WO2015158964A1 - Method for producing aircraft structural parts and device for implementing same - Google Patents

Method for producing aircraft structural parts and device for implementing same Download PDF

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Publication number
WO2015158964A1
WO2015158964A1 PCT/FR2014/050908 FR2014050908W WO2015158964A1 WO 2015158964 A1 WO2015158964 A1 WO 2015158964A1 FR 2014050908 W FR2014050908 W FR 2014050908W WO 2015158964 A1 WO2015158964 A1 WO 2015158964A1
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WIPO (PCT)
Prior art keywords
fact
piece
aeronautical
aluminum
al2o3
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PCT/FR2014/050908
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French (fr)
Inventor
Jean-Pierre LAVOUTE
Original Assignee
Figeac Aero
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Priority to PCT/FR2014/050908 priority Critical patent/WO2015158964A1/en
Publication of WO2015158964A1 publication Critical patent/WO2015158964A1/en

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/026—Anodisation with spark discharge
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/04—Anodisation of aluminium or alloys based thereon
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/18—Floors
    • B64C1/20—Floors specially adapted for freight
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
    • B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
    • B64D11/0696—Means for fastening seats to floors, e.g. to floor rails

Definitions

  • the present invention relates to the field of aeronautics and particularly to adaptations to improve the characteristics of aircraft structural parts.
  • a first solution consists of:
  • OAC type anodization ie by chromic anodic oxidation, or of OAS type, that is to say by anodic sulfuric oxidation, and
  • Such a solution has the disadvantage of being considered as polluting and / or having a salt spray time too low.
  • a second solution is to make the titanium alloy piece and cover it with paint. Such a solution has the drawback of presenting a high cost.
  • WO99 / 45177 discloses an anodizing process which provides improved coatings for applications such as adhesive fixation and aluminum brake cylinder processing.
  • the document WO2010 / 102609 describes a process for producing an abrasive coating on a light metal surface of a part of a turbomachine, in particular a compressor or turbine blade, which is characterized in that the coating is formed by a transformation of the ceramic oxide surface.
  • This document also describes a part for a turbomachine, especially a dawn compressor or turbine, which is characterized in that the light metal surface of the workpiece comprises an oxide ceramic abrasive coating.
  • US 2002/01844964 discloses a hard, wear resistant, ceramic coating, and applied to a spinning rotor in an electrolytic bath in which an electric current is imposed.
  • a special electrode has been designed to facilitate the application of the coating to the unique shape of a spinning rotor.
  • XP 002699731 discloses a method of creating a ceramic coating by arc anodizing an aluminum substrate.
  • Document XP 055068612 describes the use of a lithium aluminum alloy as an alloy to be used in aeronautics.
  • US 4256547 discloses a chromic anodic oxidation process of an aluminum alloy.
  • US 3359189 discloses a method and apparatus for continuous anodization.
  • Aeronautical aluminum alloy structural parts are large parts of up to several meters. The study of these documents shows that these parts are not currently subject to a surface treatment by ceramic creation and this because of their size. It further shows that the process used for the creation of the ceramic, the substrate used and the crystalline phases that can be obtained can be optimized.
  • the invention proposes the creation of a ceramic coating on parts that until now, compared to existing tools, could not be the subject of a process by oxidation by micro arc.
  • the aeronautical structural part is a reinforcement part of the aircraft's cell.
  • the reinforcing rails which are linear parts and the fuselage frames which are elongated parts are examples of parts concerned by the invention.
  • said linear piece of aeronautical structure is a seat rail.
  • the realization of such a surface treatment on a piece having the dimensions of an aeronautical structural part such as a seat rail is particularly innovative and particularly useful in that it allows to apply the surface treatment to a room of structure exposed to corrosion in an area considered wet in an airplane.
  • the seat rail has a complex profile including a preformed upper part of a groove welcoming and retaining the seat attachment modules. This groove has hard-to-reach surfaces which do not make it obvious for a person skilled in the art to envisage for such a part an embodiment of an electrolytic type micro arc oxidation type surface treatment.
  • the addition of material and the necessary good regularity of the surface treatment requires that the base part sees all or part of its modified dimensions before and / or after the surface treatment. It is therefore not obvious that the part to undergo the treatment is identical to the basic one not to undergo said treatment.
