EP1569303A1 - Supply reverse current device for aircraft equipment - Google Patents

Supply reverse current device for aircraft equipment Download PDF

Info

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
German (de)
French (fr)
Other versions
EP1569303B1 (en
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/en
Application granted granted Critical
Publication of EP1569303B1 publication Critical patent/EP1569303B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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)
  • Laminated Bodies (AREA)
  • Vehicle Body Suspensions (AREA)
  • Feeding And Watering For Cattle Raising And Animal Husbandry (AREA)
  • Catching Or Destruction (AREA)
  • Connector Housings Or Holding Contact Members (AREA)
  • Coupling Device And Connection With Printed Circuit (AREA)
  • Percussion Or Vibration Massage (AREA)
  • Selective Calling Equipment (AREA)
  • Control Of Electric Motors In General (AREA)
  • Cable Accessories (AREA)

Abstract

The device has a metallic conducting bar (3) integrated to a composite conducting structure of an aircraft by an insulating fixation unit (4). The bar has electric connector bodies (5a, 5b) for embedded devices (1a, 1b) arranged on the structure and an electric connector unit connected to a primary electric structure of the aircraft. The bodies have connection plates for current return connectors (8a, 8b) of the devices.

Description

La présente invention concerne le retour d'alimentation électrique d'équipements avioniques embarqués sur des appareils tels que des aéronefs et notamment positionnés sur des structures composites conductrices de l'électricité.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.

L'alimentation électrique d'équipement avioniques se fait traditionnellement par un câble d'amenée de courant à un potentiel électrique non nul et par un retour du courant par la structure de l'appareil, via une fixation métallisée à laquelle est solidarisé l'équipement, au potentiel nul ou masse de l'appareil.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.

Le recours aux structures en matériaux composites conducteurs est de plus en plus important dans les aéronefs, de telles structures venant en remplacement de structures métalliques.The use of structures in conductive composite materials is moreover more important in aircraft, such structures replacing of metal structures.

Dans le cas de structures conductrices composites par exemples structures comportant du carbone et/ ou structures de type feuilleté aluminium/composite, les matériaux, bien que conducteurs, ne présentent plus les qualités de conductivité requises pour garantir un retour de courant suffisant et au contraire peuvent présenter une résistivité suffisante pour causer une chute de tension conséquente sur le parcours du courant, un échauffement de la structure voire un danger d'incendie.In the case of composite conductive structures, for example structures with carbon and / or laminated aluminum / composite structures, 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.

Ces structures ne constituant plus des structures électriques primaires ne doivent pas être utilisées pour les retours de courant, le retour de courant devant être isolé de la structure composite conductrice.These structures no longer constituting primary electrical structures should not be used for power returns, the current return in front of be isolated from the conductive composite structure.

Un problème complémentaire est que si l'on choisit de réaliser un retour de courant par câble, il y a lieu de dimensionner le câble en fonction de la distance à parcourir et du nombre d'équipement raccordés si le câble de retour est commun à plusieurs équipements, de prévoir plusieurs câbles si un retour séparé est prévu ce qui complique la conception des systèmes électriques, accroít le poids et le coût de l'ensemble et peut être préjudiciable à la fiabilité du système par la complication du réseau électrique.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.

La présente invention vise à pallier à cette dégradation de conductivité de la structure composite conductrice tout en conservant un circuit de retour de courant simple et fiable et propose pour ce faire un dispositif de retour d'alimentation électrique pour dispositifs embarqués avioniques disposés sur une structure composite conductrice d'un aéronef, ce dispositif comportant au moins une barre métallique conductrice solidarisée à la structure composite conductrice au travers de moyens de fixation isolants, la barre métallique comportant d'une part au moins un organe de raccordement électrique pour au moins un desdits dispositifs embarqués et d'autre part un élément de raccordement électrique à une structure électrique primaire dudit aéronef.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.

