WO2006069997A1 - Device for electrical bonding of electrical cables shielding on composite structures - Google Patents
Device for electrical bonding of electrical cables shielding on composite structures Download PDFInfo
- Publication number
- WO2006069997A1 WO2006069997A1 PCT/EP2005/057185 EP2005057185W WO2006069997A1 WO 2006069997 A1 WO2006069997 A1 WO 2006069997A1 EP 2005057185 W EP2005057185 W EP 2005057185W WO 2006069997 A1 WO2006069997 A1 WO 2006069997A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- shielding
- electrical
- bonding
- area
- carbon fiber
- Prior art date
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 16
- 239000004917 carbon fiber Substances 0.000 claims abstract description 16
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 15
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 8
- 239000010936 titanium Substances 0.000 claims abstract description 8
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 8
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 4
- 229910052793 cadmium Inorganic materials 0.000 claims abstract description 4
- BDOSMKKIYDKNTQ-UHFFFAOYSA-N cadmium atom Chemical compound [Cd] BDOSMKKIYDKNTQ-UHFFFAOYSA-N 0.000 claims abstract description 4
- 239000003566 sealing material Substances 0.000 claims abstract description 4
- 239000010959 steel Substances 0.000 claims abstract description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 239000000463 material Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000005672 electromagnetic field Effects 0.000 description 2
- 239000002828 fuel tank Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000001052 transient effect Effects 0.000 description 2
- 239000004020 conductor Substances 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000000644 propagated effect Effects 0.000 description 1
- 239000002966 varnish Substances 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
- H01R13/648—Protective earth or shield arrangements on coupling devices, e.g. anti-static shielding
- H01R13/658—High frequency shielding arrangements, e.g. against EMI [Electro-Magnetic Interference] or EMP [Electro-Magnetic Pulse]
- H01R13/6591—Specific features or arrangements of connection of shield to conductive members
- H01R13/65912—Specific features or arrangements of connection of shield to conductive members for shielded multiconductor cable
- H01R13/65914—Connection of shield to additional grounding conductors
-
- 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
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
- H01R13/648—Protective earth or shield arrangements on coupling devices, e.g. anti-static shielding
- H01R13/658—High frequency shielding arrangements, e.g. against EMI [Electro-Magnetic Interference] or EMP [Electro-Magnetic Pulse]
- H01R13/6591—Specific features or arrangements of connection of shield to conductive members
- H01R13/65912—Specific features or arrangements of connection of shield to conductive members for shielded multiconductor cable
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
- H01R4/06—Riveted connections
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
- H01R4/58—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation characterised by the form or material of the contacting members
- H01R4/64—Connections between or with conductive parts having primarily a non-electric function, e.g. frame, casing, rail
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R9/00—Structural associations of a plurality of mutually-insulated electrical connecting elements, e.g. terminal strips or terminal blocks; Terminals or binding posts mounted upon a base or in a case; Bases therefor
- H01R9/03—Connectors arranged to contact a plurality of the conductors of a multiconductor cable, e.g. tapping connections
- H01R9/05—Connectors arranged to contact a plurality of the conductors of a multiconductor cable, e.g. tapping connections for coaxial cables
- H01R9/0509—Tapping connections
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R9/00—Structural associations of a plurality of mutually-insulated electrical connecting elements, e.g. terminal strips or terminal blocks; Terminals or binding posts mounted upon a base or in a case; Bases therefor
- H01R9/03—Connectors arranged to contact a plurality of the conductors of a multiconductor cable, e.g. tapping connections
- H01R9/05—Connectors arranged to contact a plurality of the conductors of a multiconductor cable, e.g. tapping connections for coaxial cables
- H01R9/0512—Connections to an additional grounding conductor
Definitions
- the invention relates to the electrical bonding of intermediate points of an electrical cable bundle shielding directly to structures made of a composite with low electrical conductivity when the bundles exceed three meters in length in areas that are not or do not form part of the structure demarcating the fuel tank.
