EP2373539A1 - Longitudinal joint for aircraft fuselage panels made of composite materials - Google Patents

Longitudinal joint for aircraft fuselage panels made of composite materials

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Publication number
EP2373539A1
EP2373539A1 EP09805809A EP09805809A EP2373539A1 EP 2373539 A1 EP2373539 A1 EP 2373539A1 EP 09805809 A EP09805809 A EP 09805809A EP 09805809 A EP09805809 A EP 09805809A EP 2373539 A1 EP2373539 A1 EP 2373539A1
Authority
EP
European Patent Office
Prior art keywords
panels
smooth
junction
longitudinal
joint
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.)
Withdrawn
Application number
EP09805809A
Other languages
German (de)
French (fr)
Inventor
Patrick Bernard
Sébastien RIVA
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 EP2373539A1 publication Critical patent/EP2373539A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/064—Stringers; Longerons
    • 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
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections
    • B64C1/069—Joining arrangements therefor
    • 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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the invention relates to a longitudinal assembly junction of two aircraft fuselage panels of composite material.
  • This longitudinal junction integrates omega-shaped rails that are particularly suitable for structures made of composite materials.
  • the invention has applications in the field of assembly of aircraft fuselage panels and, in particular, in the field of assembling composite material panels using omega rails as stiffeners.
  • An aircraft fuselage is a structure generally comprising a plurality of substantially cylindrical sections abutting one another along connecting lines, called circumferential junctions, defining planes perpendicular to the longitudinal axis of the fuselage.
  • Each section is generally made up of several panels assembled to each other along junction lines, or joining lines, oriented substantially along generatrices of the fuselage.
  • junctions are zones of fragility of the fuselage that should be reinforced to withstand the strong stresses to which the fuselage is subjected in flight.
  • the panels of a section are assembled along a seam line by means of longitudinal junctions.
  • These longitudinal junctions can be made according to different techniques depending, in particular, the type of structure of the aircraft. For example, in a metal fuselage structure, where all the panels are metal, the longitudinal junctions can be made end-to-end, by means of rails installed along the joint of the panels to be assembled.
  • FIG. 1 shows an example of a metallic aircraft fuselage structure in which the longitudinal junction is made by means of a T-rail.
  • the structure comprises a panel 1 (integrating a window 3). and a panel 2, to assemble with each other.
  • the panel 2 is stiffened by means of a plurality of smooth Z-shaped, referenced 4.
  • the panels 1 and 2 are connected via a smooth T.
  • FIG. 2 shows an example of a longitudinal junction, in a sectional view, made by means of a T-rail.
  • the panels 1 and 2 are each stiffened by Z-shaped rails 4 and assembled. one with the other by a smooth T-shaped 5.
  • This smooth T forms the longitudinal junction along the join 6 panels 1 and 2 to assemble.
  • the T-rail is fixed, as shown in Figure 2, by its horizontal sole 51, on each of the panels 1 and 2.
  • the core 52 of the T-bar allows the recovery of other elements of the structure.
  • the smooth used are generally omega smooth (or smooth ⁇ ), preferably smooth Z or L.
  • the ⁇ plates offer better stability and better resistance to internal pressure.
  • FIG. 3 shows an example of a composite structure stiffened by ⁇ -plates referenced 8.
  • the ⁇ -plate can not be used as a longitudinal junction. Indeed, the positioning of a smooth ⁇ on the joint between the panels to be assembled would not allow recovery of said joint. Also, to achieve an end-to-end longitudinal junction in a composite structure, it has been envisaged to use a T-bar.
  • An example of a longitudinal junction by a T-bar is shown in FIG. previously, the T-plate 5 is fixed by its sole on each of the panels 1 and 2. Smooth 8 in ⁇ are fixed on either side of the joint 6 to stiffen the structure.
  • the introduction of a smooth T-shaped 5 in the middle of smooth 8 in ⁇ has a significant impact on the smoothing, because the T-shaped smooth disrupt the distribution of the smooth ⁇ .
  • the step between smooth is no longer uniform and regular, as shown in Figure 3. Indeed, by their design, the not between two smooth ⁇ and two smooth T are different. Consequently, the introduction of a T-shaped rail to form a longitudinal junction modifies the pitch between rails, close to the joint of the two panels. Smoothing can not be optimized because of the presence of the T-bar.
  • Another longitudinal joining technique is a panel covering technique.
  • This panel overlap technique involves placing the ends of the two panels to be joined together. For this, one of the panels is placed on top of the other, forming at the joint an extra thickness.
  • the covering is made so that the outer panel is installed in the direction of the aerodynamic flow of the fuselage so as not to generate a penalty on the performance of the aircraft.
  • FIG. 6 An example of such a longitudinal overlap junction is shown in Figure 6.