  • a range of modification of the rail dimensions of the order of one hundredth (10 to 50 ⁇ ) has been defined.
  • another characteristic of the method of the invention is to manufacture an aeronautical structural part with nominal dimensions reduced compared to the original part or the final part to obtain in order to facilitate the electrolysis and to take account of the supply of material so that the part with surface treatment obtained adopts the same final dimensions as the original part without surface treatment.
  • said structural part is made of aluminum in one of the following shades: 7175, 7075, 7150, 7055, 7136 or 7349. Said piece forming the substrate is thus proposed in an aluminum alloy of the 7000 series (aluminum + zinc).
  • the aeronautical structural part is made of aluminum alloy of the 2000 series (aluminum + copper).
  • said structural part is made of aluminum-lithium C460. Tests have shown that an aeronautical structural part made of 2099 T83 (C460) lithium aluminum coated with 40 ⁇ of ceramic created by micro-arc oxidation in accordance with the invention has 2000 hours salt spray.
  • the ceramic layer has a thickness of 20 ⁇ .
  • the surface-formed material is then an amorphous ceramic comprising Al 2 O 3 alumina crystalline phases.
  • these crystalline phases are as follows:
  • AI203 (a-AI203, ⁇ -AI203, ⁇ -AI203, ⁇ -AI203, ⁇ -AI203)
  • the surface-formed material also comprises aluminum silicate phases, namely the mullite of the chemical formula AI 4 + 2 x Si 2 -2 ⁇ 10-x.
  • the presence of mullite has the effect of reducing the coefficient of friction, to improve the resistance to wear and increase the hardness of the piece obtained. It is therefore not silica incorporated in the surface of the layer obtained by micro-arc oxidation but mullite.
  • the prior art proposes sodium silicate in the composition of electrolytes alone.
  • This embodiment of the process has implemented an electrolyte composed of water and conductive salts.
  • the invention relates more particularly to pieces longer than 2 meters, dimension from which there is currently no solution to implement such a method.
  • the invention also relates to the seat rail and any other piece of aeronautical structure obtained by the method.
  • the invention also relates to the device for implementing said method.
  • the device comprises an electrolysis box accommodating counter electrodes and in which is engaged and from which is freed section by section the aeronautical structure part so as to perform the electrolysis operation progressively on the piece progressing longitudinally in the box.
  • Figure 1 is a schematic drawing of a top view of an embodiment of a seat rail according to the invention.
  • Figure 2 is a schematic drawing of a sectional view of a seat rail obtained according to the method of the invention
  • Figure 3 is a schematic drawing of a first counter electrode configuration
  • Figure 4 is a schematic drawing of a second counter electrode configuration.
  • the rail referenced R As illustrated by the drawing of Figure 1, the rail referenced R as a whole, is immersed in an electrolysis tank in which it will undergo oxidation by micro arc allowing it to be coated on its entire surface with a layer ceramic coating referenced C illustrated by the drawing of Figure 2.
  • FIG. 3 illustrates an embodiment of an annular geometry of a counter-electrode 100 whose radius makes it possible to pass the rail R in its inner circle.
  • FIG. 4 illustrates another embodiment of a counterelectrode disposition geometry 200, whose spacing allows the passage of the rail between them.
  • the upper counter electrode 2 is preformed with a downward projection 21 1 to facilitate deposition of material in the groove of the upper portion of the rail R.
  • the Applicant has imagined that the electrolysis operation is carried out progressively section by section from an electrolysis box accommodating said counter electrodes and in which the rail engages longitudinally, such as the passage in a die, so that a reception volume of the rail corresponding to its total length is not necessary.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

The invention concerns a method for producing a linear or elongate aircraft structural part of large dimensions of up to several metres, remarkable in that it consists of producing said part from an aluminium alloy and of carrying out an electrolytic micro arc oxidation surface treatment on same with a view to obtaining a ceramic coating. The invention also concerns a device for implementing said method. Applications: the production of aircraft structural parts

Description

PROCÉDÉ DE FABRICATION DE PIÈCES DE STRUCTURE AÉRONAUTIQUE ET DISPOSITIF PERMETTANT DE LE METTRE EN OEUVRE  METHOD FOR MANUFACTURING AERONAUTICAL STRUCTURE PARTS AND DEVICE FOR IMPLEMENTING THE SAME
DOMAINE D'APPLICATION DE L'INVENTION FIELD OF APPLICATION OF THE INVENTION
La présente invention a trait au domaine de l'aéronautique et notamment aux adaptations permettant d'améliorer les caractéristiques des pièces de structure aéronautique.  The present invention relates to the field of aeronautics and particularly to adaptations to improve the characteristics of aircraft structural parts.
