CN114180083A - Method for conducting between composite material structural members by using copper cup - Google Patents
Method for conducting between composite material structural members by using copper cup Download PDFInfo
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- CN114180083A CN114180083A CN202111382487.0A CN202111382487A CN114180083A CN 114180083 A CN114180083 A CN 114180083A CN 202111382487 A CN202111382487 A CN 202111382487A CN 114180083 A CN114180083 A CN 114180083A
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- fastener
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- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 title claims abstract description 149
- 229910052802 copper Inorganic materials 0.000 title claims abstract description 149
- 239000010949 copper Substances 0.000 title claims abstract description 149
- 239000002131 composite material Substances 0.000 title claims abstract description 84
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000012545 processing Methods 0.000 claims abstract description 3
- 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
- 239000002519 antifouling agent Substances 0.000 claims description 11
- 241000587161 Gomphocarpus Species 0.000 claims description 9
- 239000000853 adhesive Substances 0.000 claims description 9
- 230000001070 adhesive effect Effects 0.000 claims description 9
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 241001079814 Symphyotrichum pilosum Species 0.000 claims description 5
- 235000004224 Typha angustifolia Nutrition 0.000 claims description 5
- 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
- 230000005611 electricity Effects 0.000 claims description 4
- 239000003973 paint 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
- 238000003825 pressing Methods 0.000 claims description 3
- 238000012856 packing Methods 0.000 claims description 2
- 238000007789 sealing Methods 0.000 abstract description 7
- 229920000049 Carbon (fiber) Polymers 0.000 abstract description 3
- 239000004917 carbon fiber Substances 0.000 abstract description 3
- 239000003365 glass fiber Substances 0.000 abstract description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 abstract description 2
- 239000000123 paper Substances 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 239000012945 sealing adhesive Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- WSNMPAVSZJSIMT-UHFFFAOYSA-N COc1c(C)c2COC(=O)c2c(O)c1CC(O)C1(C)CCC(=O)O1 Chemical compound COc1c(C)c2COC(=O)c2c(O)c1CC(O)C1(C)CCC(=O)O1 WSNMPAVSZJSIMT-UHFFFAOYSA-N 0.000 description 1
- 241000264877 Hippospongia communis Species 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000005536 corrosion prevention Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012423 maintenance Methods 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
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a method for realizing conductive processing between composite material structural members by utilizing a copper cup, which comprises the steps of establishing a composite material structural member with a connection relation on an airplane and a conductive path between the composite material structural members; 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 invention has the characteristics that the current conduction path is simple, direct and effective, and the impedance is low; the method can be used for any part needing to realize circuit conduction in the connection area of the composite material structure containing glass fiber, carbon fiber and paper honeycomb; only bonding the conductive copper cup at the joint of the fastener; the assembly surface is attached and plays a role in sealing by using an insulating sealing rubber strip; the structure is detachable and convenient to maintain.
Description
Technical Field
The invention relates to the field of lightning protection of an engine body, in particular to a method for conducting between composite material structural members by using a copper cup.
Background
Aircraft structures are made of electrically conductive materials (aluminum alloys, carbon fibers, etc.) and, since lightning strikes develop from the cloud to the ground, they provide a "short-circuit" path, and the aircraft becomes part of the lightning path. When a lightning strike occurs, at least two lightning strike points are required: one inlet and one outlet. Since the aircraft usually travels in a horizontal plane, the inlet is usually at the front of the aircraft (nose, 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.), with each stroke of lightning traveling backwards along the fuselage or nacelle.
The design of aircraft is based on lightning protection rather than lightning protection. The principle of the lightning rod is to introduce the energy of thunder into the ground, so as to avoid the damage of the thunder to a target; since the aircraft is flying in the air, lightning cannot be conducted underground. Federal aviation regulations stipulate that an aircraft cannot influence the continued safe flight of the aircraft after a lightning strike, whether the damaged part is electrical equipment, electronic equipment, or structurally, so the design of the aircraft should ensure that the consequences of the lightning strike are minimized, and that the aircraft continues to fly and land safely after the lightning strike. The aircraft structure should therefore be designed for good continuity (low resistance) to avoid overheating during lightning strikes.