  • the panels 1 and 2 are placed partially on one another. To ensure the assembly of the two panels at their joint, an area of one of the panels is deformed.
  • the end 1a, 1b of the panel 1 is deformed in order to fit under the panel 2.
  • the zone 1a of the panel 1 is deformed so as to be placed under the end of the panel 2.
  • the zone 1 b of the panel 1 is deformed so as to ensure the continuity of the panel between the zone 1 a and the zone 1 c undeformed.
  • the panels 1 and 2 are stiffened by smooth ⁇ .
  • the plate 8 in ⁇ of the panel 2 is fixed by fixing elements 7 through the two thicknesses of panels, that is to say through the panel 2 and through the zone 1a of the panel 1.
  • the realization of the deformed area of the panel is relatively expensive. Indeed, it requires a manufacturing mold of the panel made of specific composite material with a formation of folds for carry out the deformation.
  • the smooth ⁇ is inclined which prevents smooth and uniform smoothing between the set of smooth ⁇ . Indeed, with such a technique, the ⁇ are not all on the same circumferential plane due to the deformation of the end of a panel.
  • the invention proposes a longitudinal junction, edge-to-edge, for assembling two fuselage panels of composite material while maintaining a regular pitch between the rails.
  • This longitudinal junction consists of a double smooth ⁇ having a central sole covering the joint between the two panels.
  • This longitudinal junction allows edge-to-edge assembly of panels with uniform and regular omega smoothing.
  • the invention relates to an aircraft fuselage structure comprising at least a first and a second composite material panel, placed side-by-side along a joint and assembled to one another via at least one longitudinal junction, characterized in that the longitudinal junction consists of a double smooth ⁇ comprising:
  • a first and a second element in ⁇ each comprising a head and two cores
  • the invention may comprise one or more of the following features: the central sole has a length twice that of the first or the second lateral sole.
  • the central sole is made in one piece with the elements in ⁇ and the first and second side insoles.
  • the central sole is attached to each panel by means of fasteners placed on either side of the joint.
  • the longitudinal junction comprises a third smooth mounted on the central sole.
  • the third rail is a T-rail.
  • the longitudinal junction comprises an inner or outer flange mounted on the central sole.
  • the longitudinal junction has an extra thickness integrated in the central sole.
  • the invention also relates to an aircraft fuselage comprising at least two sections assembled by a circumferential junction, characterized in that each section comprises a structure as described above.
  • the invention also relates to an aircraft, characterized in that it comprises at least one structure as described above. Brief description of the drawings
  • FIG. 1, already described, represents an example of longitudinal junction metal fuselage structure made by a T-bar.
  • Figure 2 already described, shows a sectional view of a longitudinal junction T-smooth on a metal structure.
  • Figure 3 already described, represents an omega smoothing section of a composite material structure.
  • Figure 4 already described, shows a sectional view of a longitudinal junction T-smooth on a composite material structure.
  • Figure 5 already described, shows a sectional view of a U-shaped longitudinal junction on a structure of composite material.
  • Figure 6 already described, shows a sectional view of a longitudinal junction panel covering.
  • FIG. 7, already described, represents an example of an aircraft section in which a new longitudinal junction must be integrated.
  • Figure 8 shows a sectional view of a longitudinal junction according to the invention.
  • Figures 9, 10 and 1 1 are examples of longitudinal junctions according to the invention, with insertion of a T-bar, an additional flange or an extra thickness of the bar.
  • the longitudinal junction of the invention comprises a double smooth ⁇ with central sole, adapted to be attached to a joint between two fuselage panels.
  • An example of such a longitudinal junction is shown in FIG. 8.
  • This double-smooth ⁇ junction comprises a first ⁇ element, referenced 21, and a second ⁇ element, referenced 22, connected by a central flange 23.
  • Each of these elements in ⁇ comprises a head, respectively 21a and 22a, and two souls, respectively, 21b, 21c and 22b, 22c.
  • the head of each of these elements in ⁇ , 21, 22, is able to take elements of the structure.
  • the junction 20 also comprises a first sole 24 located in the continuity of the first core 21b of the first element in ⁇ , 21, and a second sole 25 located in the continuity of the second core 22c of the second element in ⁇ , 22 .
  • the elements in ⁇ and side flanges 24 and 25 are identical to the element in ⁇ and the sole of a smooth ⁇ conventional as described above.
  • the junction 20 of the invention further comprises a central sole 23 connecting the second core 21c of the first element in ⁇ 21 with the first core 22b of the second element in ⁇ 22 and covering the joint 6 between the two panels 1 and 2.
  • the central sole 23 has a double length of a conventional ⁇ footplate.
  • the central sole 23 and the lateral soles 24 and 25 are fixed on the panels 1 and 2 by conventional fasteners. Specifically, the sole 24 is fixed on the panel 1 and the sole 25 is fixed on the panel 2. The central sole 23 is fixed on both the panel 1 and the panel 2.