- Hybrid solutions which combine electrical bonding to a metallic structure and to carbon fiber, are currently known to resolve these problems.
- a shielding or metal braid minimizing the induced effects in the cables of said bundles is added.
- This shielding is generally electrically bonded at both ends appropriately since this is the most critical point of the installation (for the purpose of having good electromagnetic protection) and when the routes exceed 3 meters, an "intermediate bonding point" must be installed, connecting the shielding to a metallic structure every 3 meters.
- This invention proposes a solution to this drawback.
- the electrical bonding device of a shielding of electrical cables arranged on the structure of an aircraft in an area exposed to the effects induced by electromagnetic fields generated by lightning and made with a composite according to this invention comprises a metallic plate with a lug where connected thereto is a projecting lead of the shielding which is fixed to said area by means of titanium rivets installed under dry conditions, with cadmium steel collars, which are coated with a sealing material.
- the intermediate points of the shielding are electrically bonded directly to the airplane structure made with a carbon fiber based- composite of the airplane. This prevents the use of metallic strips for these specific bonding points, which increase airplane weight, makes the design more complex, and therefore increase costs.
- this device can be applied in structural areas of the airplane built from carbon fiber where there is an electrical cable installation, the shielding of which must be bonded, as long as the carbon fiber area does not form part of or demarcate an airplane fuel tank. To that respect, it is considered that despite the fact that carbon fiber is much more resistive than any other metal, if the area is thick enough it may have enough resistive capacity to conduct the normally circulating type of current levels through an intermediate bonding point.
- Figure 1 shows the configuration of the bonding device of a shielding of electrical cables in aircraft according to the invention.
- Figure 2 shows the configuration of the bonding device of a shielding of electrical cables in aircraft according to the invention including the distribution of the current in the event of lightning strike, causing an induced current on the shielding.
- the rivets 11 which must be used, preferably the number of 3, are Hi- lock type anodized titanium rivets and with a minimum of 4 mm in diameter.
- the head of the rivet must be countersunk to achieve greater contact between the rivet and the carbon fiber surface.
- the collar 17 of the rivets 11 in contact with the metallic plate 9, is made of cadmium steel.
- the ends of the rivets are coated with a sealing material 19 to prevent moisture from entering the bonding, painted with a colored varnish that allows identifying the grounding points.
- the metallic plate is made of titanium since this material allows the plate to be placed in direct contact with the area 15 of carbon fiber since there is not a high enough difference in
- Titanium also has the advantage of being able to be installed in areas requiring fireproof materials.
- the metallic plate 9 is made of aluminum, which has greater conductivity than titanium.
- the device must include an insulating sheet 13, for example, fiberglass, between the metallic i o plate 9 and the area 15 of carbon fiber to prevent corrosion.
- the main feature of the device according to this invention is based on the fact that the bonding is done directly on the area made of carbon fiber, the electrical resistance of which depends on the area where the current is applied or propagated.
- propagation of the current represented by means of the current lines 21 in Figure 2 is generated from the shaft of the rivets 11 and parallel to the direction of the carbon fibers, which conducts better than if it were perpendicular thereto.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
Abstract
The invention relates to an electrical bonding device of a shielding (3) of electrical cables (5) in aircraft arranged in its structure in an area (15) made with a carbon fiber-based composite, comprising a metallic plate (9) with a lug (7) where a bonding lead (1) projecting from the shielding (3) is connected, being fixed to said area (15) by means of titanium rivets (11) installed under dry conditions with cadmium steel rings (17), which are coated with a sealing material (19).
Description
DEVICE FOR ELECTRICAL BONDING OF ELECTRICAL CABLES SHIELDING ON COMPOSITE STRUCTURES
FIELD OF THE INVENTION
The invention relates to the electrical bonding of intermediate points of an electrical cable bundle shielding directly to structures made of a composite with low electrical conductivity when the bundles exceed three meters in length in areas that are not or do not form part of the structure demarcating the fuel tank.
