protection of organisms, in particular to a conductive treatment method between composite structural members realized by copper cups.
Background
The aircraft structure is made of electrically conductive material (aluminum alloy, carbon fiber, etc.), and as lightning strikes develop from cloud to ground, the aircraft structure provides a "short-circuited" path, and the aircraft becomes part of the lightning path. When a lightning strike occurs, at least two lightning strike points are required: an inlet and an outlet. Since the aircraft typically proceeds in a horizontal plane, the inlet is typically at the front of the aircraft (nose, engine nacelle, wing tip, etc.), and the outlet is at the rear of the aircraft (wing tip, rear of vertical and horizontal stabilizers, landing gear, etc.), each strike of lightning being directed rearward along the fuselage or engine nacelle.
The design of an aircraft is based on lightning protection, rather than lightning protection. The principle of the lightning rod is that the energy of lightning is introduced into the ground, so that the damage of the lightning to a target is avoided; since the aircraft is flying in the air, lightning cannot be guided underground. Federal aviation regulations prescribe that after a lightning strike, the aircraft, whether its damaged portion is motor equipment, electronics, or structurally, may not affect continued safe flight of the aircraft, so the design of the aircraft should ensure that the consequences of the lightning strike are minimized and that the aircraft continue to fly after suffering the lightning strike, safely landing. The aircraft structure should therefore be designed for good electrical conductivity (low electrical resistance) and avoid overheating during lightning strikes.
To achieve electrical continuity, metal mesh, such as copper mesh, is often laid in the composite structure. When the electric lap joint treatment is carried out among different composite material structural members of the existing helicopter, the circuit conduction is usually realized by using fasteners, supporting plate nuts, copper sheets or rivets and the like. When the structure can realize electric lap joint without rivets, a mode of wrapping copper sheets back at the outer side is adopted to lead the supporting plate nut to be in direct contact with the copper net of the composite structural member so as to realize circuit conduction; when the structural form does not allow the copper sheet to be wrapped back outside, and the rivet is needed to be adopted for electric lap joint, if special treatment is not carried out at the rivet head, the efficiency of current transmission from the rivet head to the copper net of the composite structural member is very low, and at the moment, the conduction between the composite structural members is not really realized.
Disclosure of Invention
The application aims to provide a conductive treatment method between composite structural members by using copper cups, which can solve the defect that conduction is not conducted when rivets are used for forming conductive paths between the composite structural members, has wide application range, is simple to implement and high in conductive efficiency, and is a circuit conduction method which is needed in a helicopter structure.
In order to realize the tasks, the application adopts the following technical scheme:
a method for conducting electricity between composite structural members by using copper cups comprises the steps of establishing an electric conduction path between the composite structural members with connection relation on an airplane; the part that electrically conductive route utilized includes first copper net, copper sheet, packing ring, fastener, layer board nut, countersunk self-plugging rivet, copper cup, second copper net, wherein:
a copper sheet and a first copper net are paved below the first outermost layer glass cloth of the composite material structural member, a layer of structural adhesive film is paved between the copper sheet and the first outermost layer glass cloth, the copper sheet is attached to the first copper net, a layer of structural adhesive film is paved between the first copper net and the inner side carbon cloth, the copper sheet is paved around each fastener on the composite material structural member, and the electric connection between the fastener and the copper sheet is realized through a gasket;
a copper cup and a second copper mesh are paved below the second outermost layer glass cloth of the composite material structural member, and a layer of conductive adhesive is paved between the copper cup and the second copper mesh; the copper cup is a structure formed by pressing a countersink for fixing the countersunk head of the self-plugging rivet on the copper sheet; for countersunk self-plugging rivets which are required to be electrically connected and overlapped on the composite structural member, riveting the countersunk self-plugging rivets into the composite structural member and the supporting plate of the supporting plate nut from the copper cup, riveting the supporting plate nut on the inner side of the composite structural member, and simultaneously enabling the countersunk self-plugging rivet heads to be positioned in the countersink; the copper cup is also provided with a through hole for passing through the fastener.
Further, the overlap joint amount between the structural adhesive film laid between the copper sheet and the outermost glass cloth and the structural adhesive film laid between the copper net and the inner carbon cloth is 5mm.