La barre métallique conductrice constitue ainsi un élément conducteur primaire structurel.The conductive metal bar thus constitutes a conductive element structural primary.

Selon l'invention, l'organe de raccordement électrique peut être constitué d'une platine de raccordement pour une connexion de retour de courant d'au moins un dispositif embarqué.According to the invention, the electrical connection member can be constituted a connection board for a current feedback connection from least an embedded device.

La platine de raccordement peut comporter au moins une embase de réception d'une cosse de raccordement de ladite connexion.The connection plate may comprise at least one base of receiving a connection terminal of said connection.

Avantageusement, le dispositif comporte une pluralité d'organes de raccordement espacés de place en place longitudinalement sur la barre métallique conductrice en sorte de raccorder plusieurs dispositifs embarqués distants.Advantageously, 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.

Plus particulièrement, ledit élément de raccordement électrique est un élément de fixation de la barre métallique sur ladite structure électrique primaire.More particularly, said electrical connection element is a fixing element of the metal bar on said primary electrical structure.

Cet l'élément de fixation peut notamment être constitué d'au moins une vis en matériau fortement conducteur de l'électricité.This fastening element may especially consist of at least one screw made of material that is highly conductive to electricity.

Selon un mode de réalisation avantageux de l'invention, les moyens de fixation isolants comprennent des vis fixées dans la structure composite conductrice au travers de manchons isolants.According to an advantageous embodiment of the invention, the means of Insulating fasteners include screws fixed in the composite structure conductive through insulating sleeves.

Selon le dispositif selon l'invention, la barre métallique conductrice peut faire partie d'un réseau électrique rapporté cheminant le long d'au moins une paroi d'un espace interne de l'aéronef. According to the device according to the invention, the conductive metal bar can be part of an electrical network reported running along at least one wall an internal space of the aircraft.

En mode de réalisation particulièrement avantageux de l'invention, un support isolant peut être disposé entre la barre métallique conductrice et la structure composite conductrice.In a particularly advantageous embodiment of the invention, a insulating support can be arranged between the conductive metal bar and the conductive composite structure.

D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre d'un exemple de réalisation non limitatif en référence aux figures qui représentent:

  • En figure 1: une vue en perspective de tronçons d'un dispositif selon l'invention;
  • En figure 2: une vue de côté en coupe du dispositif de la figure 1.
    • Other characteristics and advantages of the invention will be better understood on reading the following description of a nonlimiting exemplary embodiment with reference to the figures which represent:
  • In Figure 1: a perspective view of sections of a device according to the invention;
  • In Figure 2: a side view in section of the device of Figure 1.

    • Le dispositif de retour d'alimentation électrique selon l'invention est schématisé en figure 1.The power supply return device according to the invention is schematized in figure 1.

    Ce dispositif s'applique à des dispositifs embarqués avioniques 1a, 1b disposés sur une structure composite conductrice 2 d'une partie d'un aéronef telle qu'un caisson ou un réservoir.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.

    Les structures composites conductrices employées contiennent fréquemment des particules de carbones ou sont réalisées en matériau feuilleté comprenant des feuilles d'aluminium.The conductive composite structures employed contain frequently carbon particles or are made of laminated material comprising aluminum foils.

    Ces structures présentent une certaine conductivité mais celle ci ne permet pas le passage de courants importants voire même ne garantissent pas une équipotentialité de la structure. L'utilisation d'une telle structure composite conductrice en tant que retour de courant est donc à proscrire, cette structure ne constituant pas une masse apte à servir de circuit de retour de courant.These structures have a certain conductivity but this one does not allow not the passage of important currents or even do not guarantee a equipotentiality of the structure. The use of such a composite structure conductor as a return of current is therefore to be avoided, this structure not constituting a mass capable of serving as a current return circuit.

    L'invention résout le problème des risques causés par ce manque de conductivité de la structure notamment en créant un dispositif électrique de retour de courant isolé de cette structure.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.