BACKGROUND OF THE INVENTION
The need to suitably protect cables in aircraft from electromagnetic fields created by lightning, which particularly translates into transitory current and voltage drops, is known in the aeronautical industry.
Up until a few years age, metallic materials (for example aluminum) were used in the aeronautical field as the primary material of aircraft structures. Having a large amount of said materials in the airplane involved a good grounding of the systems and made the airplane have a rather good electrical continuity and relatively low electrical resistance values, thus preventing potential drops, relevant structural damage, the presence of burning or incandescent particles or hot gases released at the point of contact between two conductors when a large current density passed (sparking), and overheating of the material due to the direct striking of lightning or for being subjected to a high current density (hot-spot).
The vertiginous evolution towards aircraft structures built with carbon fiber has caused that the damage occurring in this type of material as a result of its heterogeneous features are considerable and to be taken into account due to its criticality.
In aircrafts built with carbon fiber, the traditional bonding concept in an airplane, known as a primary metallic structure, tends to disappear and the traditional protection methods are no longer applicable.
Providing a structure built with carbon fiber means that in case of
lightning strike, from the electromagnetic point of view, the systems and equipment enclosed by said structure are more vulnerable and are therefore more exposed to induced effects, which basically translate into transient current and voltage drops. These transient states normally affect the wiring and take place as a result of the magnetic field created by the current of the lightening circulating through the outer structure.
"Hybrid" solutions, which combine electrical bonding to a metallic structure and to carbon fiber, are currently known to resolve these problems.
In particular, to protect the cable bundles installed in areas with a composite catalogued as "exposed areas" for these purposes, a shielding or metal braid minimizing the induced effects in the cables of said bundles is added. This shielding is generally electrically bonded at both ends appropriately since this is the most critical point of the installation (for the purpose of having good electromagnetic protection) and when the routes exceed 3 meters, an "intermediate bonding point" must be installed, connecting the shielding to a metallic structure every 3 meters.
The inability in some cases of having sufficient metallic structure, or the lack of closeness between the systems installed in the airplane and the metallic structures thereof, makes it necessary to install additional bonding strips and bonding jumpers, increasing airplane costs and weight.
This invention proposes a solution to this drawback.
SUMMARY OF THE INVENTION
The electrical bonding device of a shielding of electrical cables arranged on the structure of an aircraft in an area exposed to the effects induced by electromagnetic fields generated by lightning and made with a composite according to this invention, comprises a metallic plate with a lug where connected thereto is a projecting lead of the shielding which is fixed to said area by means of titanium rivets installed under dry conditions, with cadmium steel collars, which are coated with a sealing material.
With this device, the intermediate points of the shielding are electrically bonded directly to the airplane structure made with a carbon fiber based- composite of the airplane. This prevents the use of metallic strips for these
specific bonding points, which increase airplane weight, makes the design more complex, and therefore increase costs.
Generally speaking, this device can be applied in structural areas of the airplane built from carbon fiber where there is an electrical cable installation, the shielding of which must be bonded, as long as the carbon fiber area does not form part of or demarcate an airplane fuel tank. To that respect, it is considered that despite the fact that carbon fiber is much more resistive than any other metal, if the area is thick enough it may have enough resistive capacity to conduct the normally circulating type of current levels through an intermediate bonding point.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 shows the configuration of the bonding device of a shielding of electrical cables in aircraft according to the invention.
Figure 2 shows the configuration of the bonding device of a shielding of electrical cables in aircraft according to the invention including the distribution of the current in the event of lightning strike, causing an induced current on the shielding.
DETAILED DESCRIPTION OF THE INVENTION
According to Figure 1 , it can be observed that the bonding lead 1 of the shielding 3 of an electrical cable bundle 5 is connected to a lug 7 of the metallic plate 9 which is fixed by means of rivets 11 to the area 15 of the airplane structure made of carbon fiber.
