EP0188160B1 - De-icing device for a wing structure - Google Patents

De-icing device for a wing structure Download PDF

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Publication number
EP0188160B1
EP0188160B1 EP85402600A EP85402600A EP0188160B1 EP 0188160 B1 EP0188160 B1 EP 0188160B1 EP 85402600 A EP85402600 A EP 85402600A EP 85402600 A EP85402600 A EP 85402600A EP 0188160 B1 EP0188160 B1 EP 0188160B1
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EP
European Patent Office
Prior art keywords
tape
fibres
conductive
ribbon
electrical
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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
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EP85402600A
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German (de)
French (fr)
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EP0188160A1 (en
Inventor
Philippe Barbier
Alain Cohendy
Rémy Reynet
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Airbus Group SAS
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Airbus Group SAS
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    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/02—Details
    • H05B3/06—Heater elements structurally combined with coupling elements or holders
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/10—Heater elements characterised by the composition or nature of the materials or by the arrangement of the conductor
    • H05B3/12—Heater elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material
    • H05B3/14—Heater elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
    • H05B3/145—Carbon only, e.g. carbon black, graphite
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/20—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater
    • H05B3/34—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs
    • H05B3/36—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B2203/00—Aspects relating to Ohmic resistive heating covered by group H05B3/00
    • H05B2203/002—Heaters using a particular layout for the resistive material or resistive elements
    • H05B2203/005—Heaters using a particular layout for the resistive material or resistive elements using multiple resistive elements or resistive zones isolated from each other
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B2203/00—Aspects relating to Ohmic resistive heating covered by group H05B3/00
    • H05B2203/002—Heaters using a particular layout for the resistive material or resistive elements
    • H05B2203/007—Heaters using a particular layout for the resistive material or resistive elements using multiple electrically connected resistive elements or resistive zones
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B2203/00—Aspects relating to Ohmic resistive heating covered by group H05B3/00
    • H05B2203/011—Heaters using laterally extending conductive material as connecting means
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B2203/00—Aspects relating to Ohmic resistive heating covered by group H05B3/00
    • H05B2203/014—Heaters using resistive wires or cables not provided for in H05B3/54
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B2203/00—Aspects relating to Ohmic resistive heating covered by group H05B3/00
    • H05B2203/017—Manufacturing methods or apparatus for heaters
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B2214/00—Aspects relating to resistive heating, induction heating and heating using microwaves, covered by groups H05B3/00, H05B6/00
    • H05B2214/02—Heaters specially designed for de-icing or protection against icing