    Le dispositif comporte au moins une barre métallique conductrice 3. Cette barre, solidarisée à la structure composite conductrice au travers de moyens de fixation isolants 4, va véhiculer le courant de retour des équipements 1a, 1b jusqu'à une structure métallique 7 adaptée au passage de forts courants et constitutive d'une masse ou potentiel électrique nul de référence, une telle structure métallique étant appelée structure électrique primaire de l'aéronef.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.

    La barre 3 est raccordée à cette structure électrique primaire 7 par un élément de raccordement électrique 6 qui selon l'exemple représenté est aussi un élément de fixation 16, 16a, 16b de la barre métallique 3 sur la structure électrique primaire 7, par exemple une vis en matériau fortement conducteur de l'électricité.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.

    La barre 3 est ensuite positionnée sur un support isolant 12 et solidarisée à la structure composite conductrice 2 par des moyens de fixation isolants constitués selon l'exemple représenté en figure 2 par des vis 10 fixées dans la structure composite conductrice au travers de manchons isolants 11 ou par tout type de fixation (organes isolants tels que clips de fixation par exemple).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).

    La barre peut être droite ou avoir un profil courbe ou sinueux pour se rapprocher des dispositifs embarqués 1a, 1b auxquels elle doit être reliée.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.

    Dans le but de connecter ces dispositifs embarqués 1a, 1b la barre comporte au moins un organe de raccordement électrique 5a, 5b pour au moins un dispositif embarqué 1a, 1b. En fonction de la position des dispositifs embarqués sur le support, plusieurs dispositifs peuvent être raccordés sur un organe de raccordement électrique ou comme représenté sur les figures 1 et 2, un organe de raccordement 9 constitué d'une platine de raccordement pour une connexion de retour de courant 8a, 8b par dispositif embarqué peut être prévu.In order to connect these embedded devices 1a, 1b the bar has at least one electrical connection member 5a, 5b for at least an onboard device 1a, 1b. Depending on the position of the devices embedded on the support, several devices can be connected to one electrical connection member or as shown in FIGS. 1 and 2, a connecting member 9 consisting of a connection plate for a current return connection 8a, 8b by on-board device can be provided.

    La platine de raccordement selon l'exemple comporte une embase 9 de réception d'une cosse 13 de raccordement de la connexion 8a, 8b du ou des dispositifs embarqués.The connection plate according to the example comprises a base 9 of receiving a lug 13 connecting the connection 8a, 8b of the embedded devices.

    Ainsi la barre peut, selon sa longueur et le nombre d'équipements embarqués à raccorder, comporter une pluralité d'organes de raccordement électrique 5a, 5b espacés de place en place longitudinalement sur la barre métallique conductrice 3 en sorte de raccorder plusieurs dispositifs embarqués 1a, 1 b distants.Thus 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.

    L'invention permet en outre de réaliser un réseau électrique de retour de courant rapporté cheminant le long d'au moins une paroi d'un espace interne de l'aéronef, plusieurs barres métalliques conductrice 3 faisant partie du réseau électrique rapporté.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.

    Le dispositif selon l'invention peut par exemple être réalisé à partir de barres de dimension prédéterminée et comportant des tronçons sécables pour obtenir des barres de longueur adaptée en fonction de la distance des équipements aux structures électriques primaires de l'aéronef.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.

    Le réseau constitué peut par exemple faire le tour d'un espace interne d'un logement tel qu'un réservoir d'aéronef ou d'un caisson constitué de panneaux 2 en matériau composite conducteur tout en restant électriquement isolé des panneaux constituant cet espace interne à l'aide des moyens de fixation isolants 4 et du support isolant 12 disposé entre les barres 3 du réseau et les panneaux.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.

    Le dispositif selon l'invention permet ainsi de manière commode de réaliser une sous structure électrique primaire rapportée dans des caissons d'un aéronef.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.