DESCRIPTION DE L'ART ANTÉRIEUR DESCRIPTION OF THE PRIOR ART
Afin d'améliorer la résistance à la corrosion des pièces de structure aéronautique, les fabricants disposent aujourd'hui de deux solutions décrites ci-dessous.  In order to improve the corrosion resistance of aeronautical structural components, manufacturers now have two solutions described below.
Une première solution consiste :  A first solution consists of:
- à fabriquer la pièce en alliage d'aluminium,  - to manufacture the aluminum alloy part,
- à lui faire réaliser un traitement de surface par anodisation de type OAC, c'est à dire par oxydation anodique chromique, ou de type OAS c'est à dire par oxydation anodique sulfurique, et to make it carry out a surface treatment by OAC type anodization, ie by chromic anodic oxidation, or of OAS type, that is to say by anodic sulfuric oxidation, and
- à la recouvrir de peinture.  - to cover it with paint.
Une telle solution a pour inconvénient d'être considérée comme polluante et/ou de présenter un temps de tenue au brouillard salin trop faible.  Such a solution has the disadvantage of being considered as polluting and / or having a salt spray time too low.
Une deuxième solution consiste à fabriquer la pièce en alliage de titane et à la recouvrir de peinture. Une telle solution a pour inconvénient de présenter un coût élevé.  A second solution is to make the titanium alloy piece and cover it with paint. Such a solution has the drawback of presenting a high cost.
Le choix entre ces deux solutions est réalisé selon le problème de corrosion dans les zones sensibles de l'avion, le titane possédant une meilleure résistance à la corrosion que l'aluminium. The choice between these two solutions is made according to the corrosion problem in the sensitive areas of the aircraft, titanium having a better corrosion resistance than aluminum.
D'autres solutions sont décrites ci-après.  Other solutions are described below.
Le document W099/45177 décrit un procédé d ' anodisation qui permet d'obtenir des revêtements améliorés pour des applications telles que la fixation adhésive et le traitement de cylindres de frein en aluminium.  WO99 / 45177 discloses an anodizing process which provides improved coatings for applications such as adhesive fixation and aluminum brake cylinder processing.
Le document WO2010/102609 décrit un procédé de fabrication d'un revêtement abrasif sur une surface en métal léger d'une pièce d'une turbomachine , notamment d'une aube de compresseur ou de turbine, qui est caractérisé en ce que le revêtement est formé par une transformation de la surface en céramique d'oxyde. Ce document décrit également une pièce pour une turbomachine, notamment une aube de compresseur ou de turbine, qui est caractérisée en ce que la surface de métal léger de la pièce comporte un revêtement abrasif en céramique d'oxyde. The document WO2010 / 102609 describes a process for producing an abrasive coating on a light metal surface of a part of a turbomachine, in particular a compressor or turbine blade, which is characterized in that the coating is formed by a transformation of the ceramic oxide surface. This document also describes a part for a turbomachine, especially a dawn compressor or turbine, which is characterized in that the light metal surface of the workpiece comprises an oxide ceramic abrasive coating.
Le document US 2002/01844964 décrit un revêtement dur, résistant à l'usure, en céramique, et appliqué à un rotor de filature dans un bain électrolytique dans lequel est imposé un courant électrique. Une électrode spéciale a été conçue pour faciliter l'application du revêtement à la forme unique d'un rotor de filature.  US 2002/01844964 discloses a hard, wear resistant, ceramic coating, and applied to a spinning rotor in an electrolytic bath in which an electric current is imposed. A special electrode has been designed to facilitate the application of the coating to the unique shape of a spinning rotor.
Le document XP 002699731 décrit un procédé de création d'un revêtement céramique par anodisation par arc d'un substrat d ' aluminium.  XP 002699731 discloses a method of creating a ceramic coating by arc anodizing an aluminum substrate.
Le document XP 055068612 décrit l'utilisation d'un alliage lithium aluminium comme alliage à exploiter en aéronautique.  Document XP 055068612 describes the use of a lithium aluminum alloy as an alloy to be used in aeronautics.