The rivets 11 which must be used, preferably the number of 3, are Hi- lock type anodized titanium rivets and with a minimum of 4 mm in diameter. The head of the rivet must be countersunk to achieve greater contact between the rivet and the carbon fiber surface.
The collar 17 of the rivets 11 , in contact with the metallic plate 9, is made of cadmium steel.
The ends of the rivets are coated with a sealing material 19 to prevent moisture from entering the bonding, painted with a colored varnish that allows
identifying the grounding points.
In a preferred embodiment of the invention, the metallic plate is made of titanium since this material allows the plate to be placed in direct contact with the area 15 of carbon fiber since there is not a high enough difference in
5 electrochemical potentials to cause corrosion. Titanium also has the advantage of being able to be installed in areas requiring fireproof materials.
In an alternative embodiment, the metallic plate 9 is made of aluminum, which has greater conductivity than titanium. In this case, the device must include an insulating sheet 13, for example, fiberglass, between the metallic i o plate 9 and the area 15 of carbon fiber to prevent corrosion.
From the technical point of view, the main feature of the device according to this invention is based on the fact that the bonding is done directly on the area made of carbon fiber, the electrical resistance of which depends on the area where the current is applied or propagated.
15 In this case, propagation of the current represented by means of the current lines 21 in Figure 2 is generated from the shaft of the rivets 11 and parallel to the direction of the carbon fibers, which conducts better than if it were perpendicular thereto.
Claims
1.- A bonding device of a shielding (3) of electrical cables (5) arranged in the structure of an aircraft in the area (15) made of a carbon fiber-based composite, characterized in that it comprises a metallic plate (9) with a lug (7) where a bonding lead (1) projecting from said shielding (3) is connected, which is fixed to said area (15) by means of titanium rivets (11 ) installed under dry conditions with cadmium steel rings (17), which are coated with a sealing material (19).
2.- A device according to claim 1 , characterized in that the metallic plate (9) is made with titanium.
3.- A device according to claim 1 , characterized in that the metallic plate (9) is made with aluminum and in that it also comprises an insulating sheet (13) located between it and the area (15).
4.- A device according to claim 1 , characterized in that it includes at least three rivets (11 ).
5.- A device according to any of the previous claims, characterized in that the bonding lead (1 ) projects from the shielding (3) at an intermediate area thereof.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US11/794,513 US8263864B2 (en) | 2004-12-30 | 2005-12-27 | Device for electrical bonding of electrical cables shielding on composite structures |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ES200403148 | 2004-12-30 | ||
| ESP200403148 | 2004-12-30 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2006069997A1 true WO2006069997A1 (en) | 2006-07-06 |
Family
ID=35966993
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/EP2005/057185 WO2006069997A1 (en) | 2004-12-30 | 2005-12-27 | Device for electrical bonding of electrical cables shielding on composite structures |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US8263864B2 (en) |
| WO (1) | WO2006069997A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008001416A1 (en) * | 2008-04-28 | 2009-12-03 | Airbus Deutschland Gmbh | External skin arrangement for air- or spacecraft, comprises a first lightening conductor layer for conducting of light energy, and a fiber reinforced composite layer, which carries the first lightening conductor layer |