    Claims (9)

    Dispositif de retour d'alimentation électrique pour dispositifs embarqués avioniques (1a, 1b) disposés sur une structure composite conductrice (2) d'un aéronef caractérisé en ce qu'il comporte au moins une barre métallique conductrice (3) solidarisée à la structure composite conductrice au travers de moyens de fixation isolants (4), la barre (3) comportant d'une part au moins un organe de raccordement électrique (5a, 5b) pour au moins un desdits dispositifs embarqués (1a, 1b) et, d'autre part, un élément de raccordement électrique (6) à une structure électrique primaire (7) dudit aéronef.A power supply return for embedded devices avionics (1a, 1b) arranged on a conductive composite structure (2) of an aircraft characterized in that it comprises at least one conductive metal bar (3) secured to the composite structure conductive through insulating fixing means (4), the bar (3) comprising on the one hand at least one electrical connection member (5a, 5b) for at least one of said onboard devices (1a, 1b) and, on the other hand, an electrical connection element (6) to a primary electrical structure (7) of said aircraft. Dispositif de retour d'alimentation électrique selon la revendication 1 caractérisé en ce que ledit organe de raccordement électrique (5a, 5b) est constitué d'une platine de raccordement pour une connexion de retour de courant (8a, 8b) d'au moins un dispositif embarqué (1a, 1b).Power supply return device according to claim 1 characterized in that said electrical connection member (5a, 5b) consists of a connection plate for a current return connection (8a, 8b) of at least one embedded device (1a, 1b). Dispositif de retour d'alimentation électrique selon la revendication 2 caractérisé en ce que ladite platine de raccordement comporte au moins une embase (9) de réception d'une cosse (13) de raccordement de ladite connexion (8a, 8b).Power supply return device according to claim 2 characterized in that said connecting plate comprises at least one base (9) for receiving a lug (13) for connecting said connection (8a, 8b). Dispositif de retour d'alimentation électrique selon l'une quelconque des revendications précédentes caractérisé en ce qu'il comporte une pluralité d'organes de raccordement (5a, 5b) espacés de place en place longitudinalement sur la barre métallique conductrice (3) en sorte de raccorder plusieurs dispositifs embarqués (1a, 1 b) distants.Power supply return device according to any one of the preceding claims, characterized in that it comprises a plurality of connecting members (5a, 5b) spaced longitudinally in place on the conductive metal bar (3) so that to connect several remote devices (1a, 1b). Dispositif de retour d'alimentation électrique selon l'une quelconque des revendications précédentes caractérisé en ce que l'élément de raccordement électrique (6) est un élément de fixation (16, 16a, 16b) de la barre métallique (3) sur la structure électrique primaire (7).Power supply return device according to any one of the preceding claims, characterized in that the electrical connection element (6) is a fastening element (16, 16a, 16b) of the metal bar (3) on the structure primary electric (7). Dispositif de retour d'alimentation électrique selon la revendication 5 caractérisé en ce que l'élément de fixation (16, 16a, 16b) est constitué d'au moins une vis en matériau fortement conducteur de l'électricité.Power supply return device according to Claim 5, characterized in that the fastening element (16, 16a, 16b) consists of at least one screw made of a material that is highly electrically conductive. Dispositif de retour d'alimentation électrique selon l'une quelconque des revendications précédentes caractérisé en ce que les moyens de fixation isolants comprennent des vis (10) fixées dans la structure composite conductrice au travers de manchons isolants (11).Power supply return device according to any one of the preceding claims, characterized in that the insulating fixing means comprise screws (10) fixed in the conductive composite structure through insulating sleeves (11). Dispositif de retour d'alimentation électrique selon l'une quelconque des revendications précédentes caractérisé en ce que la barre métallique conductrice (3) fait partie d'un réseau électrique rapporté cheminant le long d'au moins une paroi d'un espace interne de l'aéronef.Power supply return device according to any one of the preceding claims, characterized in that the conductive metal bar (3) is part of an attached electrical network running along at least one wall of an internal space of the 'aircraft. Dispositif de retour d'alimentation électrique selon l'une quelconque des revendications précédentes caractérisé en ce qu'un support isolant (12) est disposé entre la barre métallique conductrice (3) et la structure composite conductrice (2).Power supply return device according to one of the preceding claims, characterized in that an insulating support (12) is arranged between the conductive metal bar (3) and the conductive composite structure (2).
    EP05101160A 2004-02-26 2005-02-16 Supply reverse current device for aircraft equipment Expired - Lifetime EP1569303B1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    FR0401935A FR2866991B1 (en) 2004-02-26 2004-02-26 ELECTRIC FEED RETURN DEVICE FOR AVIONIC EQUIPMENT
    FR0401935 2004-02-26