Le document US 4256547 décrit un procédé d'oxydation anodique chromique d'un alliage d'aluminium.  US 4256547 discloses a chromic anodic oxidation process of an aluminum alloy.
Le document US 3359189 décrit un procédé et un dispositif pour une anodisation continue.  US 3359189 discloses a method and apparatus for continuous anodization.
Les pièces de structure aéronautique en alliage d'aluminium sont des pièces de grandes dimensions allant jusqu'à plusieurs mètres. L'étude de ces documents montre que ces pièces ne font pas aujourd'hui l'objet d'un traitement de surface par création de céramique et ceci du fait de leurs dimensions. Elle montre en outre que le procédé utilisé pour la création de la céramique, le substrat utilisé et les phases cristallines susceptibles d'être obtenues peuvent être optimisés.  Aeronautical aluminum alloy structural parts are large parts of up to several meters. The study of these documents shows that these parts are not currently subject to a surface treatment by ceramic creation and this because of their size. It further shows that the process used for the creation of the ceramic, the substrate used and the crystalline phases that can be obtained can be optimized.
DESCRIPTION DE L'INVENTION  DESCRIPTION OF THE INVENTION
Partant de cet état de fait, la demanderesse a mené des recherches visant à proposer un procédé de fabrication permettant de proposer une pièce de structure aéronautique résistante à la corrosion et obviant aux inconvénients précités.  On the basis of this state of affairs, the applicant has conducted research aimed at proposing a manufacturing process making it possible to propose a piece of aeronautical structure that is resistant to corrosion and obviates the aforementioned drawbacks.
Ces recherches ont abouti à un procédé de fabrication nouveau et inventif d'une pièce de structure aéronautique linéaire ou allongée de grandes dimensions allant jusqu'à plusieurs mètres remarquable en ce qu'il consiste à fabriquer ladite pièce dans un alliage d'aluminium et à lui faire réaliser un traitement de surface de type électrolytique d'oxydation par micro arc en vue de l'obtention d'un revêtement céramique. Cette caractéristique apporte une solution de résistance à la corrosion et est particulièrement avantageuse en ce qu'elle est moins polluante, plus résistante au brouillard salin et moins onéreuse que les solutions de l'art antérieur pour des pièces de grandes dimensions allant jusqu'à plusieurs mètres telles celles, objet du procédé, à savoir les pièces de structure aéronautique. This research has resulted in a new and inventive manufacturing process of a piece of linear or elongated aeronautical structure of large dimensions up to several meters remarkable in that it consists in manufacturing said piece in an aluminum alloy and in make it perform an electrolytic oxidation type micro arc surface treatment to obtain a ceramic coating. This characteristic provides a solution for corrosion resistance and is particularly advantageous in that it is less polluting, more resistant to salt spray and less expensive than the solutions of the prior art for large pieces of up to several meters such as those, object of the process, namely aeronautical structural parts.
En revêtant d'une couche de céramique compacte par oxydation microarcs, une étanchéité électrique est créée entre les pièces en aluminium vis-à-vis du matériau composite, ce qui supprime toute corrosion galvanique et permet par conséquent de réduire le coût du matériau aéronautique utilisé en évitant dans la mesure du possible l'utilisation du titane. By coating with a compact ceramic layer by microarcs oxidation, an electrical seal is created between the aluminum parts vis-à-vis the composite material, which eliminates any galvanic corrosion and therefore reduces the cost of the aeronautical material used avoiding as far as possible the use of titanium.
L'invention propose la création d'un revêtement céramique sur des pièces qui jusqu'à aujourd'hui, en regard des outils existants, ne pouvaient faire l'objet d'un procédé par oxydation par micro arc.  The invention proposes the creation of a ceramic coating on parts that until now, compared to existing tools, could not be the subject of a process by oxidation by micro arc.
Selon une caractéristique, la pièce de structure aéronautique est une pièce d'armature de la cellule de l'aéronef.  According to one characteristic, the aeronautical structural part is a reinforcement part of the aircraft's cell.
Les lisses de renforts qui sont des pièces linéaires et les cadres de fuselage qui sont des pièces allongées sont des exemples de pièces concernées par l'invention.  The reinforcing rails which are linear parts and the fuselage frames which are elongated parts are examples of parts concerned by the invention.