| FR2939762A1 (en) * | 2008-12-15 | 2010-06-18 | Eads Europ Aeronautic Defence | AIRCRAFT PART OF A COMPOSITE MATERIAL WITH PROTECTION AGAINST THE EFFECTS OF ALUMINUM LIGHTNING. |
| WO2011012795A1 (en) * | 2009-07-31 | 2011-02-03 | Airbus Operations | Aircraft including electrical apparatuses and composite material parts |
| JP2015074449A (en) * | 2013-10-11 | 2015-04-20 | ザ・ボーイング・カンパニーＴｈｅＢｏｅｉｎｇ Ｃｏｍｐａｎｙ | Modular equipment center lightning threat reduction architecture |
| CN112173142A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Helicopter cable-proof device |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2932456B1 (en) * | 2008-06-17 | 2010-05-28 | Airbus France | SYSTEM FOR DRAINING A LIGHTNING CURRENT GENERATED BY A STORM DISCHARGE ON AN AIRCRAFT |
| DE202012010193U1 (en) * | 2012-10-24 | 2014-02-03 | Walter Kiersch | Carbon fiber component with electrical contact element |
| US9939358B2 (en) * | 2015-09-24 | 2018-04-10 | The Boeing Company | Sealant testing for aircraft fuel tanks |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3922050A (en) * | 1974-03-21 | 1975-11-25 | Boeing Co | Blind, shank expanding electrical terminal structure |
| US4023882A (en) * | 1974-04-25 | 1977-05-17 | Borge Hugo Pettersson | Electrical connector device securable to metal member |
| WO1983001345A1 (en) * | 1981-09-30 | 1983-04-14 | Olson, Glenn, Oliver | Fastening device and method for composite structures |
| US4473714A (en) * | 1981-09-25 | 1984-09-25 | Akzona Incorporated | Cable shield bond connector |
| DE19848617A1 (en) * | 1998-10-21 | 2000-04-27 | Profil Verbindungstechnik Gmbh | Making electrical connection to sheet part involves screwing into threaded hollow attachment element through sheet part |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1984001487A1 (en) * | 1982-09-30 | 1984-04-12 | Boeing Co | Integral lightning protection system for composite aircraft skins |
| US4561708A (en) * | 1984-05-30 | 1985-12-31 | Minnesota Mining And Manufacturing Company | Cable shield connector |
| US4917615A (en) * | 1988-11-18 | 1990-04-17 | Franks George J Jr | Ground bracket |
| DE4214508C2 (en) * | 1992-05-01 | 1996-03-14 | Daimler Benz Aerospace Airbus | Arrangement for ground connection to an internal lightning protection system |
-
2005
- 2005-12-27 US US11/794,513 patent/US8263864B2/en active Active
- 2005-12-27 WO PCT/EP2005/057185 patent/WO2006069997A1/en active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3922050A (en) * | 1974-03-21 | 1975-11-25 | Boeing Co | Blind, shank expanding electrical terminal structure |
| US4023882A (en) * | 1974-04-25 | 1977-05-17 | Borge Hugo Pettersson | Electrical connector device securable to metal member |
| US4473714A (en) * | 1981-09-25 | 1984-09-25 | Akzona Incorporated | Cable shield bond connector |
| WO1983001345A1 (en) * | 1981-09-30 | 1983-04-14 | Olson, Glenn, Oliver | Fastening device and method for composite structures |
| DE19848617A1 (en) * | 1998-10-21 | 2000-04-27 | Profil Verbindungstechnik Gmbh | Making electrical connection to sheet part involves screwing into threaded hollow attachment element through sheet part |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008001416A1 (en) * | 2008-04-28 | 2009-12-03 | Airbus Deutschland Gmbh | External skin arrangement for air- or spacecraft, comprises a first lightening conductor layer for conducting of light energy, and a fiber reinforced composite layer, which carries the first lightening conductor layer |
| DE102008001416B4 (en) * | 2008-04-28 | 2013-09-26 | Airbus Operations Gmbh | Aerial or spacecraft |
| FR2939762A1 (en) * | 2008-12-15 | 2010-06-18 | Eads Europ Aeronautic Defence | AIRCRAFT PART OF A COMPOSITE MATERIAL WITH PROTECTION AGAINST THE EFFECTS OF ALUMINUM LIGHTNING. |