  • the longitudinal junction of the invention has a total dimension corresponding to that of two smooth ⁇ placed end to end. It thus has the advantage of providing a regular pitch between the ⁇ smooth and the longitudinal junction. Indeed, the longitudinal junction 20 having a length twice that of a rail
  • the smoothing is relatively simple to perform because the ⁇ double-smooth junction can be placed at the join of the two panels while maintaining the previous smoothing since the pitch between two smooth ⁇ is retained. It is thus easy to modify a panel cut by inserting a new longitudinal junction since it suffices to replace two smooth ⁇ conventional by a double smooth junction.
  • the longitudinal junction 20 further allows additional elements to be inserted on the center flange 23 to provide additional functions, as required, at said junction.
  • FIG. 9 shows a sectional view of a longitudinal junction according to the invention incorporating a T-bar.
  • a T-bar referenced 30, has been mounted on the central sole 23 of the junction. 20 to allow possible recovery of other elements.
  • This smooth T can be fixed on the central sole 23 by the same fasteners 7 as those fixing the central sole on the panels 1 and 2.
  • the smoothing pitch remains the same as that of ⁇ smoothing because the T-bar is simply installed above the longitudinal seam.
  • This embodiment of the longitudinal junction has been described for a T-bar. It is understood that other types of healds, for example a U-shaped bar, may be installed in place of the T-bar.
  • FIG 10 there is shown a sectional view of a longitudinal junction of the invention incorporating a flange, also called strap.
  • an internal strap is positioned above the central sole 23 and fixed, via the central sole 23, to the panels 1 and 2.
  • a strap is a reinforcing element capable of reinforcing a structure.
  • a strap may be internal, as in Figure 10, that is to say installed on an inner face of the structure. It can also be external, that is to say installed on the external face of the structure.
  • Figure 1 1 there is shown a sectional view of a longitudinal junction of the invention incorporating an extra thickness.
  • an extra thickness is inserted into the central sole 23.
  • This extra thickness 50 can be made of composite material, by means of an additional fold to strengthen the longitudinal junction 20 near the joint 6.
  • the central sole is then made to be thicker, which allows it to provide additional functions or to strengthen the junction between the panels in case of transfer of forces particularly important.
  • FIGS. 8 to 10 there is shown the fastening elements 7 of the longitudinal junction distributed over the set of lateral and central flanges.
  • FIG. 11 only the fastening elements of the central and lateral flanges 23 are shown.
  • the first lateral flange 24 does not comprise a fixing element; it is co-packed with panel 1.
  • junction 20 as just described is made of one and the same piece, according to conventional manufacturing techniques of smooth ⁇ ; only the shape of the manufacturing mold changes in order to obtain the double ⁇ shape. It is therefore possible to co-bond one of the lateral flanges of the omega double-smooth junction on one of the panels, thereby eliminating a row of fasteners and therefore to reduce the overall mass of the aircraft. This embodiment also results in a saving of time during assembly of the panels.
  • the longitudinal junction just described allows the longitudinal assembly end to end of all the panels of the fuselage, regardless of the fuselage section considered. Indeed, even sections of the fuselage strongly conical or that with orbital junctions can be made with the longitudinal junction of the invention, without the need for bias wedges.

Abstract

The invention relates to an aircraft fuselage structure comprising at least first and second panels (1, 2) made of composite materials, placed side-by-side along a joint (6) and assembled together by means of at least one longitudinal joint (20), said longitudinal joint comprising a double Ω-shaped runner comprising: first and second Ω-shaped elements (21, 22), each including a head (21a, 22a) and two webs (21b, 21c, 22b, 22c); a first lateral flange (24) positioned as a continuation of the first web (21b) of the first Ω-shaped element; a second lateral flange (25) positioned as a continuation of the last web (22c) of the second Ω-shaped element; and a central flange (23) connecting the second web (21c) of the first Ω-shaped element with the first web (22b) of the second Ω-shaped element and covering the joint between the two panels.

Description

JONCTION LONGITUDINALE POUR PANNEAUX DE FUSELAGE D'AERONEF EN MATERIAUX COMPOSITES LONGITUDINAL JUNCTION FOR AIRCRAFT FUSELAGE PANELS IN COMPOSITE MATERIALS
Domaine de l'inventionField of the invention
L'invention concerne une jonction d'assemblage longitudinal de deux panneaux de fuselage d'aéronef en matériau composite. Cette jonction longitudinale intègre des lisses en oméga particulièrement adaptées aux structures en matériaux composites. L'invention trouve des applications dans le domaine de l'assemblage de panneaux de fuselage d'aéronef et, en particulier, dans le domaine de l'assemblage de panneaux en matériaux composites utilisant, comme raidisseurs, des lisses en oméga.The invention relates to a longitudinal assembly junction of two aircraft fuselage panels of composite material. This longitudinal junction integrates omega-shaped rails that are particularly suitable for structures made of composite materials. The invention has applications in the field of assembly of aircraft fuselage panels and, in particular, in the field of assembling composite material panels using omega rails as stiffeners.