Further, the spacing between the copper sheets is not more than 200mm.
Further, the composite structural member, is secured with fasteners such that the washer and the pallet nut form a conductive path.
Further, polishing the outermost layer glass cloth within a shadow area of phi 18mm from the axis of the fastener before installing the fastener on the composite material structural member, wherein the polishing area is not sprayed with paint, and other parts are coated with primer.
Further, polishing the outermost glass cloth of the assembly area of the copper cup and the composite structural member until the copper mesh is exposed, and spraying a metal surface paint and a layer of strontium chromate epoxy insulating primer on the outer surface of the copper cup.
Further, the protective paint layers on the two parts of the contact surface of the fastener head and the gasket are removed between the fastener head and the gasket, the gasket removes the protective paint layer on the contact surface of the gasket and the copper cup, and the supporting plate nut removes the protective paint layer on the contact surface of the supporting plate nut and the countersunk self-plugging rivet upsetting head.
Further, the copper cup has a dimension Φ 1 The diameter of the countersunk pit is 0.5-1.5mm larger than that of the nail rod of the fastener, and the countersunk pit size phi for installing the countersunk head blind rivet 2 Is equal to the diameter of the rivet stem of the countersunk head self-plugging rivet, and the hole spacing value d 1 The distance between the supporting plate nut and the rivet hole is equal to the edge distance d 2 、d 3 = (2 x countersunk head blind rivet shank diameter+1), copper cup countersink depth value h 1 The countersink angle alpha of the copper cup is equal to the countersink rivet head angle.
Further, lightning strikes cause current at the parts such as the composite material skin or the flap on the outer surface of the fuselage, the current sequentially flows into the gasket and the fastener nail head through the copper sheet via the first copper mesh paved in the composite material structural member, then flows into the fastener nail rod, and flows into the supporting plate nut via the fastener rod end.
Compared with the prior art, the application has the following technical characteristics:
1. the electric conduction efficiency is high: the current conduction path is simple, direct and effective, and the impedance is low.
2. The application range is wide: the method can be used at any part where the connection area of the composite material structure containing glass fiber, carbon fiber and paper honeycomb is required to realize circuit conduction.
3. The weight is light: the conductive copper cup is only bonded at the joint of the fastener, so that the weight is light.
4. The installation is simple, and the maintenance is convenient: the insulating sealing adhesive tape is used for enabling the assembly surface to be attached and plays a role in sealing, and the installation is simple; the structure is detachable, and the maintenance is convenient.
Drawings
FIG. 1 is a schematic diagram of a circuit conducting structure according to the present application;
FIG. 2 is a schematic diagram of a current transfer path of the present application;
FIG. 3 is a schematic view of the composite structure I of the present application with copper mesh and copper sheets laid;
FIG. 4 is a schematic diagram of a copper mesh and copper cup laid in the composite structural member II;
FIG. 5 is a schematic diagram of the preparation of a fastener prior to assembly;
FIG. 6 is a schematic view of the copper cup structure.
Numbering represents: 1 composite structural member I,2 first copper net, 3 copper sheet, 4 structural adhesive film, 5 washer, 6 fastener, 7 fastener pin head, 8 first outmost glass cloth, 9 inboard carbon cloth, 10 insulating joint strip, 11 structural member, 12 layer board nut, 13 countersunk self-plugging rivet upsets, 14 countersunk self-plugging rivet, 15 countersunk self-plugging rivet pin head, 16 composite structural member II,17 second outmost glass cloth, 18 copper cup, 19 conductive adhesive, 20 second copper net, 21 other layers, 22 assembly area, 23 protective paint layer, 24 protective paint layer.
Detailed Description
Referring to the drawings, the application provides a conductive treatment method between composite structural members by using copper cups, and for a composite structural member I1 and a composite structural member II16 which have a connection relationship on an aircraft, an insulating sealing adhesive tape 10 exists between the two structural members, the following method is adopted for conducting treatment between structural members:
as shown in fig. 1, the conductive path is composed of a first copper mesh 2, a copper sheet 3, a washer 5, a fastener 6 (fastener nail 7, fastener shank), a carrier nut 12, a blind rivet 14 (blind rivet head 13, blind rivet nail 15), a copper cup 18, and a second copper mesh 20.