To achieve circuit conduction, metal meshes such as copper meshes are often laid in composite structural members. When different composite material structural members of the existing helicopter are subjected to electric lap joint treatment, circuit conduction is usually realized by using fasteners, supporting plate nuts, copper sheets or rivets and the like. When the structure can realize electric lapping without rivets, the supporting plate nut is directly contacted with the copper mesh of the composite material structural member by adopting a mode of wrapping copper sheets at the outer side, so that circuit conduction is realized; when the structural form does not allow the copper sheet to be wrapped back on the outer side, and the rivet is needed to be used for electric lapping, if the rivet head is not specially processed, the efficiency of current transmitted from the rivet head to the copper mesh of the composite material structural member is very low, and at the moment, the conduction between the composite material structural members is not really realized.
Disclosure of Invention
The invention aims to provide a method for conducting between composite material structural members by using a copper cup, which can overcome the defect that conducting paths are not communicated when rivets are used for forming the conducting paths between the composite material structural members, has wide application range, simple implementation and high conducting efficiency, and is a circuit conducting method which is urgently needed by a helicopter structure.
In order to realize the task, the invention adopts the following technical scheme:
a method for realizing conductive processing between composite material structural members by using a copper cup comprises the steps of establishing a composite material structural member with a connection relation on an airplane and a conductive path between the composite material structural members; the parts that electrically conductive route utilized include copper mesh, copper sheet, packing ring, fastener, layer board nut, countersunk head self-plugging rivet, copper cup, copper mesh, wherein:
the composite material structural member is characterized in that a copper sheet and a copper net are laid under the outermost layer of glass cloth, a layer of structural adhesive film is laid between the copper sheet and the outermost layer of glass cloth, the copper sheet is attached to the copper net, a layer of structural adhesive film is laid between the copper net and the inner side of carbon cloth, the copper sheet is laid around each fastener on the composite material structural member, and the fasteners and the copper sheet are electrically connected through gaskets;
the composite structural member is characterized in that a copper cup and a copper mesh are laid under the outermost layer of glass cloth, and a layer of conductive adhesive is laid between the copper cup and the copper mesh; the copper cup is a structure formed by pressing a dimple for fixing the nail head of the countersunk self-plugging rivet on a copper sheet; for the composite material structural member needing the conductive lapped countersunk self-plugging rivet, riveting the countersunk self-plugging rivet into a composite material structural member and a supporting plate of a supporting plate nut from a copper cup, riveting the supporting plate nut on the inner side of the composite material structural member, and simultaneously enabling the rivet head of the countersunk self-plugging rivet to be positioned in the countersink; the copper cup is also provided with a through hole for passing through the fastener.
Furthermore, the lap joint quantity between the structural adhesive film paved between the copper sheet and the outermost glass cloth and the structural adhesive film paved between the copper net and the inner side carbon cloth is 5 mm.
Further, the spacing between the copper sheets is not more than 200 mm.
Further, the composite structural member is secured with the fastener such that the washer and the pallet nut form a conductive path.
Further, before the composite material structural member is installed on the fastener, the outermost glass cloth in the shadow area range which is 18mm away from the axis phi of the fastener is ground, the ground area is not painted, and other parts are painted with primer.
Further, polishing the outermost glass cloth of the assembly area of the copper cup and the composite material structural member until the copper mesh is exposed, and spraying metal surface paint and a layer of strontium chromate epoxy insulation primer on the outer surface of the copper cup.
Further, a protective paint layer on two parts of the contact surface of the nail head of the fastener and the gasket is removed between the nail head of the fastener and the gasket, the protective paint layer on the contact surface of the gasket and the copper cup is removed from the gasket, and the protective paint layer on the contact surface of the supporting plate nut and the pier head of the countersunk head blind rivet is removed from the supporting plate nut.
Further, the size Φ of the copper cup1The diameter of the counter sink is 0.5-1.5mm larger than the diameter of the nail rod of the fastener, and the counter sink size phi for installing the countersunk self-plugging rivet2Equal to the diameter of the rod of the countersunk self-plugging rivet and the hole spacing value d1Should be equal to the distance between the supporting plate nut and the rivet hole and the margin value d2、d3The depth value h of the copper cup countersink is equal to (2 +1) the diameter of the rod of the countersunk self-plugging rivet1Equal to the depth of the rivet head of the countersunk head self-plugging rivet, and the angle alpha of the countersink of the copper cup is equal to the angle of the rivet head of the countersunk head self-plugging rivet.