Etat de la techniqueState of the art
Un fuselage d'aéronef est une structure comportant généralement plusieurs tronçons sensiblement cylindriques aboutés les uns aux autres suivant des lignes de jonction, appelées jonctions circonférentielles, définissant des plans perpendiculaires à l'axe longitudinal du fuselage. Chaque tronçon est généralement constitué de plusieurs panneaux assemblés les uns aux autres suivant des lignes de jonction, ou lignes de jointure, orientées sensiblement suivant des génératrices du fuselage.An aircraft fuselage is a structure generally comprising a plurality of substantially cylindrical sections abutting one another along connecting lines, called circumferential junctions, defining planes perpendicular to the longitudinal axis of the fuselage. Each section is generally made up of several panels assembled to each other along junction lines, or joining lines, oriented substantially along generatrices of the fuselage.
Ces deux types de jonctions sont des zones de fragilité du fuselage qu'il convient de renforcer pour résister aux fortes sollicitations auxquelles le fuselage est soumis en vol.These two types of junctions are zones of fragility of the fuselage that should be reinforced to withstand the strong stresses to which the fuselage is subjected in flight.
Les panneaux d'un tronçon sont assemblés le long d'une ligne de jointure au moyen de jonctions longitudinales. Ces jonctions longitudinales peuvent être réalisées selon différentes techniques en fonction, notamment, du type de structure de l'aéronef. Par exemple, dans une structure de fuselage métallique, où tous les panneaux sont en métal, les jonctions longitudinales peuvent être réalisées en bout-à-bout, au moyen de lisses installées le long de la jointure des panneaux à assembler.The panels of a section are assembled along a seam line by means of longitudinal junctions. These longitudinal junctions can be made according to different techniques depending, in particular, the type of structure of the aircraft. For example, in a metal fuselage structure, where all the panels are metal, the longitudinal junctions can be made end-to-end, by means of rails installed along the joint of the panels to be assembled.
Les lisses sont des pièces profilées utilisées dans une structure de fuselage de l'aéronef pour raidir la peau et certaines zones spécifiques telles que les encadrements de portes et de hublots. Les lisses peuvent avoir des sections de formes différentes, par exemple en T, en Z, en L, etc. Sur la figure 1 , on a représenté un exemple de structure de fuselage d'aéronef métallique dans laquelle la jonction longitudinale est réalisée au moyen d'une lisse en T. Dans cet exemple, la structure comporte un panneau 1 (intégrant un hublot 3) et un panneau 2, à assembler l'un avec l'autre. Le panneau 2 est raidi par l'intermédiaire d'une pluralité de lisses en Z, référencées 4. Les panneaux 1 et 2 sont reliés par l'intermédiaire d'une lisse en T.The rails are profiled parts used in a fuselage structure of the aircraft to stiffen the skin and specific areas such as door frames and portholes. The rails may have sections of different shapes, for example T, Z, L, etc. FIG. 1 shows an example of a metallic aircraft fuselage structure in which the longitudinal junction is made by means of a T-rail. In this example, the structure comprises a panel 1 (integrating a window 3). and a panel 2, to assemble with each other. The panel 2 is stiffened by means of a plurality of smooth Z-shaped, referenced 4. The panels 1 and 2 are connected via a smooth T.
Sur la figure 2, on a représenté un exemple de jonction longitudinale, selon une vue en coupe, réalisée au moyen d'une lisse en T. Dans cet exemple, les panneaux 1 et 2 sont raidis chacun par des lisses 4 en Z et assemblés l'un avec l'autre par une lisse 5 en T. Cette lisse en T forme la jonction longitudinale le long de la jointure 6 des panneaux 1 et 2 à assembler. La lisse en T est fixée, comme montré sur la figure 2, par sa semelle horizontale 51 , sur chacun des panneaux 1 et 2. L'âme 52 de la lisse en T permet la reprise d'autres éléments de la structure.FIG. 2 shows an example of a longitudinal junction, in a sectional view, made by means of a T-rail. In this example, the panels 1 and 2 are each stiffened by Z-shaped rails 4 and assembled. one with the other by a smooth T-shaped 5. This smooth T forms the longitudinal junction along the join 6 panels 1 and 2 to assemble. The T-rail is fixed, as shown in Figure 2, by its horizontal sole 51, on each of the panels 1 and 2. The core 52 of the T-bar allows the recovery of other elements of the structure.