Definitions

  • the technique then evolved on the "heating panels" side, that is to say the placing of plates or mats of a fibrous composite structure in which conductive fibers are dispersed (whether boron or carbon) .
  • the supply of electric current to pass through the fibers is carried out by the connection of wires to a metal frame attached to the edge of the panel and kept in contact with the fibers or to a metal deposit, produced by vaporization or by electrolytic means, at the ends of the panel containing the fibers.
  • these devices have a major defect with regard to the necessary electrical contacts between the fibers and the supply wires.
  • the resins used in the composite materials have a fairly average adhesive power, so that detachments of the metallic foils can distribute the current to the fibers.
  • the improvement in bonding leads to an increase in the resistance of the contact points resulting in very localized overheating degrading adhesive and resin and therefore to weakening of the mechanical connection and rupture of the electrical connection.
  • the extra thicknesses which exist at the points of the electrical connections are detrimental to the respect of the aerodynamic profile of the airfoil and constitute a hindrance to the correct positioning of the shielding structures and of protection of the leading edges against shocks and the erosion.
  • the present invention intends to remedy these drawbacks by proposing a deicing device in which the heating element or elements are integrated without altering the resistance of the leading edge of the airfoil, and are connected to the supply wires in an extremely stable without constituting critical points both from the electrical point of view and from the mechanical point of view.
  • the device is also obtained by a simple manufacturing process which allows it to be easily adapted to the wing or blade profile to be fitted or even to be integrated therein at the same time of the manufacture of the wing or the blade.
  • the invention therefore has as its first object an element with electrical resistance forming part of a device for deicing a wing structure such as the wing of an airplane or the blades of a helicopter comprising conductive fibers. drowned in a composite fiber structure and supply wires electrically connected to said conductive fibers.
  • the conductive fibers are carbon fibers in the form of at least one ribbon in which the fibers are oriented longitudinally, prepreg of resin and of which at least one end is subject in a deformable tubular element with metallic meshes ensuring the electrical connection by contact with said strip and by welding or crimping with the corresponding supply wire.
  • a second object of the invention resides in a de-icing device comprising at least one of the aforementioned elements and which consists of a length, determined as a function of the resistance to be obtained from the above-mentioned carbon fiber ribbon, including the part tape covered by said tubular element, disposed between at least two layers of a composite material so as to form a heating mat.
  • the aforementioned element may consist of at least two sections of parallel and side by side ribbon arranged on either side of an intermediate layer of composite material and connected in series by one of their ends to the by means of a section of ribbon overlapping said ends not covered by said intermediate layer.
  • a third object of the invention is the method for producing the above defrosting device in which the heating mat is formed flat and then is placed between a form and a counterform where it is polymerized under pressure to obtain the profile. the leading edge of the wing structure to be fitted.
  • an element 1 resistant from the electrical point of view, consisting of a ribbon 2 of carbon fibers oriented parallel to the longitudinal dimension of the ribbon, and prepreg d '' a resin capable of being polymerized and hardened. It will be noted that for a section of 3 square millimeters the section of pure carbon is, in a ribbon used of the order of 1.9 mm2.
  • One end 2a of the tape is covered with a tubular element 3 consisting knitted by knitting a suitable wire. To this knit is soldered to tin a supply wire 4 in an area where the sleeve is gathered around the wire and / or in an area of the sleeve covering both the ribbon and one end of the wire which is introduced therein.
  • FIG. 2 shows that in order to produce a defrosting device with the above-mentioned element 1, an element 6 such as that on an insulating base substrate 5 (for example glass fabric preferably prepreg) is provided, 1 aforesaid which is constituted by three sections 6a, 6b, 6c ribbon of carbon fibers that form an electrical resistance of a value which will depend, for a given section of the ribbon, of the total length of the element 6.
  • the free ends of the sections 6a and 6c are fitted with tubular knits soldered in tin to the connection wires 7a 7b.
  • a second protective layer 8 identical to layer 5 covers the latter and the element 6 which it carries.
  • the mat thus formed can be polymerized under pressure between a shape and a counter-shape reproducing the profile of the wing on which the device will be docked. Care will have been taken to place the substrates 5 and 8 so that they completely cover the ends of the sections 6 a and 6 b sheathed with the knitted sleeve so that only the conductors 7 a and 7 b are located outside of the together.
  • the pressure applied during the polymerization makes it possible on the one hand to firmly anchor the sleeves in the resin of the ribbon and on the other hand to ensure intimate contact between the two substrates 5 and 8 in the area between the two sections 6 a 6 c creating effective isolation from one with respect to the other.
  • Figures 3 to 10 illustrate the constitution of a defrosting device intended to be supplied with three-phase current.
  • a support substrate 9 similar to that 5 in FIG. 2, three sections 10 of ribbon of prepreg carbon fibers are placed parallel and regularly spaced from each other by a distance at least equal to the width of the ribbon.
  • a section of overlapping ribbon 11 one of their three ends constitutes the common of the triangle mounting of the three resistors that the device will include.
  • An intermediate layer 12 also made of preferably pre-impregnated glass fabric is then placed on the sections 10 and 11 so as to leave the ends 10 has sections 10.
  • the defrosting device made in a very simple manner flat can then be polymerized under pressure into a suitable mold. It can also be incorporated into the very mold for constituting the wing structure (airplane wing or helicopter blade) itself made of composite material. In the latter case, we will have chosen substrates 9, 12 and 17 of the same kind as those which are used for the constitution of the wings or blades.
  • the invention finds an interesting application in the field of aeronautics.