    Publications (2)

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

    Family

    ID=34746444

    Family Applications (1)

    Application Number Title Priority Date Filing Date
    EP05101160A Expired - Lifetime EP1569303B1 (en) 2004-02-26 2005-02-16 Supply reverse current device for aircraft equipment

    Country Status (7)

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

    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 (en) * 2009-07-31 2011-02-03 Airbus Operations Aircraft including electrical apparatuses and composite material parts

    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 (en) * 2009-06-03 2010-12-23 Airbus France Arrangement for lightning protection of an electronic unit
    FR2989468B1 (en) * 2012-04-17 2014-05-23 Airbus Operations Sas METHOD OF CONTROLLING THE PERFORMANCE OF ELECTRICAL JUNCTION IN A CURRENT RETURN NETWORK OF AN AIRCRAFT.
    FR3012527B1 (en) * 2013-10-30 2015-10-30 Snecma METALLIZING AN ELECTRICALLY INSULATING CASE OF AN AERONAUTICAL MOTOR
    FR3012516B1 (en) * 2013-10-30 2018-01-05 Safran Aircraft Engines METALLIZING A CASING OF AN AERONAUTICAL MOTOR IN ELECTRICALLY INSULATING MATERIAL
    EP3538440B1 (en) * 2016-11-11 2020-07-15 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 (en) * 1992-02-12 1993-08-13 Eurocopter France Fastener with countersunk head, such as a rivet, for joining together pieces of composite material equipped with electrically conductive coatings and structure obtained by this joining
    DE19936640A1 (en) * 1999-08-04 2001-02-15 Eads Airbus Gmbh Electrical ground connection between aerodynamic control member movable on bearing and structure carrying bearing in aircraft, comprises sliding contact e.g. using carbon brush or rings

    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 (en) * 1998-07-29 2002-01-01 Const Aeronauticas Sa Lightning protection system for composite aircraft structures

    Patent Citations (2)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    FR2687195A1 (en) * 1992-02-12 1993-08-13 Eurocopter France Fastener with countersunk head, such as a rivet, for joining together pieces of composite material equipped with electrically conductive coatings and structure obtained by this joining
    DE19936640A1 (en) * 1999-08-04 2001-02-15 Eads Airbus Gmbh Electrical ground connection between aerodynamic control member movable on bearing and structure carrying bearing in aircraft, comprises sliding contact e.g. using carbon brush or rings

    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 (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
    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 (en) * 2009-07-31 2015-04-29 空中客车运营简化股份公司 Aircraft including electrical apparatuses and composite material parts

