EP1569303A1 - Verzorgungsrückleitungsvorrichtung für Flugzeugausrüstung - Google Patents

Verzorgungsrückleitungsvorrichtung für Flugzeugausrüstung Download PDF

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Publication number
EP1569303A1
EP1569303A1 EP05101160A EP05101160A EP1569303A1 EP 1569303 A1 EP1569303 A1 EP 1569303A1 EP 05101160 A EP05101160 A EP 05101160A EP 05101160 A EP05101160 A EP 05101160A EP 1569303 A1 EP1569303 A1 EP 1569303A1
Authority
EP
European Patent Office
Prior art keywords
power supply
conductive
supply return
return device
aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP05101160A
Other languages
English (en)
French (fr)
Other versions
EP1569303B1 (de
Inventor
Hicham Berrada
François Montegut
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of EP1569303A1 publication Critical patent/EP1569303A1/de
Application granted granted Critical
Publication of EP1569303B1 publication Critical patent/EP1569303B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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

Definitions

  • the present invention relates to the return of power supply avionics equipment on aircraft such as aircraft and in particular positioned on composite structures that conduct electricity.
  • the power supply of avionics equipment is traditionally done by a current supply cable at a non-zero electrical potential and by a back of the current by the structure of the device, via a metallic fixation to which is secured the equipment, the zero potential or mass of the device.
  • the materials although conductive, no longer exhibit the qualities of conductivity required to guarantee a sufficient current return and on the contrary can have sufficient resistivity to cause a significant voltage drop on the course of the current, a heating of the structure even a danger fire.
  • a complementary problem is that if one chooses to make a return of cable current, the cable should be dimensioned according to the distance to browse and number of connected equipment if the return cable is common to multiple equipment, to provide multiple cables if a separate return is provided which complicates the design of electrical systems, increases the weight and overall cost and may be detrimental to the reliability of the system by the complication of the electricity network.
  • the present invention aims to overcome this degradation of the conductivity of the conductive composite structure while retaining a current return circuit simple and reliable and offers for this purpose a power return device electrical system for avionics embedded devices arranged on a structure conductive composite of an aircraft, this device comprising at least one bar conductive metal bonded to the conductive composite structure through insulating fastening means, the metal bar comprising on the one hand at least an electrical connection member for at least one of said devices on the other hand an electrical connection element to a structure primary electric motor of said aircraft.
  • the conductive metal bar thus constitutes a conductive element structural primary.
  • the electrical connection member can be constituted a connection board for a current feedback connection from least an embedded device.
  • connection plate may comprise at least one base of receiving a connection terminal of said connection.
  • the device comprises a plurality of organs of connection spaced from place to place longitudinally on the metal bar conductor so as to connect several remote embedded devices.
  • said electrical connection element is a fixing element of the metal bar on said primary electrical structure.
  • This fastening element may especially consist of at least one screw made of material that is highly conductive to electricity.
  • the means of Insulating fasteners include screws fixed in the composite structure conductive through insulating sleeves.
  • the conductive metal bar can be part of an electrical network reported running along at least one wall an internal space of the aircraft.
  • a insulating support can be arranged between the conductive metal bar and the conductive composite structure.
  • the power supply return device according to the invention is schematized in figure 1.
  • This device applies to avionics avionics devices 1a, 1b disposed on a conductive composite structure 2 of a part of an aircraft such as a box or a tank.
  • the conductive composite structures employed contain frequently carbon particles or are made of laminated material comprising aluminum foils.
  • the invention solves the problem of the risks caused by this lack of conductivity of the structure including creating an electrical return device isolated current of this structure.
  • the device comprises at least one conductive metal bar 3. bar, secured to the conductive composite structure through means of insulating fixing 4, will convey the return current of equipment 1a, 1b to a metal structure 7 adapted to the passage of strong currents and constituting a mass or reference zero electric potential, such metal structure being called primary electrical structure of the aircraft.
  • the bar 3 is connected to this primary electrical structure 7 by a electrical connection element 6 which according to the example shown is also a fastening element 16, 16a, 16b of the metal bar 3 on the electrical structure primary 7, for example a screw of highly electrically conductive material.
  • the bar 3 is then positioned on an insulating support 12 and secured to the conductive composite structure 2 by insulating fixing means constituted according to the example shown in FIG. 2 by screws 10 fixed in the conductive composite structure through insulating sleeves 11 or by any type of fastening (insulating members such as fastening clips, for example).
  • the bar can be straight or have a curved or sinuous profile for approaching the on-board devices 1a, 1b to which it must be connected.
  • the bar has at least one electrical connection member 5a, 5b for at least an onboard device 1a, 1b.
  • a connecting member 9 consisting of a connection plate for a current return connection 8a, 8b by on-board device can be provided.
  • connection plate according to the example comprises a base 9 of receiving a lug 13 connecting the connection 8a, 8b of the embedded devices.
  • the bar can, depending on its length and the number of equipment embedded to be connected, have a plurality of connecting members 5a, 5b spaced from place to place longitudinally on the bar conductive metal 3 so as to connect several embedded devices 1a, 1 b distant.
  • the invention also makes it possible to produce an electrical return network of reported current running along at least one wall of an internal space of the aircraft, several conductive metal bars 3 belonging to the network reported electric.
  • the device according to the invention can for example be made from bars of predetermined size and having breakable sections for obtain bars of suitable length according to the distance of equipment to the primary electrical structures of the aircraft.
  • the constituted network can for example go around an internal space of a housing such as an aircraft tank or a box consisting of panels 2 in conductive composite material while remaining electrically isolated from the panels constituting this internal space by means of the insulating fixing means 4 and the insulating support 12 disposed between the bars 3 of the network and the panels.
  • the device according to the invention thus makes it easy to carry out a primary electrical sub structure reported in the caissons of an aircraft.