Sur ces figures, et en particulier sur la figure 1 , on voit que le pas entre deux lisses, en Z ou en T, est régulier.In these figures, and in particular in Figure 1, we see that the pitch between two smooth, Z or T, is regular.
Dans un environnement composite, c'est-à-dire dans un aéronef à fuselage au moins partiellement composite, les lisses utilisées sont généralement des lisses en oméga (ou lisses en Ω), de préférence aux lisses en Z ou en L. En effet, les lisses en Ω offrent une meilleure stabilité et une meilleure tenue à la pression interne. On a représenté, sur la figure 3 un exemple d'une structure composite raidie par des lisses en Ω référencées 8.In a composite environment, that is to say in an aircraft with fuselage at least partially composite, the smooth used are generally omega smooth (or smooth Ω), preferably smooth Z or L. Indeed , the Ω plates offer better stability and better resistance to internal pressure. FIG. 3 shows an example of a composite structure stiffened by Ω-plates referenced 8.
Toutefois, de par sa forme non pleine, la lisse en Ω ne peut être utilisée comme jonction longitudinale. En effet, le positionnement d'une lisse en Ω sur la jointure entre les panneaux à assembler ne permettrait pas un recouvrement de ladite jointure. Aussi, pour réaliser une jonction longitudinale en bout-à-bout, dans une structure composite, il a été envisagé d'utiliser une lisse en T. Un exemple de jonction longitudinale par une lisse en T est représenté sur la figure 4. Comme expliqué précédemment, la lisse 5 en T est fixée par sa semelle sur chacun des panneaux 1 et 2. Des lisses 8 en Ω sont fixées de part et d'autre de la jointure 6 pour raidir la structure. Cependant, l'introduction d'une lisse 5 en T au milieu de lisses 8 en Ω a un impact important sur le lissage, car les lisses en T viennent perturber la distribution des lisses en Ω. Le pas entre lisses n'est plus uniforme et régulier, comme montré sur la figure 3. En effet, de par leur conception, les pas entre deux lisses en Ω et deux lisses en T sont différents. En conséquence, l'introduction d'une lisse en T pour former une jonction longitudinale modifie le pas entre lisses, à proximité de la jointure des deux panneaux. Le lissage ne peut alors pas être optimisé du fait de la présence de la lisse en T.However, due to its non-full shape, the Ω-plate can not be used as a longitudinal junction. Indeed, the positioning of a smooth Ω on the joint between the panels to be assembled would not allow recovery of said joint. Also, to achieve an end-to-end longitudinal junction in a composite structure, it has been envisaged to use a T-bar. An example of a longitudinal junction by a T-bar is shown in FIG. previously, the T-plate 5 is fixed by its sole on each of the panels 1 and 2. Smooth 8 in Ω are fixed on either side of the joint 6 to stiffen the structure. However, the introduction of a smooth T-shaped 5 in the middle of smooth 8 in Ω has a significant impact on the smoothing, because the T-shaped smooth disrupt the distribution of the smooth Ω. The step between smooth is no longer uniform and regular, as shown in Figure 3. Indeed, by their design, the not between two smooth Ω and two smooth T are different. Consequently, the introduction of a T-shaped rail to form a longitudinal junction modifies the pitch between rails, close to the joint of the two panels. Smoothing can not be optimized because of the presence of the T-bar.
Une autre technique a été envisagée pour réaliser une jonction longitudinale dans une structure composite raidie par des lisses en Ω. Cette technique consiste à utiliser une lisse 9 en U comme jonction longitudinale, comme montré sur la figure 5. Cependant, cette lisse en U apporte également une perturbation sur la distribution du lissage car elle ne permet pas d'avoir un lissage uniforme et régulier entre les lisses 8 en Ω et la lisse 9 en U.Another technique has been considered to achieve a longitudinal junction in a composite structure stiffened by Ω smooth. This technique consists in using a U-shaped lug 9 as a longitudinal junction, as shown in FIG. 5. However, this U-shaped liner also brings about a disturbance in the distribution of the loft since it does not allow a uniform and regular smoothing between the smooth 8 in Ω and the smooth 9 in U.
Une autre technique de jonction longitudinale est une technique par recouvrement de panneaux. Cette technique de jonction par recouvrement de panneaux consiste à placer les extrémités des deux panneaux à assembler en recouvrement. Pour cela, un des panneaux est placé au- dessus de l'autre, formant à la jointure une surépaisseur. Le recouvrement est réalisé de sorte que le panneau extérieur est installé dans le sens de l'écoulement aérodynamique du fuselage afin de ne pas générer de pénalité sur les performances de l'aéronef.Another longitudinal joining technique is a panel covering technique. This panel overlap technique involves placing the ends of the two panels to be joined together. For this, one of the panels is placed on top of the other, forming at the joint an extra thickness. The covering is made so that the outer panel is installed in the direction of the aerodynamic flow of the fuselage so as not to generate a penalty on the performance of the aircraft.