Further, lightning strike and the like cause current at the composite material skin or the cover and the like on the outer surface of the body, the current passes through the copper mesh laid in the composite material structural member, sequentially flows into the washer and the fastener pin head, then flows to the fastener pin rod, flows into the support plate nut through the fastener rod end, and directly contacts with the countersunk head blind rivet head due to the fact that the support plate nut and the countersunk head blind rivet head are directly contacted, the current sequentially passes through the countersunk head blind rivet pin rod, the countersunk head blind rivet pin head and the copper cup after flowing into the countersunk head blind rivet head, then flows to the copper mesh through the conductive adhesive, and finally flows to the rear part of the body along the body skin.
Compared with the prior art, the invention has the following technical characteristics:
1. the electric conduction efficiency is high: the current conduction path is simple, direct and effective, and has low impedance.
2. The application range is wide: the method can be used for any part needing to realize circuit conduction in the connection area of the composite material structure containing glass fiber, carbon fiber and paper honeycombs.
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. Simple installation, convenient maintenance: the assembly surface is attached and plays a role in sealing by using the insulating sealing rubber strip, and the installation is simple; the structure is detachable and convenient to maintain.
Drawings
FIG. 1 is a schematic diagram of a circuit conducting structure according to the present invention;
FIG. 2 is a schematic diagram of the current delivery path of the present invention;
FIG. 3 is a schematic view of the composite structural member I of the present invention laid with copper mesh and copper sheet;
FIG. 4 is a schematic view of a copper mesh and a copper cup laid on the composite structural member II;
FIG. 5 is a schematic illustration of the preparation of the fastener prior to assembly;
FIG. 6 is a schematic view of a copper cup structure.
Description of numbering: 1 composite material structure I, 2 copper mesh, 3 copper sheets, 4 structural adhesive films, 5 gaskets, 6 fasteners, 7 fastener nail heads, 8 outmost glass cloth, 9 inner side carbon cloth, 10 insulating sealing adhesive tapes, 11 structure parts, 12 supporting plate nuts, 13 countersunk self-plugging rivet heads, 14 countersunk self-plugging rivets, 15 countersunk self-plugging rivet nail heads, 16 composite material structure II, 17 outmost glass cloth, 18 copper cups, 19 conductive adhesive, 20 copper mesh, 21 other laying layers, 22 assembly areas, 23 protective paint layers and 24 protective paint layers.
Detailed Description
Referring to the accompanying drawings, the invention provides a method for realizing the conductive treatment between composite material structural members by using a copper cup, and for the composite material structural member I1 and the composite material structural member II16 which have a connection relation on an airplane, because an insulating sealing rubber strip 10 exists between the two, the conductive treatment between the structural members is carried out by adopting the following method:
the conductive path is composed of a copper mesh 2, a copper sheet 3, a washer 5, a fastener 6 (a fastener nail head 7 and a fastener nail rod), a supporting plate nut 12, a countersunk blind rivet 14 (a countersunk blind rivet head 13 and a countersunk blind rivet head 15), a copper cup 18 and a copper mesh 20 as shown in fig. 1.
As shown in fig. 1, a copper sheet 3 and an ECS0027 copper mesh 2 are laid under an outermost layer of glass cloth 8 of a composite material structural member I1, an ECS0004.24 structure adhesive film 4 is laid between the copper sheet 3 and the outermost layer of glass cloth 8, the copper sheet 3 is adhered to the ECS0027 copper mesh 2, an ECS0004.24 structure adhesive film 4 is laid between the ECS0027 copper mesh 2 and an inner side carbon cloth 9, and the lap joint amount between the two layers of structure adhesive films is 5 mm; wherein, copper sheets 3 are laid around each fastener 6, the spacing between the copper sheets 3 is not more than 200mm, and the electric connection between the fasteners and the copper sheets is realized through the gasket 5.
