EP1569303B1 - Versorgungsrückleitungsvorrichtung für Flugzeugausrüstung - Google Patents

Versorgungsrückleitungsvorrichtung für Flugzeugausrüstung Download PDF

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Publication number
EP1569303B1
EP1569303B1 EP05101160A EP05101160A EP1569303B1 EP 1569303 B1 EP1569303 B1 EP 1569303B1 EP 05101160 A EP05101160 A EP 05101160A EP 05101160 A EP05101160 A EP 05101160A EP 1569303 B1 EP1569303 B1 EP 1569303B1
Authority
EP
European Patent Office
Prior art keywords
current return
electrical
connection
return device
electrical current
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.)
Expired - Lifetime
Application number
EP05101160A
Other languages
English (en)
French (fr)
Other versions
EP1569303A1 (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 of avionics equipment embedded on aircraft such as aircraft and in particular positioned on composite structures that conduct electricity.
  • the power supply of avionic equipment is traditionally done by a current supply cable to a non-zero electrical potential and by a current return by the structure of the device, via a metallized fastener to which the equipment is secured. , at zero potential or mass of the device.
  • the materials although conductive, no longer have the conductivity qualities required to guarantee a sufficient current return and on the contrary can have a resistivity sufficient to cause a significant voltage drop on the path of the current, a heating of the structure or even a fire hazard.
  • a complementary problem is that if one chooses to carry out a current return by cable, it is necessary to size the cable according to the distance to be traveled and the number of connected equipment if the return cable is common to several equipment, to provide several cables if a separate return is provided This complicates the design of electrical systems, increases the weight and cost of the assembly and can be detrimental to the reliability of the system by the complication of the power grid.
  • the present invention aims to overcome this degradation of conductivity of the conductive composite structure while retaining a simple and reliable current return circuit and proposes for this purpose a power supply return device for avionics embedded devices arranged on a composite structure conductor of an aircraft, this device comprising at least one conductive metal bar secured to the conductive composite structure through insulating fixing means, the metal bar comprising on the one hand at least one electrical connection member for at least one of said devices on the other hand an electrical connection element to a primary electrical structure of said aircraft.
  • the conductive metal bar thus constitutes a structural primary conductive element.
  • the electrical connection member may consist of a connection plate for a return current connection of at least one onboard device.
  • connection board may comprise at least one base for receiving a connection terminal of said connection.
  • the device comprises a plurality of connecting members spaced apart in place longitudinally on the conductive metal bar so as to connect several remote onboard devices.
  • said electrical connection element is a fixing element of the metal bar on said primary electrical structure.
  • This fixing element may in particular consist of at least one screw made of a material that is highly electrically conductive.
  • the insulating fixing means comprise screws fixed in the conductive composite structure through insulating sleeves.
  • the conductive metal bar may be part of an electrical network reported running along at least one wall of an internal space of the aircraft.
  • an insulating support may be arranged between the conductive metal bar and the conductive composite structure.
  • the power supply return device according to the invention is shown schematically in FIG.
  • This device applies to avionic avionics devices 1a, 1b arranged on a conductive composite structure 2 of a part of an aircraft such as a box or a tank.
  • the conductive composite structures employed frequently contain 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, in particular by creating an electric current return device isolated from this structure.
  • the device comprises at least one conductive metal bar 3.
  • This bar secured to the conductive composite structure through insulating fixing means 4, will convey the return current of the equipment 1a, 1b to a metal structure 7 adapted to the passage strong currents and constituting a mass or zero reference electric potential, such a metal structure being called the primary electrical structure of the aircraft.
  • the bar 3 is connected to this primary electrical structure 7 by an electrical connection element 6 which according to the example shown is also a fixing element 16, 16a, 16b of the metal bar 3 on the primary electrical structure 7, for example a screw of highly electrically conductive material.
  • an electrical connection element 6 which according to the example shown is also a fixing element 16, 16a, 16b of the metal bar 3 on the primary electrical structure 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 Figure 2 by screws 10 fixed in the conductive composite structure through insulating sleeves 11 or by any type of fixation (insulating members such as fixing clips for example).
  • the bar may be straight or have a curved or sinuous profile to approach the embedded devices 1a, 1b to which it must be connected.
  • the bar comprises at least one electrical connection member 5a, 5b for at least one onboard device 1a, 1b.
  • a connecting member 9 consisting of a connecting plate for a return connection current 8a, 8b per onboard device can be provided.
  • connection board comprises a base 9 for receiving a lug 13 connecting the connection 8a, 8b of the onboard devices.
  • the bar may, depending on its length and the number of on-board equipment to be connected, comprise a plurality of electrical connection members 5a, 5b spaced in place longitudinally on the conductive metal bar 3 so as to connect several onboard devices 1a. , 1 b distant.
  • the invention also makes it possible to provide an electrical return current feedback network running along at least one wall of an internal space of the aircraft, several conductive metal bars 3 forming part of the reported electrical network.
  • the device according to the invention may for example be made from bars of predetermined size and having breakable sections to obtain bars of suitable length as a function of the distance of the equipment to the primary electrical structures of the aircraft.
  • the network formed may 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 using 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 conveniently makes it possible to produce 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)