Landscapes

  • Connections By Means Of Piercing Elements, Nuts, Or Screws (AREA)
  • Structure Of Printed Boards (AREA)
  • Cable Accessories (AREA)
  • Selective Calling Equipment (AREA)
  • Control Of Electric Motors In General (AREA)
  • Percussion Or Vibration Massage (AREA)
  • Connector Housings Or Holding Contact Members (AREA)
  • Coupling Device And Connection With Printed Circuit (AREA)
  • Vehicle Body Suspensions (AREA)
  • Feeding And Watering For Cattle Raising And Animal Husbandry (AREA)
  • Catching Or Destruction (AREA)
  • Laminated Bodies (AREA)
EP05101160A 2004-02-26 2005-02-16 Versorgungsrückleitungsvorrichtung für Flugzeugausrüstung Expired - Lifetime EP1569303B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0401935 2004-02-26
FR0401935A FR2866991B1 (fr) 2004-02-26 2004-02-26 Dispositif de retour d'alimentation electrique pour equipements avioniques

Publications (2)

Publication Number Publication Date
EP1569303A1 true EP1569303A1 (de) 2005-08-31
EP1569303B1 EP1569303B1 (de) 2006-09-20

Family

ID=34746444

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05101160A Expired - Lifetime EP1569303B1 (de) 2004-02-26 2005-02-16 Versorgungsrückleitungsvorrichtung für Flugzeugausrüstung

Country Status (7)

Country Link
US (1) US7485800B2 (de)
EP (1) EP1569303B1 (de)
AT (1) ATE340421T1 (de)
CA (1) CA2495987C (de)
DE (1) DE602005000133T2 (de)
ES (1) ES2273307T3 (de)
FR (1) FR2866991B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010099052A3 (en) * 2009-02-26 2010-11-11 The Boeing Company Distributing power in systems having a composite structure
WO2011012795A1 (fr) * 2009-07-31 2011-02-03 Airbus Operations Aeronef comprenant des equipements electriques et des pieces en materiau composite