Selon une autre caractéristique particulièrement avantageuse de l'invention, ladite pièce linéaire de structure aéronautique est un rail de siège. La réalisation d'un tel traitement de surface sur une pièce présentant les dimensions d'une pièce de structure aéronautique tel un rail de siège est particulièrement novateur et particulièrement utile en ce qu'il permet d'appliquer le traitement de surface à une pièce de structure exposée à la corrosion dans une zone considérée comme étant humide dans un avion. De plus, le rail de siège présente un profil complexe et notamment une partie supérieure préformée d'une gorge accueillant et retenant les modules de fixation des sièges. Cette gorge présente des surfaces difficilement accessibles qui ne rendent pas évident pour un homme de métier d'envisager pour une telle pièce un mode de réalisation d'un traitement de surface de type électrolytique d'oxydation par micro arc.  According to another particularly advantageous feature of the invention, said linear piece of aeronautical structure is a seat rail. The realization of such a surface treatment on a piece having the dimensions of an aeronautical structural part such as a seat rail is particularly innovative and particularly useful in that it allows to apply the surface treatment to a room of structure exposed to corrosion in an area considered wet in an airplane. In addition, the seat rail has a complex profile including a preformed upper part of a groove welcoming and retaining the seat attachment modules. This groove has hard-to-reach surfaces which do not make it obvious for a person skilled in the art to envisage for such a part an embodiment of an electrolytic type micro arc oxidation type surface treatment.
De plus, l'apport de matière ainsi que la nécessaire bonne régularité du traitement de surface requiert que la pièce de base voit tout ou partie de ses cotes modifiées avant et/ou après le traitement de surface. Il n'est donc pas évident que la pièce devant subir le traitement soit identique à celle de base ne devant pas subir ledit traitement. Par exemple, selon un mode de réalisation non limitatif lié au rail de siège, une fourchette de modification des cotes du rail de l'ordre du centième (10 à 50 μιη) a été définie. Ainsi, une autre caractéristique du procédé de l'invention consiste à fabriquer une pièce de structure aéronautique avec des cotes nominales réduites par rapport à la pièce originale ou à la pièce finale à obtenir afin de faciliter 1 ' électrolyse et de tenir compte de l'apport de matière de sorte que la pièce avec traitement de surface obtenu adopte les mêmes cotes finales que la pièce originelle sans traitement de surface. In addition, the addition of material and the necessary good regularity of the surface treatment requires that the base part sees all or part of its modified dimensions before and / or after the surface treatment. It is therefore not obvious that the part to undergo the treatment is identical to the basic one not to undergo said treatment. For example, according to a non-limiting embodiment related to the seat rail, a range of modification of the rail dimensions of the order of one hundredth (10 to 50 μιη) has been defined. Thus, another characteristic of the method of the invention is to manufacture an aeronautical structural part with nominal dimensions reduced compared to the original part or the final part to obtain in order to facilitate the electrolysis and to take account of the supply of material so that the part with surface treatment obtained adopts the same final dimensions as the original part without surface treatment.
Selon une autre caractéristique particulièrement avantageuse de l'invention, ladite pièce de structure est réalisée en aluminium selon une des nuances suivantes : 7175, 7075, 7150, 7055, 7136 ou 7349. Ladite pièce formant le substrat est ainsi proposée dans un alliage aluminium de la série 7000 (aluminium + zinc).  According to another particularly advantageous feature of the invention, said structural part is made of aluminum in one of the following shades: 7175, 7075, 7150, 7055, 7136 or 7349. Said piece forming the substrate is thus proposed in an aluminum alloy of the 7000 series (aluminum + zinc).
Selon une autre caractéristique, la pièce de structure aéronautique est réalisée en alliage aluminium de la série 2000 (aluminium + cuivre).  According to another characteristic, the aeronautical structural part is made of aluminum alloy of the 2000 series (aluminum + copper).
Selon une autre caractéristique particulièrement avantageuse de l'invention, ladite pièce de structure est réalisée en aluminium- lithium C460. Des essais ont montré qu'une pièce de structure aéronautique en aluminium lithium 2099 T83 (C460) revêtue de 40 μιη de céramique créée par oxydation micro-arcs conformément à l'invention tient 2000 heures au brouillard salin.  According to another particularly advantageous feature of the invention, said structural part is made of aluminum-lithium C460. Tests have shown that an aeronautical structural part made of 2099 T83 (C460) lithium aluminum coated with 40 μιη of ceramic created by micro-arc oxidation in accordance with the invention has 2000 hours salt spray.