Un exemple d'une telle jonction longitudinale par recouvrement est représenté sur la figure 6. Sur cette figure, les panneaux 1 et 2 sont placés partiellement l'un sur l'autre. Pour assurer l'assemblage des deux panneaux au niveau de leur jointure, une zone d'un des panneaux est déformée. Dans l'exemple de la figure 6, l'extrémité 1 a, 1 b du panneau 1 est déformée afin de s'insérer sous le panneau 2. La zone 1 a du panneau 1 est déformée de façon à être placée sous l'extrémité du panneau 2. La zone 1 b du panneau 1 est déformée de façon à assurer la continuité du panneau entre la zone 1 a et la zone 1 c non déformée. Dans cet exemple, les panneaux 1 et 2 sont raidis par des lisses en Ω.An example of such a longitudinal overlap junction is shown in Figure 6. In this figure, the panels 1 and 2 are placed partially on one another. To ensure the assembly of the two panels at their joint, an area of one of the panels is deformed. In the example of FIG. 6, the end 1a, 1b of the panel 1 is deformed in order to fit under the panel 2. The zone 1a of the panel 1 is deformed so as to be placed under the end of the panel 2. The zone 1 b of the panel 1 is deformed so as to ensure the continuity of the panel between the zone 1 a and the zone 1 c undeformed. In this example, the panels 1 and 2 are stiffened by smooth Ω.
La lisse 8 en Ω du panneau 2 est fixée par des éléments de fixation 7 à travers les deux épaisseurs de panneaux, c'est-à-dire à travers le panneau 2 et à travers la zone 1 a du panneau 1.The plate 8 in Ω of the panel 2 is fixed by fixing elements 7 through the two thicknesses of panels, that is to say through the panel 2 and through the zone 1a of the panel 1.
Toutefois, la réalisation de la zone déformée du panneau est relativement onéreuse. En effet, elle nécessite un moule de fabrication du panneau en matériau composite spécifique avec une formation de plis pour réaliser la déformation. De plus, dans la zone déformée, la lisse en Ω se trouve inclinée ce qui empêche d'avoir un lissage uniforme et régulier entre l'ensemble des lisses en Ω. En effet, avec une telle technique, les lisses en Ω ne sont pas toutes sur le même plan circonférentiel du fait de la déformation de l'extrémité d'un panneau.However, the realization of the deformed area of the panel is relatively expensive. Indeed, it requires a manufacturing mold of the panel made of specific composite material with a formation of folds for carry out the deformation. In addition, in the deformed area, the smooth Ω is inclined which prevents smooth and uniform smoothing between the set of smooth Ω. Indeed, with such a technique, the Ω are not all on the same circumferential plane due to the deformation of the end of a panel.
Toutes les techniques évoquées précédemment ne permettent pas d'obtenir un lissage optimum de la structure composite. En effet, la technique de jonction utilisant une lisse en T ou une lisse en U nécessite de connaître, au préalable, la position exacte de la lisse de jonction (lisse en T ou en U) pour pouvoir effectuer un lissage en Ω de la structure, le moins dégradé possible (c'est-à-dire le plus régulier possible). Quant à la technique de jonction par recouvrement de panneaux, elle nécessite de connaître la position exacte de la jonction pour pouvoir réaliser le panneau en conséquence. Avec de telles techniques, il est essentiel de connaître la position de la jonction avant de réaliser la structure. Il n'est donc pas possible de modifier la forme d'un panneau de fuselage en utilisant un découpage de panneau déjà existant. Ainsi, pour effectuer un découpage de panneaux différent, nécessitant une nouvelle jonction longitudinale 10, comme montré sur la figure 7, il est nécessaire de modifier entièrement le lissage des panneaux situés autour de cette jonction longitudinale, toute intégration d'une nouvelle jonction longitudinale ayant nécessairement des impacts sur le lissage des panneaux de fuselage.All the techniques mentioned above do not make it possible to obtain optimum smoothing of the composite structure. Indeed, the joining technique using a T-bar or a U-shaped bar requires knowing, beforehand, the exact position of the connecting bar (T-shaped or U-shaped) in order to smooth the structure in Ω. , the least degraded possible (that is to say the most regular possible). As for the panel overlap technique, it requires knowing the exact position of the junction to be able to make the panel accordingly. With such techniques, it is essential to know the position of the junction before making the structure. It is therefore not possible to modify the shape of a fuselage panel by using an existing panel cutout. Thus, to perform a different panel cutting, requiring a new longitudinal junction 10, as shown in Figure 7, it is necessary to completely modify the smoothing of the panels located around this longitudinal junction, any integration of a new longitudinal junction having necessarily impacts on the smoothing of the fuselage panels.