The composite material structural member II16 is characterized in that a copper cup 18 and an ECS0027 copper mesh 20 are laid under the outermost layer of glass cloth 17, and a layer of ECS2184.10 conductive adhesive 19 is laid between the copper cup 18 and the ECS0027 copper mesh 20; wherein, the copper cup 18 is a structure formed by pressing a dimple for fixing a rivet countersunk head on a copper sheet; for the composite material structural part II16, riveting the countersunk self-plugging rivet 14 into the composite material structural part II16 from the copper cup 18, enabling the countersunk self-plugging rivet 14 to sequentially penetrate through the outermost glass cloth 17, other layers 21 and the structural part 11 at the bottom on the composite material structural part II16, and finally penetrating through a supporting plate of a supporting plate nut 12, riveting the supporting plate nut 12 at the inner side of the composite material structural part II16, and enabling the head 15 of the countersunk self-plugging rivet to be located in the countersink; the copper cup 18 is also provided with a through hole for passing through the fastener.
The composite structure I1 and the composite structure II16 are fastened with fasteners such that the washer 5 and the pallet nut 12 form a conductive path.
As shown in fig. 3, before the fastener is installed in the composite material structural member I1, the outermost glass cloth in the shadow area range of 18mm from the axis phi of the fastener is ground, the ground area is not painted, and other parts are painted with primer ECS 2067;
as shown in fig. 4, the outermost glass cloth of the assembly area 22 of the copper cup 18 and the composite structural member II16 is ground until the copper mesh is exposed, and the outer surface of the copper cup 18 is sprayed with metal surface paint ECS2209 and 1 layer of strontium chromate epoxy insulation primer DHS 186-111;
as shown in FIG. 5, the protective paint layer 23 on the contact surface between the fastener head 7 and the washer 5 is removed, the protective paint layer 24 on the contact surface between the washer 5 and the copper cup 18 is removed, and the protective paint layer on the contact surface between the carrier nut 12 and the countersunk blind rivet head 13 is removed.
As shown in FIG. 6, the via size of the copper cup is Φ1Determined by the actual installed fastener diameter size (generally, #)1Value 0.5-1.5mm larger than the diameter of the shank of the fastener), dimple size phi of the installation rivet2Determined by the shank diameter of the rivet (generally,. phi.)2Value equal to rivet shank diameter), hole spacing value d1Should be equal to the distance between the supporting plate nut 12 and the rivet hole and the margin value d2、d3Determined by the shank diameter (in general, d)2、d3The depth value h of the copper cup countersink is equal to (2 x the diameter of the screw rod of the countersunk head self-plugging rivet plus 1) mm)1Equal to the depth of the head 15 of the countersunk self-plugging rivet, and the angle alpha of the dimple of the copper cup is equal to the angle of the head 15 of the countersunk self-plugging rivet.
As shown in fig. 2, the current transfer path: lightning strike and the like cause current at the composite material skin or the cover and other parts on the outer surface of the machine body, the current passes through the copper mesh 2 laid in the composite material structural member I1, sequentially flows into the gasket 5 and the fastener nail head 7 through the copper sheet 3, then flows to the fastener nail rod 6, flows into the support plate nut 12 through the fastener rod end, and directly contacts with the countersunk blind rivet head 13, so the current sequentially passes through the countersunk blind rivet nail rod 14, the countersunk blind rivet head 15 and the copper cup 18 after flowing into the countersunk blind rivet head 13, then flows to the ECS0027 copper mesh 20 through the ECS2184.10 conductive adhesive 19, and finally flows to the rear part of the machine body along the machine body skin.
The conductive treatment method between the composite material structural part I1 and the composite material structural part II16 can be applied to the space between a cover and a fuselage skin on an airplane.
The invention is suitable for the situation that the composite material structural member can not realize the direct contact between the supporting plate nut and the copper sheet to transfer current by utilizing the copper sheet wrapped outside, thereby solving the problem that the circuit conduction is realized by utilizing the rivet; according to the invention, the copper mesh and the copper sheet are laid 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 between the composite material structural members can be solved; according to the invention, the composite materials are separated by using the insulating sealing adhesive tape, the assembly surface is not flat when the copper sheets are bonded and electrically lapped, and the adhesive tape can enable the structure to be more attached and play a role in sealing; according to the invention, the structural adhesive film is used for bonding when the copper net and the copper sheet are laid in the composite material piece at the same time, so that the possibility that the copper sheet is easy to fall off after the outer glass cloth is polished is avoided; the invention utilizes the standard component to simultaneously realize the connection and circuit conduction between the structural components, thereby achieving two purposes; the invention has simple, direct and effective current transfer path and solves the problem of low conductive efficiency between composite structural members; according to the invention, because the copper cup needs to be provided with the rivet prefabricated hole, the assembly precision is considered, the copper cup is a rear part, namely the copper cup and the composite material structural member are not jointly fed into a furnace for curing; the copper cup is fixed on the machine body structure by the conductive adhesive, so that the copper cup can play a role in fixing and conducting electricity at the same time; the metal surface paint ECS2209 on the outer side of the copper cup has the function of improving the adhesive force of the strontium chromate epoxy insulating primer so as to improve the corrosion prevention period; the invention can also be applied to the conductive treatment between the composite structural members of the internal structure of the fuselage structure, and the insulating sealing rubber strips between the structural members are eliminated.