Step 1, laying a conductive path in a composite structural member I1
As shown in fig. 1, a copper sheet 3 and an ECS0027 first copper net 2 are paved under a first outermost glass cloth 8, a layer of ECS0004.24 structural adhesive film 4 is paved between the copper sheet 3 and the first outermost glass cloth 8, the copper sheet 3 is attached to the ECS0027 first copper net 2, a layer of ECS0004.24 structural adhesive film 4 is paved between the ECS0027 first copper net 2 and an inner carbon cloth 9, and the lap joint amount between the two layers of structural adhesive films is 5mm; wherein, copper sheets 3 are laid around each fastener 6, the interval between the copper sheets 3 is not more than 200mm, and the electrical connection between the fastener and the copper sheets is realized through washers 5.
Step 2, laying a conductive path in the composite structural member II16
The copper cup 18 and the ECS0027 second copper net 20 are paved below the outermost glass cloth 17 of the composite structural member II16, and a layer of ECS2184.10 conductive adhesive 19 is paved between the copper cup 18 and the ECS0027 second copper net 20; wherein, the copper cup 18 is a structure formed by pressing a countersink for fixing a rivet countersink on the copper sheet; for the countersunk self-plugging rivet 14 which needs conductive lap joint of the composite structural member II16, the countersunk self-plugging rivet 14 is riveted into the composite structural member II16 from the copper cup 18, so that the countersunk self-plugging rivet sequentially passes through the outermost glass cloth 17, other layers 21 and the structural member 11 at the bottom of the composite structural member II16, finally passes through the supporting plate of the supporting plate nut 12, rivets the supporting plate nut 12 on the inner side of the composite structural member II16, and simultaneously positions the countersunk self-plugging rivet head 15 in the countersink; the copper cup 18 is also provided with a through hole for passing through the fastener.
Step 3, conducting path between composite structural member I1 and composite structural member II16
The composite structural members I1, II16 are secured with fasteners such that the washer 5 and the blade nut 12 form an electrically conductive path.
As shown in fig. 3, before the composite structural member I1 is provided with a fastener, polishing the outermost layer of glass cloth within a shadow area of phi 18mm from the axis of the fastener, wherein the polished area is not sprayed with paint, and other parts are coated with primer ECS2067;
as shown in fig. 4, polishing the outermost glass cloth of the assembly area 22 of the copper cup 18 and the composite structural member II16 until the copper mesh is exposed, and spraying a metal surface paint ECS2209 and a 1-layer strontium chromate epoxy insulating primer DHS186-111 on the outer surface of the copper cup 18;
as shown in fig. 5, the protective paint layer 23 on the contact surface of the fastener head 7 and the washer is removed between the fastener head 7 and the washer 5, the washer 5 removes the protective paint layer 24 on the contact surface of the washer 5 and the copper cup 18, and the supporting plate nut 12 removes the protective paint layer on the contact surface of the supporting plate nut and the countersunk head 13.
As shown in fig. 6, the through hole dimension Φ of the copper cup 1 Determined by the actual installed fastener diameter dimensions (generally, # 1 The value is 0.5-1.5mm larger than the diameter of the nail rod of the fastener), and the countersink size phi of the mounting rivet 2 Determined by shank diameter (in general, phi 2 A value equal to the diameter of the rivet shank), a hole spacing value d 1 Should be equal to the distance between the pallet nut 12 and the rivet hole, the margin value d 2 、d 3 Determined by shank diameter (in general, d 2 、d 3 = (2 x countersunk head blind rivet shank diameter+1) mm), copper cup countersink depth value h 1 The depth of the countersunk head 15 of the self-plugging rivet is equal, and the countersink angle alpha of the copper cup is equal to the angle of the countersunk head 15 of the self-plugging rivet.