Exposé de l'inventionPresentation of the invention
L'invention a justement pour but de remédier aux inconvénients des techniques exposées précédemment. A cette fin, l'invention propose une jonction longitudinale, de type bord à bord, permettant d'assembler deux panneaux de fuselage en matériau composite tout en conservant un pas régulier entre les lisses. Cette jonction longitudinale est constituée d'une double lisse en Ω comportant une semelle centrale recouvrant la jointure entre les deux panneaux. Cette jonction longitudinale permet un assemblage bord à bord de panneaux avec un lissage uniforme et régulier en oméga.The purpose of the invention is precisely to overcome the disadvantages of the techniques described above. To this end, the invention proposes a longitudinal junction, edge-to-edge, for assembling two fuselage panels of composite material while maintaining a regular pitch between the rails. This longitudinal junction consists of a double smooth Ω having a central sole covering the joint between the two panels. This longitudinal junction allows edge-to-edge assembly of panels with uniform and regular omega smoothing.
De façon plus précise, l'invention concerne une structure de fuselage d'aéronef comportant au moins un premier et un deuxième panneaux en matériau composite, placés côte-à-côte le long d'une jointure et assemblés l'un à l'autre par l'intermédiaire d'au moins une jonction longitudinale, caractérisée en ce que la jonction longitudinale consiste en une double lisse en Ω comportant :More specifically, the invention relates to an aircraft fuselage structure comprising at least a first and a second composite material panel, placed side-by-side along a joint and assembled to one another via at least one longitudinal junction, characterized in that the longitudinal junction consists of a double smooth Ω comprising:
- un premier et un second éléments en Ω, comprenant chacun une tête et deux âmes,a first and a second element in Ω, each comprising a head and two cores,
- une première semelle latérale située dans la continuité de la première âme du premier élément en Ω,a first lateral sole located in the continuity of the first core of the first element in Ω,
- une deuxième semelle latérale située dans la continuité de la dernière âme du second élément en Ω, et - une semelle centrale reliant la deuxième âme du premier élément ena second lateral sole located in the continuity of the last core of the second element in Ω, and a central sole connecting the second core of the first element in
Ω avec la première âme du second élément en Ω et recouvrant la jointure entre les deux panneaux.Ω with the first core of the second element in Ω and covering the joint between the two panels.
L'invention peut comporter une ou plusieurs des caractéristiques suivantes : - la semelle centrale a une longueur double de celle de la première ou de la deuxième semelle latérale.The invention may comprise one or more of the following features: the central sole has a length twice that of the first or the second lateral sole.
- la semelle centrale est réalisée d'une seule pièce avec les éléments en Ω et les première et deuxième semelles latérales.- The central sole is made in one piece with the elements in Ω and the first and second side insoles.
- la semelle centrale est fixée sur chaque panneau au moyen d'éléments de fixations placés de part et d'autre de la jointure.- The central sole is attached to each panel by means of fasteners placed on either side of the joint.
- la jonction longitudinale comporte une troisième lisse montée sur la semelle centrale.- The longitudinal junction comprises a third smooth mounted on the central sole.
- la troisième lisse est une lisse en T.the third rail is a T-rail.
- la jonction longitudinale comporte une bride interne ou externe montée sur la semelle centrale.- The longitudinal junction comprises an inner or outer flange mounted on the central sole.
- la jonction longitudinale comporte une surépaisseur intégrée dans la semelle centrale.- The longitudinal junction has an extra thickness integrated in the central sole.
L'invention concerne aussi un fuselage d'aéronef comportant au moins deux tronçons assemblés par une jonction circonférentielle, caractérisé en ce que chaque tronçon comporte une structure telle que décrite précédemment.The invention also relates to an aircraft fuselage comprising at least two sections assembled by a circumferential junction, characterized in that each section comprises a structure as described above.
L'invention concerne également un aéronef, caractérisé en ce qu'il comporte au moins une structure telle que décrite précédemment. Brève description des dessinsThe invention also relates to an aircraft, characterized in that it comprises at least one structure as described above. Brief description of the drawings
La figure 1 , déjà décrite, représente un exemple de structure de fuselage métallique à jonction longitudinale réalisée par une lisse en T.FIG. 1, already described, represents an example of longitudinal junction metal fuselage structure made by a T-bar.
La figure 2, déjà décrite, représente une vue en coupe d'une jonction longitudinale à lisse en T, sur une structure métallique.Figure 2, already described, shows a sectional view of a longitudinal junction T-smooth on a metal structure.
La figure 3, déjà décrite, représente une section de lissage en oméga d'une structure en matériau composite.Figure 3, already described, represents an omega smoothing section of a composite material structure.