The above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equally replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present application, and are intended to be included within the scope of the present application.
Claims (9)
1. A method for realizing conductive processing between composite material structural members by using copper cups is characterized by comprising the steps of establishing a conductive path between a composite material structural member I (1) and a composite material structural member II (16) which are connected on an airplane; the parts that electrically conductive route utilized include copper mesh (2), copper sheet (3), packing ring (5), fastener (6), layer board nut (12), countersunk head self-plugging rivet (14), copper cup (18), copper mesh (20), wherein:
the composite material structural part I (1) is characterized in that a copper sheet (3) and a copper net (2) are laid under an outermost layer of glass cloth (8), a layer of structural adhesive film (4) is laid between the copper sheet (3) and the outermost layer of glass cloth (8), the copper sheet (3) is attached to the copper net (2), a layer of structural adhesive film (4) is laid between the copper net (2) and an inner side of carbon cloth (9), the copper sheet (3) is laid around each fastener (6) on the composite material structural part I (1), and the fasteners (6) and the copper sheet (3) are electrically connected through gaskets (5);
a copper cup (18) and a copper net (20) are laid under the outermost layer of glass cloth (17) of the composite material structural part II (16), and a layer of conductive adhesive (19) is laid between the copper cup (18) and the copper net (20); the copper cup (18) is a structure formed by pressing a dimple for fixing a countersunk self-plugging rivet head (15) on a copper sheet; for the countersunk self-plugging rivet (14) needing conductive lap joint of the composite material structural part II (16), riveting the countersunk self-plugging rivet (14) into a supporting plate of the composite material structural part II (16) and a supporting plate nut (12) from a copper cup (18), riveting the supporting plate nut (12) at the inner side of the composite material structural part II (16), and simultaneously enabling a rivet head (15) of the countersunk self-plugging rivet to be positioned in the countersink; the copper cup (18) is also provided with a through hole for the fastener (6) to pass through.
2. The method for conducting between composite structural members by using a copper cup as claimed in claim 1, wherein the lap joint amount between the structural adhesive film (4) laid between the copper sheet (3) and the outermost glass cloth (8) and the structural adhesive film (4) laid between the copper mesh (2) and the inner carbon cloth (9) is 5 mm.
3. The method for conducting between composite structural members by means of copper cups according to claim 1, wherein the spacing between the copper sheets (3) is not more than 200 mm.
4. The method for conducting electricity between composite structural members by using a copper cup as claimed in claim 1, wherein the composite structural member I (1) and the composite structural member II (16) are fixed by using a fastener, so that the washer (5) and the supporting plate nut (12) form a conducting path.
5. The method for conducting between composite material structural members by using the copper cup as claimed in claim 1, wherein before the fastener (6) is installed on the composite material structural member I (1), the outermost glass cloth in the shadow area range of 18mm from the axis phi of the fastener (6) is ground, the ground area is not painted, and other parts are painted with primer.
6. The method for conducting electricity between composite structural members by using a copper cup as claimed in claim 1, wherein the outermost glass cloth of the assembly area (22) of the copper cup (18) and the composite structural member II (16) is polished until the copper mesh is exposed, and the outer surface of the copper cup (18) is sprayed with a metal surface paint and a layer of strontium chromate epoxy insulating primer.
7. The method for conducting electricity between composite structural members by using the copper cups as claimed in claim 1, wherein the protective paint layer (23) on the contact surface of the fastener nail head (7) and the gasket (5) is removed between the fastener nail head (7) and the gasket (5), the protective paint layer (24) on the contact surface of the gasket (5) and the copper cup (18) is removed, and the protective paint layer on the contact surface of the supporting plate nut (12) and the countersunk head blind rivet pier head (13) is removed.