Description

On sait que la formation du givre sur les fuselages et les voilures d'aéronefs est due à la rencontre d'une surface froide (de température inférieure à 0°C) avec des gouttelettes d'eau en surfusion contenues dans l'atmosphère. Il se produit alors des dépôts de glace sur la surface et, dans le domaine des voilures en général et particulièrement des voilures tournantes d'hélicoptères, les plus importants s'observent sur le bord d'attaque et son voisinage de la structure alaire. Il en résulte des modifications du profil des ailes ou des pales qui peuvent être préjudiciables à leurs qualités aérodynamiques.We know that the formation of frost on aircraft fuselages and wings is due to the encounter of a cold surface (temperature below 0 ° C) with supercooled water droplets contained in the atmosphere. Ice deposits are then produced on the surface and, in the field of wings in general and particularly rotary wings of helicopters, the most important are observed on the leading edge and its vicinity of the wing structure. This results in changes in the profile of the wings or blades which may be detrimental to their aerodynamic qualities.

On connaît différents types de dispositifs permettant le dégivrage de ces zones critiques et l'un d'eux consiste à chauffer ces zones au moyen de résistances électriques.Different types of devices are known for defrosting these critical zones and one of them consists in heating these zones by means of electrical resistors.

Plusieurs genres de résistances ont été mis en oeuvre pour accomplir cette fonction. Tous présentent des inconvénients tels que le dégivrage par chauffage reste une question qui, à l'heure actuelle, n'est pas encore résolue de manière entièrement satisfaisante. C'est ainsi qu'on a mis en place, sous une protection métallique collée au bord d'attaque de la voilures, des résistances métalliques. L'ensemble de ce dispositif est assez fragile et de durée de vie relativement courte. En cas de panne il est pratiquement exclu d'effectuer une réparation sans changer intégralement la totalité d'un dispositif.Several kinds of resistors have been used to accomplish this function. All of them have drawbacks such that defrosting by heating remains a question which, at the present time, has not yet been entirely satisfactorily resolved. This is how we set up, under a metal protection glued to the leading edge of the wings, metal resistances. The whole of this device is quite fragile and of relatively short lifespan. In the event of a breakdown, it is practically impossible to carry out a repair without completely changing the entire device.

La technique a évolué ensuite du côté "panneaux chauffants" c'est-à-dire la mise en place de plaques ou tapis d'une structure composite fibreuse dans laquelle des fibres conductrices sont dispersées (qu'elles soient en bore ou en carbone). L'alimentation en courant électrique devant parcourir les fibres est réalisée par la connexion de fils à un cadre métallique rapporté au bord du panneau et maintenu au contact des fibres ou à un dépôt métallique, réalisé par vaporisation ou par voie électrolytique, aux extrémités du panneau contenant les fibres. Outre l'inconvénient d'être de montage et d'agencement complexes, ces dispositifs présentent un défaut majeur en ce qui concerne les contacts électriques nécessaires entre les fibres et les fils d'alimentation. On sait en effet que les résines utilisées dans les matériaux composites ont un pouvoir adhérent assez moyen, de sorte que peuvent se produire des décollements des clinquants métalliques distribuant le courant aux fibres. L'amélioration du collage conduit à augmenter la résistance des points de contact entraînant une surchauffe très localisée dégradant colle et résine et donc à une fragilisation de la liaison mécanique et une rupture de la liaison électrique. Par ailleurs, les surépaisseurs qui existent aux endroits des connexions électriques sont préjudiciables au respect du profil aérodynamique de la voilure et constituent une gêne à la mise en place correcte des structures de blindage et de protection des bords d'attaque contre les chocs et l' érosion.The technique then evolved on the "heating panels" side, that is to say the placing of plates or mats of a fibrous composite structure in which conductive fibers are dispersed (whether boron or carbon) . The supply of electric current to pass through the fibers is carried out by the connection of wires to a metal frame attached to the edge of the panel and kept in contact with the fibers or to a metal deposit, produced by vaporization or by electrolytic means, at the ends of the panel containing the fibers. In addition to the drawback of being of complex assembly and arrangement, these devices have a major defect with regard to the necessary electrical contacts between the fibers and the supply wires. It is known in fact that the resins used in the composite materials have a fairly average adhesive power, so that detachments of the metallic foils can distribute the current to the fibers. The improvement in bonding leads to an increase in the resistance of the contact points resulting in very localized overheating degrading adhesive and resin and therefore to weakening of the mechanical connection and rupture of the electrical connection. Furthermore, the extra thicknesses which exist at the points of the electrical connections are detrimental to the respect of the aerodynamic profile of the airfoil and constitute a hindrance to the correct positioning of the shielding structures and of protection of the leading edges against shocks and the erosion.