Selon un autre mode de réalisation, la couche de céramique adopte une épaisseur de 20 μιη.  According to another embodiment, the ceramic layer has a thickness of 20 μιη.
Sur la base de l'alliage ci-dessus, le matériau formé en surface est alors une céramique amorphe comprenant des phases cristallines d'alumine A1203. Selon un mode de réalisation préféré du procédé, ces phases cristallines sont les suivantes :  Based on the above alloy, the surface-formed material is then an amorphous ceramic comprising Al 2 O 3 alumina crystalline phases. According to a preferred embodiment of the process, these crystalline phases are as follows:
AI203 (a- AI203, β- AI203, y- AI203, δ- AI203)  AI203 (a-AI203, β-AI203, γ-AI203, δ-AI203)
De façon inattendue, le matériau formé en surface comprend également des phases de silicate d'aluminium à savoir la mullite de formule chimique AI4+2xSÎ2-2xOio-x. La présence de mullite a pour effet de diminuer le coefficient de frottement, d'améliorer la résistance à l'usure et d'augmenter la dureté de la pièce obtenue. Il ne s'agit donc pas de silice incorporée à la surface de la couche obtenue par oxydation micro-arc mais de mullite. L'art antérieur propose du silicate de sodium dans la composition des seuls électrolytes . Unexpectedly, the surface-formed material also comprises aluminum silicate phases, namely the mullite of the chemical formula AI 4 + 2 x Si 2 -2 × 10-x. The presence of mullite has the effect of reducing the coefficient of friction, to improve the resistance to wear and increase the hardness of the piece obtained. It is therefore not silica incorporated in the surface of the layer obtained by micro-arc oxidation but mullite. The prior art proposes sodium silicate in the composition of electrolytes alone.
Ce mode de réalisation du procédé a mis en œuvre un électrolyte composé d'eau et de sels conducteurs.  This embodiment of the process has implemented an electrolyte composed of water and conductive salts.
Selon un mode de réalisation préféré mais non limitatif, l'invention concerne plus particulièrement les pièces d'une longueur supérieure à 2 mètres, dimension à partir de laquelle il n'existe aujourd'hui aucune solution pour mettre en oeuvre un tel procédé.  According to a preferred embodiment but not limiting, the invention relates more particularly to pieces longer than 2 meters, dimension from which there is currently no solution to implement such a method.
Bien entendu, l'invention concerne également le rail de siège et toute autre pièce de structure aéronautique obtenus selon le procédé .  Of course, the invention also relates to the seat rail and any other piece of aeronautical structure obtained by the method.
De plus, l'invention concerne également le dispositif permettant de mettre en œuvre ledit procédé. En effet, les grandes dimensions des pièces de structure aéronautique et leur complexité ont amené la demanderesse à envisager de nouvelles mises en œuvre. Ainsi selon une caractéristique particulièrement avantageuse, le dispositif comprend un caisson d ' électrolyse accueillant des contre électrodes et dans lequel s'engage et d'où se libère tronçon par tronçon la pièce de structure aéronautique de façon à réaliser l'opération d ' électrolyse progressivement sur la pièce progressant longitudinalement dans le caisson. Une telle solution permet d'envisager la mise en œuvre du procédé quelle que soit la longueur de la pièce de structure aéronautique et est donc particulièrement adaptée à un rail de siège.  In addition, the invention also relates to the device for implementing said method. Indeed, the large dimensions of aeronautical structure parts and their complexity have led the applicant to consider new implementations. Thus, according to a particularly advantageous characteristic, the device comprises an electrolysis box accommodating counter electrodes and in which is engaged and from which is freed section by section the aeronautical structure part so as to perform the electrolysis operation progressively on the piece progressing longitudinally in the box. Such a solution allows to consider the implementation of the method regardless of the length of the aeronautical structural part and is therefore particularly suitable for a seat rail.