8. The method of claim 1, wherein the dimension Φ of the copper cup is selected from the group consisting of1The diameter of the counter sink is 0.5-1.5mm larger than the diameter of the nail rod of the fastener, and the counter sink size phi of the countersunk self-plugging rivet (14) is arranged2Equal to the diameter of the rod of the countersunk self-plugging rivet and the hole spacing value d1Should be equal to the distance between the supporting plate nut (12) and the rivet hole and the margin value d2、d3(2 x diameter of countersunk blind rivet rod +1), depth of copper cup countersinkValue h1Equal to the depth of the rivet head of the countersunk head self-plugging rivet, and the angle alpha of the countersink of the copper cup is equal to the angle of the rivet head (15) of the countersunk head self-plugging rivet.
9. The method for conducting between composite structural members by using copper cups according to claim 1, wherein lightning strikes or the like cause currents at composite skin or flap or other parts on the outer surface of a fuselage, the currents flow into a washer (5) and a fastener pin head (7) through a copper mesh (2) laid in a composite structural member I (1) in sequence through a copper sheet (3) and then flow into a fastener (6) and then flow into a fastener pin rod, the currents flow into a counter blind rivet pin head (13) and then sequentially through the counter blind rivet pin rod, a counter blind rivet pin head (15) and a copper cup (18) and then flow into the copper mesh (20) through a conductive adhesive (19) because the counter blind rivet pin head (12) is in direct contact with the counter blind rivet pin head (13), and finally the currents flow to the rear part of the fuselage along the fuselage skin.
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 |
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| 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 true CN114180083A (en) | 2022-03-15 |
| CN114180083B CN114180083B (en) | 2023-09-01 |
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|---|---|---|---|---|
| GB8726711D0 (en) * | 1987-11-14 | 1987-12-16 | British Aerospace | Lightning protective fasteners |
| GB9411006D0 (en) * | 1994-06-02 | 1994-07-20 | British Aerospace | Method of fastening composite aircraft skins |
| EP0976652A1 (en) * | 1998-07-29 | 2000-02-02 | Construcciones Aeronauticas, S.A. | Lightning protection system for composite aircraft structures |
| EP0976653A1 (en) * | 1998-07-29 | 2000-02-02 | Construcciones Aeronauticas, S.A. | Lightning protection system for composite aircraft structures |
| EP1484245A1 (en) * | 2003-06-06 | 2004-12-08 | Airbus Espana, S.L. | Lightning strike protection system for aircraft fuel tanks made of low electrical conductivity composite material |
| US20100219287A1 (en) * | 2009-02-27 | 2010-09-02 | Airbus Operations S.L. | Protection against direct lightning strikes in riveted areas of cfrp panels |
| CN107323648A (en) * | 2017-06-22 | 2017-11-07 | 中国航空工业集团公司沈阳飞机设计研究所 | The conduction metalolic network of composite airplane |
| CN208291490U (en) * | 2018-06-03 | 2018-12-28 | 精功（绍兴）复合材料有限公司 | One kind being used for aircraft integral tank mount structure |
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| CN112176384A (en) * | 2020-09-27 | 2021-01-05 | 深圳市信维通信股份有限公司 | Plastic vibrator electroplating equipment |
| CN212556824U (en) * | 2020-06-29 | 2021-02-19 | 中国航发商用航空发动机有限责任公司 | Lightning protection panel connection structure |
| CN214397183U (en) * | 2020-11-17 | 2021-10-15 | 中航通飞华南飞机工业有限公司 | Sealing installation structure for ice-throwing-preventing plate of propeller plane body |
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| CN212556824U (en) * | 2020-06-29 | 2021-02-19 | 中国航发商用航空发动机有限责任公司 | Lightning protection panel connection structure |
| CN112072335A (en) * | 2020-09-25 | 2020-12-11 | 中国直升机设计研究所 | Conductive structure between composite material structural members and conductive processing method |
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| CN214397183U (en) * | 2020-11-17 | 2021-10-15 | 中航通飞华南飞机工业有限公司 | Sealing installation structure for ice-throwing-preventing plate of propeller plane body |
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| CN114180083B (en) | 2023-09-01 |
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