Un tel dispositif est connu du document EP-A-38922.Such a device is known from document EP-A-38922.

La présente invention entend remédier à ces inconvénients en proposant un dispositif de dégivrage dans lequel le ou les éléments chauffants sont intégrés sans altération de la résistance du bord d'attaque de la voilure, et sont connectés aux fils d'alimentation d'une manière extrêmement stable sans constituer de points critiques tant du point de vue électrique que du point de vue mécanique. Le dispositif par ailleurs est obtenu par un procédé de fabrication simple qui lui permet d'être aisément adapté au profil d'aile ou de pale à équiper voire à y être intégré au moment même de la fabrication de l'aile ou de la pale.The present invention intends to remedy these drawbacks by proposing a deicing device in which the heating element or elements are integrated without altering the resistance of the leading edge of the airfoil, and are connected to the supply wires in an extremely stable without constituting critical points both from the electrical point of view and from the mechanical point of view. The device is also obtained by a simple manufacturing process which allows it to be easily adapted to the wing or blade profile to be fitted or even to be integrated therein at the same time of the manufacture of the wing or the blade.

A cet effet l'invention a donc pour premier objet un élément à résistance électrique entrant dans la constitution d'un dispositif de dégivrage d'une structure alaire telle que la voilure d'un avion ou les pales d'un hélicoptère comprenant des fibres conductrices noyées dans une structure à fibres composites et des fils d'alimentation connectés électriquement auxdites fibres conductrices.To this end, the invention therefore has as its first object an element with electrical resistance forming part of a device for deicing a wing structure such as the wing of an airplane or the blades of a helicopter comprising conductive fibers. drowned in a composite fiber structure and supply wires electrically connected to said conductive fibers.

Selon l'une des caractéristiques principales de l'invention, les fibres conductrices sont des fibres de carbone se présentant sous la forme d'au moins un ruban dans lequel les fibres sont orientées longitudinalement, préimprégné de résine et dont au moins une extrémité est assujettie dans un élément tubulaire déformable à mailles métalliques assurant la liaison électrique par contact avec ledit ruban et par soudure ou sertissage avec le fil d'alimentation correspondant.According to one of the main characteristics of the invention, the conductive fibers are carbon fibers in the form of at least one ribbon in which the fibers are oriented longitudinally, prepreg of resin and of which at least one end is subject in a deformable tubular element with metallic meshes ensuring the electrical connection by contact with said strip and by welding or crimping with the corresponding supply wire.

Un second objet de l'invention réside dans un dispositif de dégivrage comportant au moins l'un des éléments susdits et qui est constitué par une longueur, déterminée en fonction de la résistance à obtenir du ruban de fibres de carbone susdit, y compris la partie du ruban recouverte par ledit élément tubulaire, disposée entre au moins deux couches d'un matériau composite de manière à former un tapis chauffant.A second object of the invention resides in a de-icing device comprising at least one of the aforementioned elements and which consists of a length, determined as a function of the resistance to be obtained from the above-mentioned carbon fiber ribbon, including the part tape covered by said tubular element, disposed between at least two layers of a composite material so as to form a heating mat.

En outre, l'élément susdit pourra être constitué d'au moins deux tronçons de ruban parallèles et côte à côte disposés de part et d'autre d'une couche intercalaire de matériau composite et reliés en série par l'une de leurs extrémités au moyen d'un tronçon de ruban chevauchant lesdites extrémités non recouvertes par ladite couche intercalaire.In addition, the aforementioned element may consist of at least two sections of parallel and side by side ribbon arranged on either side of an intermediate layer of composite material and connected in series by one of their ends to the by means of a section of ribbon overlapping said ends not covered by said intermediate layer.

Enfin un troisième objet de l'invention est le procédé de réalisation du dispositif de dégivrage ci-dessus dans lequel le tapis chauffant est formé à plat puis est placé entre une forme et une contre-forme où il est polymérisé sous pression pour obtenir le profil du bord d'attaque de la structure alaire à équiper.Finally, a third object of the invention is the method for producing the above defrosting device in which the heating mat is formed flat and then is placed between a form and a counterform where it is polymerized under pressure to obtain the profile. the leading edge of the wing structure to be fitted.