Claims (9)

  1. Vorrichtung für die Rückleitung der Stromversorgung für Vorrichtungen (1a, 1b) an Bord von Flugzeugen, die auf einer leitenden Verbundstruktur (2) eines Flugzeugs angeordnet sind, dadurch gekennzeichnet, dass sie wenigstens einen leitenden Metallstab (3) umfasst, der mit der leitenden Verbundstruktur über isolierende Befestigungsmittel (4) verbunden ist, wobei der Stab (3) einerseits wenigstens ein elektrisches Verbindungsorgan (5a, 5b) für wenigstens eine der an Bord vorhandenen Vorrichtungen (1a, 1b) besitzt und andererseits ein elektrisches Verbindungselement (6) mit einer primären elektrischen Struktur (7) des Flugzeugs besitzt.
  2. Vorrichtung für die Rückleitung der Stromversorgung nach Anspruch 1, dadurch gekennzeichnet, dass das elektrische Verbindungsorgan (5a, 5b) aus einer Verbindungsplatine für einen Stromrückleitungsanschluss (8a, 8b) wenigstens einer an Bord vorhandenen Vorrichtung (1a, 1b) gebildet ist.
  3. Vorrichtung für die Rückleitung der Stromversorgung nach Anspruch 2, dadurch gekennzeichnet, dass die Verbindungsplatine wenigstens eine Grundfläche (9) für die Aufnahme einer Verbindungshülse (13) für den Anschluss (8a, 8b) aufweist.
  4. Vorrichtung für die Rückleitung der Stromversorgung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass sie mehrere Verbindungsorgane (5a, 5b) aufweist, die von einem Ort zum nächsten in Längsrichtung auf dem leitenden metallischen Stab (3) voneinander beabstandet sind, um mehrere in einem Abstand vorhandene Vorrichtungen (1a, 1b) an Bord zu verbinden.
  5. Vorrichtung für die Rückleitung der Stromversorgung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das elektrische Verbindungselement (6) ein Element (16, 16a, 16b) für die Befestigung des Metallstabs (3) an der primären elektrischen Struktur (7) ist.
  6. Vorrichtung für die Rückleitung der Stromversorgung nach Anspruch 5, dadurch gekennzeichnet, dass das Befestigungselement (16, 16a, 16b) aus wenigstens einer Schraube aus einem Material, das Elektrizität gut leitet, gebildet ist.
  7. Vorrichtung für die Rückleitung der Stromversorgung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die isolierenden Befestigungsmittel Schrauben (10) umfassen, die in der leitenden Verbundstruktur durch isolierende Muffen (11) hindurch befestigt sind.
  8. Vorrichtung für die Rückleitung der Stromversorgung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der leitende metallische Stab (3) einen Teil eines angefügten elektrischen Netzes bildet, das wenigstens längs einer Wand eines Innenraums des Flugzeugs verläuft.
  9. Vorrichtung für die Rückleitung der Stromversorgung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass zwischen dem leitenden metallischen Stab (3) und der leitenden Verbundstruktur (2) ein isolierender Träger (12) angeordnet ist.
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 EP1569303A1 (de) 2005-08-31
EP1569303B1 true 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)

Families Citing this family (8)

* 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
US8231080B2 (en) 2009-02-26 2012-07-31 The Boeing Company Distributing power in systems having a composite structure
DE102009026686A1 (de) * 2009-06-03 2010-12-23 Airbus France Anordnung zum Blitzschutz einer elektronischen Einheit
FR2948637B1 (fr) * 2009-07-31 2012-01-20 Airbus Operations Sas Aeronef comprenant des equipements electriques et des pieces en materiau composite
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

Family Cites Families (6)

* 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
FR2687195B1 (fr) * 1992-02-12 1995-07-07 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.
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.
DE19936640B4 (de) * 1999-08-04 2008-01-10 Airbus Deutschland Gmbh Masseverbindung zwischen gelenkig miteinander verbundenen Bauteilen eines Flugzeuges

Also Published As

Publication number Publication date
EP1569303A1 (de) 2005-08-31
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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