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090266935A1 (en) * 2008-04-28 2009-10-29 Paul Joern Shell arrangement as well as aircraft or spacecraft
DE102009026686A1 (de) * 2009-06-03 2010-12-23 Airbus France Anordnung zum Blitzschutz einer elektronischen Einheit
FR2989468B1 (fr) * 2012-04-17 2014-05-23 Airbus Operations Sas Procede de controle de la performance des jonctions electriques dans un reseau de retour de courant d'un aeronef.
FR3012527B1 (fr) * 2013-10-30 2015-10-30 Snecma Metallisation d'un carter electriquement isolant d'un moteur aeronautique
FR3012516B1 (fr) * 2013-10-30 2018-01-05 Safran Aircraft Engines Metallisation d'un carter d'un moteur aeronautique en materiau electriquement isolant
CA3043569A1 (en) * 2016-11-11 2018-05-17 Bombardier Inc. Signal return network for composite aircraft

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2687195A1 (fr) * 1992-02-12 1993-08-13 Eurocopter France Organe d'assemblage a tete fraisee, tel qu'un rivet, pour l'assemblage de pieces en materiau composite munies de revetements electriquement conducteurs, et structure obtenue par cet assemblage.
DE19936640A1 (de) * 1999-08-04 2001-02-15 Eads Airbus Gmbh Masseverbindung zwischen gelenkig miteinander verbundenen Bauteilen

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3989984A (en) * 1975-07-11 1976-11-02 Mcdonnell Douglas Corporation Aircraft lightning protection means
US4502092A (en) * 1982-09-30 1985-02-26 The Boeing Company Integral lightning protection system for composite aircraft skins
GB9807198D0 (en) * 1998-04-04 1998-06-03 British Aerospace Adhesively bonded joints in carbon fibre composite structures
ES2162718A1 (es) * 1998-07-29 2002-01-01 Const Aeronauticas Sa Un sistema de proteccion contra descargas electricas, especialmente rayos, de componentes estructurales de aviones.

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2687195A1 (fr) * 1992-02-12 1993-08-13 Eurocopter France Organe d'assemblage a tete fraisee, tel qu'un rivet, pour l'assemblage de pieces en materiau composite munies de revetements electriquement conducteurs, et structure obtenue par cet assemblage.
DE19936640A1 (de) * 1999-08-04 2001-02-15 Eads Airbus Gmbh Masseverbindung zwischen gelenkig miteinander verbundenen Bauteilen

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010099052A3 (en) * 2009-02-26 2010-11-11 The Boeing Company Distributing power in systems having a composite structure
US8231080B2 (en) 2009-02-26 2012-07-31 The Boeing Company Distributing power in systems having a composite structure
US8453971B2 (en) 2009-02-26 2013-06-04 The Boeing Company Composite structure power distribution
WO2011012795A1 (fr) * 2009-07-31 2011-02-03 Airbus Operations Aeronef comprenant des equipements electriques et des pieces en materiau composite
FR2948637A1 (fr) * 2009-07-31 2011-02-04 Airbus Operations Sas Aeronef comprenant des equipements electriques et des pieces en materiau composite
CN102576946A (zh) * 2009-07-31 2012-07-11 空中客车运营简化股份公司 包括电气设备和复合材料部件的航空器
US8755164B2 (en) 2009-07-31 2014-06-17 Airbus Operations (S.A.S) Aircraft including pieces of electrical equipment and parts made of composite material
CN102576946B (zh) * 2009-07-31 2015-04-29 空中客车运营简化股份公司 包括电气设备和复合材料部件的航空器

Also Published As

Publication number Publication date
EP1569303B1 (de) 2006-09-20
DE602005000133T2 (de) 2007-09-13
CA2495987A1 (fr) 2005-08-26
US7485800B2 (en) 2009-02-03
CA2495987C (fr) 2012-12-18
ES2273307T3 (es) 2007-05-01
ATE340421T1 (de) 2006-10-15
FR2866991A1 (fr) 2005-09-02
US20050190547A1 (en) 2005-09-01
DE602005000133D1 (de) 2006-11-02
FR2866991B1 (fr) 2006-05-19

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