On pourra ensuite fixer le dispositif ainsi formé sur la structure alaire. On pourra également disposer le dispositif réalisé à plat entre la forme et la contre-forme que comprend le dispositif de moulage de la structure alaire elle-même en matériau composite de même nature que celui du tapis chauffant.We can then fix the device thus formed on the wing structure. It is also possible to arrange the device produced flat between the shape and the counterform that the device for molding the wing structure itself made of composite material of same nature as that of the heating mat.

L' invention sera mieux comprise au cours de la description donnée ci-après à titre d'exemple purement indicatif et non limitatif qui permettra d'en dégager les avantages et les caractéristiques secondaires.The invention will be better understood during the description given below by way of purely indicative and non-limiting example which will make it possible to identify the advantages and the secondary characteristics thereof.

Il sera fait référence aux dessins annexés dans lesquels :

  • la figure 1 illustre schématiquement les principales caractéristiques de l'élément selon l'invention ;
  • la figure 2 illustre la constitution dans son principe d'un dispositif de dégivrage ;
  • les figures 3 à 10 illustrent les étapes successives de fabrication d'un dispositif de dégivrage dans lequel les éléments résistants sont montés en étoile et destinés à être alimentés en courant triphasé.
Reference will be made to the appended drawings in which:
  • Figure 1 schematically illustrates the main features of the element according to the invention;
  • Figure 2 illustrates the constitution in principle of a deicing device;
  • Figures 3 to 10 illustrate the successive stages in the manufacture of a deicing device in which the resistive elements are mounted in a star and intended to be supplied with three-phase current.

En se reportant tout d'abord à la figure 1 on voit l'extrémité d'un élément 1, résistant du point de vue électrique, constitué par un ruban 2 de fibres de carbone orientées parallèlement à la dimension longitudinale du ruban, et préimprégné d'une résine apte à être polymérisée et durcie. On notera que pour une section de 3 millimètres carrés la section de carbone pur est, dans un ruban utilisé de l'ordre de 1,9 mm². L'une des extrémités 2a du ruban est coiffée d'un élément tubulaire 3 à mailles constitué par tricotage d'un fil métallique approprié. A ce tricot est soudé à l'étain un fil d'alimentation 4 dans une zone où le manchon est rassemblé autour du fil et/ou dans une zone du manchon recouvrant à la fois le ruban et une extrémité du fil qui y est introduite. L'un des avantages de la connexion électrique réalisée par ces moyens réside dans le fait que le tricot métallique s'imprime aisément dans la résine du ruban de carbone qui après polymérisation sous pression constitue un moyen d'accrochage possédant une très bonne résistance à l'arrachement. Le contact intime des fils métalliques et des fibres de carbone du ruban est facteur de bonne qualité du contact électrique.Referring first to Figure 1 we see the end of an element 1, resistant from the electrical point of view, consisting of a ribbon 2 of carbon fibers oriented parallel to the longitudinal dimension of the ribbon, and prepreg d '' a resin capable of being polymerized and hardened. It will be noted that for a section of 3 square millimeters the section of pure carbon is, in a ribbon used of the order of 1.9 mm². One end 2a of the tape is covered with a tubular element 3 consisting knitted by knitting a suitable wire. To this knit is soldered to tin a supply wire 4 in an area where the sleeve is gathered around the wire and / or in an area of the sleeve covering both the ribbon and one end of the wire which is introduced therein. One of the advantages of the electrical connection made by these means lies in the fact that the metallic knit is easily printed in the resin of the carbon ribbon which, after polymerization under pressure, constitutes a means of attachment having very good resistance to l 'tearing. The intimate contact of the metallic wires and carbon fibers of the ribbon is a factor in the good quality of the electrical contact.