| WO2010069922A1 (en) * | 2008-12-15 | 2010-06-24 | European Aeronautic Defence And Space Company Eads France | Aircraft part made of a composite material with aluminium protection against the effects of lightning |
| WO2011012795A1 (en) * | 2009-07-31 | 2011-02-03 | Airbus Operations | Aircraft including electrical apparatuses and composite material parts |
| FR2948637A1 (en) * | 2009-07-31 | 2011-02-04 | Airbus Operations Sas | AIRCRAFT COMPRISING ELECTRICAL EQUIPMENT AND PARTS OF COMPOSITE MATERIAL |
| CN102576946A (en) * | 2009-07-31 | 2012-07-11 | 空中客车运营简化股份公司 | Aircraft including electrical apparatuses and composite material parts |
| JP2013500895A (en) * | 2009-07-31 | 2013-01-10 | エアバス オペラシオン ソシエテ パ アクシオンス シンプリフィエ | Aircraft having parts made of electrical equipment and composite materials |
| RU2538183C2 (en) * | 2009-07-31 | 2015-01-10 | Эрбюс Операсьон | Aircraft with electrical equipment and part of composites |
| JP2015074449A (en) * | 2013-10-11 | 2015-04-20 | ザ・ボーイング・カンパニーＴｈｅＢｏｅｉｎｇ Ｃｏｍｐａｎｙ | Modular equipment center lightning threat reduction architecture |
| CN112173142A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Helicopter cable-proof device |
| CN112173142B (en) * | 2020-09-25 | 2022-11-25 | 中国直升机设计研究所 | Helicopter cable-proof device |
Also Published As
| Publication number | Publication date |
|---|---|
| US20100089608A1 (en) | 2010-04-15 |
| US8263864B2 (en) | 2012-09-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8263864B2 (en) | Device for electrical bonding of electrical cables shielding on composite structures | |
| US2982494A (en) | Lightning arrestor for radomes | |
| CA2200439C (en) | Lightweight braided shielding for wiring harnesses | |
| CA2575899C (en) | Fuel tank for an aircraft | |
| JP2010512270A (en) | Lightning protection system for composite structure of aircraft | |
| RU2676623C1 (en) | Composite structure | |
| CN105228899B (en) | Aircraft bottom plate comprising ground plane | |
| Brusso | History of aircraft wiring arc-fault protection [history] | |
| CN211529658U (en) | Cable for electric control equipment | |
| US20050190547A1 (en) | Electrical current return device for avionic equipment | |
| US8540189B2 (en) | Cable way for aircraft with a structure made of composite material | |
| JP2012006528A (en) | Laminar composite for machine body structures of aircraft and machine body structure of aircraft | |
| USRE25417E (en) | Lightning arrestor for radomes | |
| US20110042136A1 (en) | Grounding bar/hatchplate for use with lightning arrestors | |
| EP0753458B1 (en) | Cowling assembly | |
| JPS62154499A (en) | Arrestor | |
| CN208861687U (en) | A kind of resistance to ultra low temperature environment protection type cross-linked polyolefin cable used for wind power generation | |
| CN208835687U (en) | A kind of isolated bus gantry | |
| CN206672733U (en) | A kind of moistureproof low residual voltage metal oxide arrester | |
| CN208189267U (en) | A kind of high temperature-resistant cable | |
| CN208753004U (en) | A kind of special cable for strong magnetic environment | |
| CN207339197U (en) | A kind of bare wire security bar | |
| CN103854791B (en) | A kind of small size environmental protection oil-resisting type railway locomotive cable | |
| CN209001504U (en) | A kind of forceful electric power cable transportation system | |
| CN208477967U (en) | Single shields thin wall type high voltage cable |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
| NENP | Non-entry into the national phase |
Ref country code: DE |
|
| 122 | Ep: pct application non-entry in european phase |
Ref document number: 05825192 Country of ref document: EP Kind code of ref document: A1 |
|
| WWW | Wipo information: withdrawn in national office |
Ref document number: 5825192 Country of ref document: EP |
|
| WWE | Wipo information: entry into national phase |
Ref document number: 11794513 Country of ref document: US |