    Also Published As

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

    Similar Documents

    Publication Publication Date Title
    FR2952762A1 (en) CONTACTOR MOUNTING ASSEMBLY WITH IMPROVED THERMAL CHARACTERISTICS
    EP1569303B1 (en) Supply reverse current device for aircraft equipment
    WO2006084995A2 (en) Assembly forming a very long electrical connection
    FR2982712A1 (en) PLATE FOR DISTRIBUTING ELECTRIC ENERGY COMPRISING A PROTECTED DISTRIBUTION BAR.
    EP2692199A1 (en) Heat exchanger having electric heating elements
    WO2010072919A1 (en) Modular electrical card for power components
    EP1120659B1 (en) Electrical energy meter
    EP3727944B1 (en) Electrically conductive part for an electrical assembly
    EP3476665B1 (en) Electrical insulation bar, in particular for a power electronics module of an inverter
    EP2456014A3 (en) Connection terminal between a rotating electric machine of an automobile and a cable of the electric circuit of said vehicle
    EP3997759A1 (en) Connection device for grounding an electrical apparatus and/or creating an equipotential link between conductive elements
    WO2017032814A1 (en) Switching element for electrical energy distribution board and electrical energy distribution box fitted with such a switching element
    EP3727943B1 (en) Electrical connection bar for an electrical assembly
    EP3331336B1 (en) Compact power electronics system for electric powertrain
    EP3109943B1 (en) Electric connection device for an electrical appliance
    FR3109032A1 (en) ELECTRICAL CONNECTION BOX EQUIPPED WITH REMOTE RELAYS
    EP0829927B1 (en) Device for connecting a bus bar to an electrical conductor
    EP3351476B1 (en) Casing for distributing electrical power for an aircraft
    FR2786612A1 (en) Electrical connection system for supply bus bars includes connector linking to bar and providing connection point for multiple cables
    EP4371222A1 (en) Modular interconnections for a motor and a power electronic unit
    EP4564671A1 (en) Electronic break protection apparatus with heat sink
    FR2965899A1 (en) HEATED FILM WITH ELECTRICAL CONNECTION POWERED BY THREE PHASE
    EP4113767A1 (en) Electrical connection device between cables comprising a plate with electrically isolated channels surrounding busbars
    FR2805409A1 (en) POWER DISTRIBUTION DEVICE COMPRISING BARS APPLIED TO A PLATE
    FR2785458A1 (en) Retaining bracket for electrical plug comprises forked element fitting behind body of plug and retained by screws into support panel to prevent vibration loosening plug

    Legal Events

    Date Code Title Description
    PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

    Free format text: ORIGINAL CODE: 0009012

    AK Designated contracting states

    Kind code of ref document: A1

    Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

    AX Request for extension of the european patent

    Extension state: AL BA HR LV MK YU

    17P Request for examination filed

    Effective date: 20060125

    GRAP Despatch of communication of intention to grant a patent

    Free format text: ORIGINAL CODE: EPIDOSNIGR1

    AKX Designation fees paid

    Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

    GRAS Grant fee paid

    Free format text: ORIGINAL CODE: EPIDOSNIGR3

    GRAA (expected) grant

    Free format text: ORIGINAL CODE: 0009210

    AK Designated contracting states

    Kind code of ref document: B1

    Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: IE

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    Ref country code: AT

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    Ref country code: IT

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

    Effective date: 20060920

    Ref country code: NL

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    Ref country code: SI

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    Ref country code: FI

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    Ref country code: LT

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    Ref country code: CZ

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    Ref country code: SK

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    Ref country code: RO

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    Ref country code: PL

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    REG Reference to a national code

    Ref country code: GB

    Ref legal event code: FG4D

    Free format text: NOT ENGLISH

    REG Reference to a national code

    Ref country code: CH

    Ref legal event code: EP

    REG Reference to a national code

    Ref country code: IE

    Ref legal event code: FG4D

    Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

    REF Corresponds to:

    Ref document number: 602005000133

    Country of ref document: DE

    Date of ref document: 20061102

    Kind code of ref document: P

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: BG

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20061220

    Ref country code: DK

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20061220

    REG Reference to a national code

    Ref country code: SE

    Ref legal event code: TRGR

    GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

    Effective date: 20061227

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: IS

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20070120

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: MC

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20070228

    NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: PT

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20070312

    REG Reference to a national code

    Ref country code: IE

    Ref legal event code: FD4D

    REG Reference to a national code

    Ref country code: ES

    Ref legal event code: FG2A

    Ref document number: 2273307

    Country of ref document: ES

    Kind code of ref document: T3

    PLBE No opposition filed within time limit

    Free format text: ORIGINAL CODE: 0009261

    STAA Information on the status of an ep patent application or granted ep patent

    Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

    26N No opposition filed

    Effective date: 20070621

    BERE Be: lapsed

    Owner name: AIRBUS FRANCE

    Effective date: 20070228

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: BE

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20070228

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: GR

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20061221

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: EE

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    PGRI Patent reinstated in contracting state [announced from national office to epo]

    Ref country code: IT

    Effective date: 20090401

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: LU

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20070216

    Ref country code: CY

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: TR

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20060920

    Ref country code: HU

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20070321

    REG Reference to a national code

    Ref country code: CH

    Ref legal event code: PL

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: CH

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20090228

    Ref country code: LI

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20090228

    REG Reference to a national code

    Ref country code: GB

    Ref legal event code: 732E

    Free format text: REGISTERED BETWEEN 20110721 AND 20110727

    REG Reference to a national code

    Ref country code: FR

    Ref legal event code: TP

    Owner name: AIRBUS HOLDING, FR

    Effective date: 20110913

    Ref country code: FR

    Ref legal event code: CJ

    Effective date: 20110916

    Ref country code: FR

    Ref legal event code: CA

    Effective date: 20110916

    Ref country code: FR

    Ref legal event code: CD

    Owner name: AIRBUS HOLDING, FR

    Effective date: 20110916

    REG Reference to a national code

    Ref country code: ES

    Ref legal event code: PC2A

    Owner name: AIRBUS OPERATIONS SAS

    Effective date: 20120308

    REG Reference to a national code

    Ref country code: DE

    Ref legal event code: R082

    Ref document number: 602005000133

    Country of ref document: DE

    Representative=s name: SPARING - ROEHL - HENSELER, DE

    REG Reference to a national code

    Ref country code: DE

    Ref legal event code: R082

    Ref document number: 602005000133

    Country of ref document: DE

    Representative=s name: SPARING - ROEHL - HENSELER, DE

    Effective date: 20120326

    Ref country code: DE

    Ref legal event code: R081

    Ref document number: 602005000133

    Country of ref document: DE

    Owner name: AIRBUS OPERATIONS SAS, FR

    Free format text: FORMER OWNER: AIRBUS FRANCE, TOULOUSE, FR

    Effective date: 20120326

    PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

    Ref country code: SE

    Payment date: 20130219

    Year of fee payment: 9

    REG Reference to a national code

    Ref country code: SE

    Ref legal event code: EUG

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: SE

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20140217

    REG Reference to a national code

    Ref country code: FR

    Ref legal event code: PLFP

    Year of fee payment: 12

    REG Reference to a national code

    Ref country code: FR

    Ref legal event code: PLFP

    Year of fee payment: 13

    REG Reference to a national code

    Ref country code: FR

    Ref legal event code: PLFP

    Year of fee payment: 14

    PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

    Ref country code: FR

    Payment date: 20190124

    Year of fee payment: 19

    Ref country code: ES

    Payment date: 20190320

    Year of fee payment: 15

    PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

    Ref country code: GB

    Payment date: 20200219

    Year of fee payment: 16

    Ref country code: DE

    Payment date: 20200219

    Year of fee payment: 16

    REG Reference to a national code

    Ref country code: ES

    Ref legal event code: FD2A

    Effective date: 20210706

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: ES

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20200217

    REG Reference to a national code

    Ref country code: DE

    Ref legal event code: R119

    Ref document number: 602005000133

    Country of ref document: DE

    GBPC Gb: european patent ceased through non-payment of renewal fee

    Effective date: 20210216

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: IT

    Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

    Effective date: 20200216

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: DE

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20210901

    Ref country code: GB

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20210216

    Ref country code: FR

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20210228