La figure 2 montre que pour réaliser un dispositif de dégivrage avec l'élément 1 susdit on dispose sur un substrat de base 5 isolant (par exemple tissu de verre de préférence préimprégné) et de dimensions correspondant au développé du dispositif, un élément 6 tel que 1 susdit qui est ici constitué par trois tronçons 6a, 6b, 6c de ruban de fibres de carbone qui forment une résistance électrique d'une valeur qui dépendra, pour une section donnée du ruban, de la longueur totale de l'élément 6. Les extrémités libres des tronçons 6a et 6c sont équipés de tricots tubulaires soudés à l'étain aux fils de connexion 7a 7b. Une seconde couche de protection 8 identique à la couche 5 recouvre cette dernière et l'élément 6 qu'elle porte. Le tapis ainsi constitué peut être polymérisé sous pression entre une forme et une contre-forme reproduisant le profil de l'aile sur laquelle le dispositif sera accosté. On aura pris soin de placer les substrats 5 et 8 de manière qu' ils recouvrent complètement les extrémités des tronçons 6a et 6b gainées du manchon tricoté pour que seuls les conducteurs 7a et 7b soient situés à l'extérieur de l'ensemble. La pression appliquée lors de la polymérisation permet d'une part, d'ancrer fermement les manchons dans la résine du ruban et d'autre part d'assurer un contact intime entre les deux substrats 5 et 8 dans la zone entre les deux tronçons 6a 6c créant une isolation efficace de l'un par rapport à l'autre.FIG. 2 shows that in order to produce a defrosting device with the above-mentioned element 1, an element 6 such as that on an insulating base substrate 5 (for example glass fabric preferably prepreg) is provided, 1 aforesaid which is constituted by three sections 6a, 6b, 6c ribbon of carbon fibers that form an electrical resistance of a value which will depend, for a given section of the ribbon, of the total length of the element 6. The free ends of the sections 6a and 6c are fitted with tubular knits soldered in tin to the connection wires 7a 7b. A second protective layer 8 identical to layer 5 covers the latter and the element 6 which it carries. The mat thus formed can be polymerized under pressure between a shape and a counter-shape reproducing the profile of the wing on which the device will be docked. Care will have been taken to place the substrates 5 and 8 so that they completely cover the ends of the sections 6 a and 6 b sheathed with the knitted sleeve so that only the conductors 7 a and 7 b are located outside of the together. The pressure applied during the polymerization makes it possible on the one hand to firmly anchor the sleeves in the resin of the ribbon and on the other hand to ensure intimate contact between the two substrates 5 and 8 in the area between the two sections 6 a 6 c creating effective isolation from one with respect to the other.

En outre le tronçon 6b ayant été simplement posé à l'extrémité des tronçons 6a et 6c, la pression permet également d'obtenir une bonne continuité électrique entre eux.Further section 6b being simply placed on the end sections 6a and 6c, the pressure also provides good electrical continuity therebetween.

Les figures 3 à 10 illustrent la constitution d'un dispositif de dégivrage destiné à être alimenté en courant triphasé. Sur un substrat de support 9 semblable à celui 5 de la figure 2 on place trois tronçons 10 de ruban de fibres de carbone préimprégné parallèles et régulièrement espacés l'un de l'autre d'une distance au moins égale à la largeur du ruban. Un tronçon de ruban 11 chevauchant l'une de leurs trois extrémités constitue le commun du montage en triangle des trois résistances que comportera le dispositif. Une couche intercalaire 12 également en tissu de verre de préférence préimprégné est ensuite placée sur les tronçons 10 et 11 de manière à laisser découvertes les extrémités 10a des tronçons 10. Sur cette couche intercalaire 12 et entre les tronçons 10 on place à nouveau trois tronçons 13 de ruban de fibres de carbone pour que l'une de leurs extrémités soit à côté des extrémités 10a susdites tandis que leur autre extrémité affleure le bord transversal inférieur de la couche 9. On réalise la continuité électrique entre chaque tronçon 10 et le tronçon 13 correspondant au moyen de petits tronçons 14 qui les chevauchent deux à deux dans la zone laissée découverte par la couche intercalaire 12. Les extrémités libres des tronçons 13 sont ensuite pourvues de manchons tubulaires 15 en tricot métallique eux-mêmes soudés à l'étain aux fils d'alimentation 16. Enfin un substrat de protection 17 identique au substrat 9 recouvre l'ensemble.Figures 3 to 10 illustrate the constitution of a defrosting device intended to be supplied with three-phase current. On a support substrate 9 similar to that 5 in FIG. 2, three sections 10 of ribbon of prepreg carbon fibers are placed parallel and regularly spaced from each other by a distance at least equal to the width of the ribbon. A section of overlapping ribbon 11 one of their three ends constitutes the common of the triangle mounting of the three resistors that the device will include. An intermediate layer 12 also made of preferably pre-impregnated glass fabric is then placed on the sections 10 and 11 so as to leave the ends 10 has sections 10. On this intermediate layer 12 and between the sections 10 three sections are again placed 13 of carbon fiber ribbon so that one of their ends is next to the ends 10 a above, while their other end is flush with the lower transverse edge of the layer 9. Electric continuity is produced between each section 10 and the section 13 corresponding by means of small sections 14 which overlap them two by two in the area left uncovered by the intermediate layer 12. The free ends of the sections 13 are then provided with tubular sleeves 15 in metallic knit themselves welded with tin to supply wires 16. Finally, a protective substrate 17 identical to the substrate 9 covers the assembly.