As shown in fig. 2, the current transfer path: the lightning stroke and the like cause current at the parts of the composite material skin or the flap and the like on the outer surface of the fuselage, the current sequentially flows into the gasket 5 and the fastener nail rod 6 through the copper sheet 3 by passing through the first copper mesh 2 paved in the composite material structural member I1, flows into the fastener nail rod 6 through the fastener rod end, and flows into the supporting plate nut 12 through the fastener rod end, and because the supporting plate nut 12 is in direct contact with the countersunk blind rivet upsetting head 13, the current sequentially passes through the countersunk blind rivet nail rod 14, the countersunk blind rivet nail head 15 and the copper cup 18 after flowing into the countersunk blind rivet upsetting head 13, then flows into the second copper mesh 20 of the ECS0027 through the ECS2184.10 conductive adhesive 19, and finally the current flows to the rear part of the fuselage along the fuselage skin.
The conductive treatment method between the composite structural member I1 and the composite structural member II16 can be applied between a flap and a fuselage skin of an airplane, for example.
The application is suitable for the situation that the composite structural member cannot realize direct contact of the supporting plate nut and the copper sheet to transfer current by using the outer coated copper sheet, thereby solving the problem that the circuit conduction is realized by using rivets; according to the application, the copper net and the copper sheet are paved in the composite material structure, the structural circuit conduction is realized by reasonably utilizing the fasteners, the supporting plate nuts, the rivets and the copper cups, and the problem that the circuit conduction cannot be realized among the composite material structural members can be solved; according to the application, the composite materials are separated by the insulating sealing adhesive tape, the assembly surface is uneven due to the adhesion of the electric lap joint copper sheets, and the adhesive tape can enable the structure assembly to be more fit and play a role in sealing; according to the application, the copper mesh and the copper sheet are simultaneously paved in the composite material part and bonded by using the structural adhesive film, so that the possibility that the copper sheet is easy to fall off after polishing the outer glass cloth is avoided; the application utilizes the standard component to realize the connection between structural components and the circuit conduction at the same time, thereby achieving two purposes; the current transmission path is simple, direct and effective, and the problem of low conduction efficiency between composite structural members is solved; according to the application, because the copper cup is required to be provided with the rivet prefabricated hole, the assembly precision is considered, and the copper cup is a rear workpiece, namely, the copper cup and the composite structural member are not subjected to furnace curing together; the copper cup is fixed on the machine body structure by the conductive adhesive, so that the copper cup can play roles of fixing and conducting at the same time; the copper cup outer side metal surface paint ECS2209 has the function of improving the adhesion of the strontium chromate epoxy insulating primer so as to improve the anti-corrosion period; the application can be applied to the conductive treatment between the composite structural members of the internal structure of the fuselage structure, and the insulating sealing adhesive tape between the structural members is canceled at the moment.
The above embodiments are only for illustrating the technical solution of the present application, and are not limiting thereof; although the application has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced equally; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present application, and are intended to be included in the scope of the present application.
Claims (7)
1. The method for conducting the electricity between the composite structural members by using the copper cups is characterized by comprising the steps of establishing an electricity conducting path between a composite structural member I (1) and a composite structural member II (16) which are connected on an aircraft; the part that electrically conductive route utilized includes first copper net (2), copper sheet (3), packing ring (5), fastener (6), layer board nut (12), countersunk head self-plugging rivet (14), copper cup (18), second copper net (20), wherein:
the method comprises the steps that a copper sheet (3) and a first copper mesh (2) are paved below a first outermost layer glass cloth (8) of a composite material structural member I (1), a layer of structural adhesive film (4) is paved between the copper sheet (3) and the first outermost layer glass cloth (8), the copper sheet (3) is attached to the first copper mesh (2), a layer of structural adhesive film (4) is paved between the first copper mesh (2) and an inner side carbon cloth (9), the copper sheet (3) is paved around each fastener (6) on the composite material structural member I (1), and the electric connection between the fasteners (6) and the copper sheet (3) is realized through gaskets (5);