Les concepts fondamentaux de l'invention venant d'être exposés ci-dessus dans leur forme la plus élémentaire, d'autres détails et caractéristiques ressortiront plus clairement à la lecture de la description qui suit et en regard des dessins annexés, donnant à titre d'exemple non limitatif, un mode de réalisation d'un rail de siège et d'un dispositif conformes à l'invention.  The basic concepts of the invention having been described above in their most elementary form, other details and characteristics will emerge more clearly on reading the description which follows and with reference to the appended drawings, giving non-limiting example, an embodiment of a seat rail and a device according to the invention.
BRÈVE DESCRIPTION DES DESSINS BRIEF DESCRIPTION OF THE DRAWINGS
La figure 1 est un dessin schématique d'une vue de dessus d'un mode de réalisation d'un rail de siège conforme à l'invention;  Figure 1 is a schematic drawing of a top view of an embodiment of a seat rail according to the invention;
La figure 2 est un dessin schématique d'une vue en coupe d'un rail de siège obtenu selon le procédé de l'invention; La figure 3 est un dessin schématique d'une première configuration de contre électrodes; Figure 2 is a schematic drawing of a sectional view of a seat rail obtained according to the method of the invention; Figure 3 is a schematic drawing of a first counter electrode configuration;
La figure 4 est un dessin schématique d'une deuxième configuration de contre électrodes.  Figure 4 is a schematic drawing of a second counter electrode configuration.
DESCRIPTION D'UN MODE DE RÉALISATION PRÉFÉRÉ DESCRIPTION OF A PREFERRED EMBODIMENT
Comme illustré par le dessin de la figure 1 , le rail référencé R dans son ensemble, est plongé dans une cuve d ' électrolyse dans laquelle il va subir une oxydation par micro arc lui permettant d'être revêtu sur toute sa surface d'une couche de revêtement céramique référencée C illustrée par le dessin de la figure 2 .  As illustrated by the drawing of Figure 1, the rail referenced R as a whole, is immersed in an electrolysis tank in which it will undergo oxidation by micro arc allowing it to be coated on its entire surface with a layer ceramic coating referenced C illustrated by the drawing of Figure 2.
La figure 3 illustre un mode de réalisation d'une géométrie annulaire d'une contre électrode 100 dont le rayon permet de passage du rail R dans son cercle intérieur.  FIG. 3 illustrates an embodiment of an annular geometry of a counter-electrode 100 whose radius makes it possible to pass the rail R in its inner circle.
La figure 4 illustre un autre mode de réalisation d'une géométrie de disposition de contre électrodes 200 , dont l'écartement autorise le passage du rail entre elles. La contre électrode supérieure 2 10 est préformée d'une saillie vers le bas 21 1 pour faciliter le dépôt de matière dans la gorge de la partie supérieure du rail R.  FIG. 4 illustrates another embodiment of a counterelectrode disposition geometry 200, whose spacing allows the passage of the rail between them. The upper counter electrode 2 is preformed with a downward projection 21 1 to facilitate deposition of material in the groove of the upper portion of the rail R.
En regard de la longueur desdites pièces, la demanderesse a imaginé que l'opération d ' électrolyse est réalisée progressivement tronçon par tronçon à partir d'un caisson d ' électrolyse accueillant lesdites contre électrodes et dans lequel s'engage longitudinalement le rail, tel le passage dans une filière, de sorte qu'un volume d'accueil du rail correspondant à sa longueur totale ne soit pas nécessaire .  In view of the length of said parts, the Applicant has imagined that the electrolysis operation is carried out progressively section by section from an electrolysis box accommodating said counter electrodes and in which the rail engages longitudinally, such as the passage in a die, so that a reception volume of the rail corresponding to its total length is not necessary.
On comprend que le rail et son procédé de fabrication, qui vient d'être ci-dessus décrit et représenté, l'ont été en vue d'une divulgation plutôt que d'une limitation. Bien entendu, divers aménagements, modifications et améliorations pourront être apportés à l'exemple ci-dessus, sans pour autant sortir du cadre de 1 ' invention .  It is understood that the rail and its manufacturing method, which has just been described above and shown, have been for the purpose of disclosure rather than limitation. Of course, various arrangements, modifications and improvements may be made to the example above, without departing from the scope of the invention.