Le dispositif de dégivrage confectionné de manière très simple à plat peut ensuite être polymérisé sous pression en forme dans un moule approprié. Il peut être également incorporé dans le moule même de constitution de la structure alaire (aile d'avion ou pale d'hélicoptère) elle-même en matériau composite. Dans ce dernier cas on aura choisi des substrats 9, 12 et 17 de même nature que ceux qui sont utilisés pour la constitution des ailes ou pales.The defrosting device made in a very simple manner flat can then be polymerized under pressure into a suitable mold. It can also be incorporated into the very mold for constituting the wing structure (airplane wing or helicopter blade) itself made of composite material. In the latter case, we will have chosen substrates 9, 12 and 17 of the same kind as those which are used for the constitution of the wings or blades.

L'invention trouve une application intéressante dans le domaine de l'aéronautique.The invention finds an interesting application in the field of aeronautics.

Claims (3)

  1. De-icing device for a wing structure such as the wings of an aeroplane or the blades of a helicopter, comprising an electrical resistance element (1) with conductive carbon fibres which are embedded in a composite fibre/synthetic resin structure and are arranged between at least two layers (5,8) of a pre-impregnated composite fibre material, constituting an electrical insulation so as to form a heating mat and supply wires electrically connected to the said conductive fibres, characterised in that the conductive fibres are in the form of at least one tape (2) in which the fibres are arranged longitudinally, and which is pre-impregnated with resin, and at least one end of which is fastened in a deformable tubular element (3) of metallic mesh providing the electrical connection by contact with the said tape and by soldering to the corresponding supply wire (4).
  2. De-icing device produced from at least one element according to Claim 1, characterised in that it is formed by a length (6a,6b,6c), determined as a function of the resistance to be obtained, of the said conductive fibre tape, including the part of the tape covered by the said tubular element.
  3. Device according to Claim 2, characterised in that the said element consists of at least two tape sections (10,13), parallel and side by side, arranged on each side of an insert layer (12) of insulating composite material and connected in series by one of their ends by means of a tape section (14) overlapping the said ends not covered by the said insert layer (12).
EP85402600A 1984-12-26 1985-12-23 De-icing device for a wing structure Expired - Lifetime EP0188160B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8419801 1984-12-26
FR8419801A FR2578377B1 (en) 1984-12-26 1984-12-26 HEATING ELEMENT FOR A DEFROSTING DEVICE OF A WING STRUCTURE, DEVICE AND METHOD FOR OBTAINING SAME

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EP0188160A1 EP0188160A1 (en) 1986-07-23
EP0188160B1 true EP0188160B1 (en) 1991-06-05

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EP85402600A Expired - Lifetime EP0188160B1 (en) 1984-12-26 1985-12-23 De-icing device for a wing structure

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US (1) US4737618A (en)
EP (1) EP0188160B1 (en)
JP (1) JPH0747400B2 (en)
CA (1) CA1258481A (en)
DE (1) DE3583133D1 (en)
FR (1) FR2578377B1 (en)
IN (1) IN165810B (en)

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Also Published As

Publication number Publication date
FR2578377A1 (en) 1986-09-05
DE3583133D1 (en) 1991-07-11
US4737618A (en) 1988-04-12
JPH0747400B2 (en) 1995-05-24
EP0188160A1 (en) 1986-07-23
JPS61157495A (en) 1986-07-17
IN165810B (en) 1990-01-13
CA1258481A (en) 1989-08-15
FR2578377B1 (en) 1988-07-01

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