a copper cup (18) and a second copper mesh (20) are paved below the second outermost glass cloth (17) of the composite structural member II (16), and a layer of conductive adhesive (19) is paved between the copper cup (18) and the second copper mesh (20); wherein, the copper cup (18) is a structure formed by pressing a countersink for fixing the countersunk head (15) of the countersunk head self-plugging rivet on the copper sheet; for a countersunk self-plugging rivet (14) which needs conductive lap joint of a composite structural member II (16), riveting the countersunk self-plugging rivet (14) into a supporting plate of the composite structural member II (16) and a supporting plate nut (12) from a copper cup (18), riveting the supporting plate nut (12) on the inner side of the composite structural member II (16), and simultaneously enabling a countersunk self-plugging rivet head (15) to be positioned in the countersink; the copper cup (18) is also provided with a through hole for passing through the fastener (6);
polishing the outermost glass cloth of an assembly area (22) of the copper cup (18) and the composite structural member II (16) until the copper mesh is exposed, and spraying a metal surface paint and a layer of strontium chromate epoxy insulating primer on the outer surface of the copper cup (18);
lightning strikes cause current at the composite material skin or flap part of the outer surface of the fuselage, the current sequentially flows into a gasket (5) through a copper sheet (3) through a first copper mesh (2) paved in a composite material structural member I (1), flows into a fastener (6) nail rod after passing through a fastener nail head (7), flows into a supporting plate nut (12) through the rod end of the fastener (6), and flows into the countersunk head (13) through direct contact of the supporting plate nut (12) and the countersunk head (13), so that the current sequentially flows into the countersunk head (13) and then sequentially passes through the countersunk head (15) and a copper cup (18), flows into a second copper mesh (20) through a conductive adhesive (19), and finally flows into the rear part of the fuselage along the fuselage skin.
2. The method for conducting electricity between composite structural members by using copper cups according to claim 1, characterized in that the overlap between the structural adhesive film (4) laid between the copper sheet (3) and the first outermost glass cloth (8) and the structural adhesive film (4) laid between the first copper net (2) and the inner carbon cloth (9) is 5mm.
3. The method for conducting electricity between structural members of composite material realized by means of copper cups according to claim 1, characterized in that the spacing between the copper sheets (3) is not more than 200mm.
4. The method of conducting electricity between composite structural members using copper cups according to claim 1, wherein the composite structural members I (1), II (16) are fastened using fasteners such that the washers (5) and the pallet nuts (12) form an electrically conductive path.
5. The method for conducting electricity between composite structural members by using copper cups according to claim 1, wherein the outermost glass cloth in a shadow area of phi 18mm from the axis of the fastener (6) is polished before the fastener (6) is installed in the composite structural member I (1), the polished area is not painted, and other parts are primed.
6. A method of conducting electricity between composite structural members using copper cups according to claim 1, characterized in that the protective lacquer layer (23) on both parts of the contact surface of the fastener head (7) with the washer (5) is removed between the fastener head (7) and the washer (5), the washer (5) removes the protective lacquer layer (24) on the contact surface with the copper cup (18), and the pallet nut (12) removes the protective lacquer layer on the contact surface with the countersunk blind rivet head (13).
7. The method for conducting electricity between structural members of composite material using copper cups according to claim 1, wherein the dimensions Φ of the copper cups are 1 The diameter of the countersink is 0.5-1.5mm larger than that of the nail rod of the fastener, and the countersink size phi of the countersunk head blind rivet (14) is arranged 2 Is equal to the diameter of the rivet stem of the countersunk head self-plugging rivet, and the hole spacing value d 1 Is equal to the distance between the supporting plate nut (12) and the rivet hole, and the margin value d 2 、d 3 = (2 x countersunk head blind rivet shank diameter+1), copper cup countersink depth value h 1 Equal to the depth of the countersunk head of the blind rivet, the countersink angle of the copper cupThe degree alpha is equal to the angle of the countersunk blind rivet head (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111382487.0A CN114180083B (en) | 2021-11-19 | 2021-11-19 | Method for conducting electricity between composite structural members by using copper cups |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111382487.0A CN114180083B (en) | 2021-11-19 | 2021-11-19 | Method for conducting electricity between composite structural members by using copper cups |
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| CN114180083A CN114180083A (en) | 2022-03-15 |
| CN114180083B true CN114180083B (en) | 2023-09-01 |
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| ES2376323B1 (en) * | 2009-02-27 | 2013-01-24 | Airbus Operations, S.L. | IMPROVEMENT OF PROTECTION AGAINST DIRECT IMPACT OF RAYS IN RIVED PANEL AREAS IN CFRP. |
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| CN114180083A (en) | 2022-03-15 |
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