Claims

REVENDICATIONS
1. Procédé de fabrication d'une pièce linéaire ou allongée de structure aéronautique de grandes dimensions allant jusqu'à plusieurs mètres, CARACTÉRISÉ PAR LE FAIT QU'il consiste à fabriquer ladite pièce dans un alliage d'aluminium et à lui faire réaliser un traitement de surface de type électrolytique d'oxydation par micro arc en vue de l'obtention d'un revêtement céramique.  1. A method of manufacturing a linear or elongated piece of aeronautical structure of large dimensions up to several meters, CHARACTERIZED BY THE FACT that it consists in manufacturing said piece in an aluminum alloy and to make it perform a treatment electrolytic type micro arc oxidation type to obtain a ceramic coating.
2. Procédé selon la revendication 1, CARACTÉRISÉ EN CE QUE ladite pièce de structure aéronautique est un rail de siège.  2. Method according to claim 1, CHARACTERIZED IN THAT said aeronautical structural part is a seat rail.
3. Procédé selon la revendication 1, CARACTÉRISÉE PAR LE FAIT 3. Method according to claim 1, CHARACTERIZED BY THE FACT
QUE ladite pièce de structure est réalisée en aluminium selon une des nuances suivantes : 7175, 7075, 7150, 7055, 7136 ou 7349. THAT said structural part is made of aluminum in one of the following shades: 7175, 7075, 7150, 7055, 7136 or 7349.
4. Procédé selon la revendication 1, CARACTÉRISÉ PAR LE FAIT QUE ladite pièce de structure est réalisée en aluminium-lithium C460.  4. Method according to claim 1, CHARACTERIZED BY THE FACT THAT said structural part is made of aluminum-lithium C460.
5. Procédé selon la revendication 4, CARACTÉRISÉ PAR LE FAIT QUE le matériau formé en surface est une céramique amorphe comprenant des phases cristallines d'alumine A1203.  5. Method according to claim 4, CHARACTERIZED BY THE FACT THAT the material formed at the surface is an amorphous ceramic comprising crystalline phases of alumina A1203.
6. Procédé selon la revendication 5, CARACTÉRISÉ PAR LE FAIT QUE lesdites phases cristallines sont les suivantes :  6. Process according to claim 5, CHARACTERIZED BY THE FACT THAT said crystalline phases are the following:
AI203 (0- AI203, β- AI203, y- AI203, 5- AI203).  AI203 (O-Al2O3, β-Al2O3, y-Al2O3, 5- Al2O3).
7. Procédé selon la revendication 4, CARACTÉRISÉ PAR LE FAIT QUE le matériau formé en surface comprend des phases de silicate d ' aluminium.  7. The method of claim 4, CHARACTERIZED BY THE FACT THAT the surface-formed material comprises aluminum silicate phases.
8. Procédé selon les revendications 1 ou 2 , CARACTÉRISÉ EN CE 8. Method according to claims 1 or 2, CHARACTERIZED IN THE EC
QU'il consiste à fabriquer une pièce de structure aéronautique avec des cotes nominales réduites par rapport à la pièce originale ou à la pièce finale à obtenir, afin de faciliter 1 ' électrolyse et de tenir compte de l'apport de matière. THAT it consists in manufacturing a piece of aeronautical structure with nominal dimensions reduced compared to the original part or the final piece to obtain, in order to facilitate the electrolysis and take into account the contribution of material.
9. Dispositif permettant de mettre en œuvre le procédé selon la revendication 1 ou 2 , CARACTÉRISÉ PAR LE FAIT QU'il comprend un caisson d'électrolyse accueillant des contre électrodes et dans lequel s'engage et d'où se libère tronçon par tronçon la pièce de structure aéronautique de façon à réaliser l'opération d'électrolyse progressivement sur la pièce progressant longitudinalement dans le caisson .  9. Device for implementing the method according to claim 1 or 2, CHARACTERIZED BY THE FACT THAT it comprises an electrolysis chamber accommodating against electrodes and in which engages and from which is released section by section the aeronautical structure part so as to perform the electrolysis operation progressively on the piece progressing longitudinally in the box.
PCT/FR2014/050908 2014-04-15 2014-04-15 Method for producing aircraft structural parts and device for implementing same WO2015158964A1 (en)

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FR2877018A1 (en) * 2004-10-25 2006-04-28 Snecma Moteurs Sa Manufacture of a coating on a metal substrate, notably of aluminium, by micro arc oxidation to produce a wearing surface for aviation applications such as turbojet engine components
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