La figure 4, déjà décrite, représente une vue en coupe d'une jonction longitudinale à lisse en T, sur une structure en matériau composite. La figure 5, déjà décrite, représente une vue en coupe d'une jonction longitudinale à lisse en U, sur une structure en matériau composite.Figure 4, already described, shows a sectional view of a longitudinal junction T-smooth on a composite material structure. Figure 5, already described, shows a sectional view of a U-shaped longitudinal junction on a structure of composite material.
La figure 6, déjà décrite, représente une vue en coupe d'une jonction longitudinale par recouvrement de panneaux.Figure 6, already described, shows a sectional view of a longitudinal junction panel covering.
La figure 7, déjà décrite, représente un exemple de tronçon d'aéronef dans lequel une nouvelle jonction longitudinale doit être intégrée.FIG. 7, already described, represents an example of an aircraft section in which a new longitudinal junction must be integrated.
La figure 8 représente une vue en coupe d'une jonction longitudinale selon l'invention.Figure 8 shows a sectional view of a longitudinal junction according to the invention.
Les figures 9, 10 et 1 1 représentent des exemples de jonctions longitudinales selon l'invention, avec insertion d'une lisse en T, d'une bride supplémentaire ou d'une surépaisseur de la lisse.Figures 9, 10 and 1 1 are examples of longitudinal junctions according to the invention, with insertion of a T-bar, an additional flange or an extra thickness of the bar.
Description détaillée de modes de réalisation de l'inventionDETAILED DESCRIPTION OF EMBODIMENTS OF THE INVENTION
La jonction longitudinale de l'invention comporte une double lisse en Ω avec semelle centrale, apte à être fixée sur une jointure entre deux panneaux de fuselage. Un exemple d'une telle jonction longitudinale est représenté sur la figure 8. Cette jonction 20 à double lisse en Ω comporte un premier élément en Ω, référencé 21 , et un second élément en Ω, référencé 22, reliés par une semelle centrale 23. Chacun de ces éléments en Ω comprend une tête, respectivement 21 a et 22a, et deux âmes, respectivement, 21 b, 21 c et 22b, 22c. La tête de chacun de ces éléments en Ω, 21 , 22, est apte à reprendre des éléments de la structure.The longitudinal junction of the invention comprises a double smooth Ω with central sole, adapted to be attached to a joint between two fuselage panels. An example of such a longitudinal junction is shown in FIG. 8. This double-smooth Ω junction comprises a first Ω element, referenced 21, and a second Ω element, referenced 22, connected by a central flange 23. Each of these elements in Ω comprises a head, respectively 21a and 22a, and two souls, respectively, 21b, 21c and 22b, 22c. The head of each of these elements in Ω, 21, 22, is able to take elements of the structure.
La jonction 20 comporte également une première semelle 24 située dans la continuité de la première âme 21 b du premier élément en Ω, 21 , ainsi qu'une deuxième semelle 25 située dans la continuité de la deuxième âme 22c du second élément en Ω, 22. Les éléments en Ω et les semelles latérales 24 et 25 sont identiques à l'élément en Ω et à la semelle d'une lisse en Ω classique telle que décrite précédemment.The junction 20 also comprises a first sole 24 located in the continuity of the first core 21b of the first element in Ω, 21, and a second sole 25 located in the continuity of the second core 22c of the second element in Ω, 22 . The elements in Ω and side flanges 24 and 25 are identical to the element in Ω and the sole of a smooth Ω conventional as described above.
La jonction 20 de l'invention comporte en outre une semelle centrale 23 reliant la deuxième âme 21 c du premier élément en Ω 21 avec la première âme 22b du second élément en Ω 22 et recouvrant la jointure 6 entre les deux panneaux 1 et 2. La semelle centrale 23 a une longueur double d'une semelle de lisse en Ω classique.The junction 20 of the invention further comprises a central sole 23 connecting the second core 21c of the first element in Ω 21 with the first core 22b of the second element in Ω 22 and covering the joint 6 between the two panels 1 and 2. The central sole 23 has a double length of a conventional Ω footplate.
La semelle centrale 23 et les semelles latérales 24 et 25 sont fixées sur les panneaux 1 et 2 par des éléments de fixation classiques. Plus précisément, la semelle 24 est fixée sur le panneau 1 et la semelle 25 est fixée sur le panneau 2. La semelle centrale 23 est fixée à la fois sur le panneau 1 et sur le panneau 2.The central sole 23 and the lateral soles 24 and 25 are fixed on the panels 1 and 2 by conventional fasteners. Specifically, the sole 24 is fixed on the panel 1 and the sole 25 is fixed on the panel 2. The central sole 23 is fixed on both the panel 1 and the panel 2.
On comprend, de la description qui précède, que la jonction longitudinale de l'invention a une dimension totale correspondant à celle de deux lisses en Ω placées bout à bout. Elle présente ainsi l'avantage d'offrir un pas régulier entre les lisses en Ω et la jonction longitudinale. En effet, la jonction longitudinale 20 ayant une longueur double de celle d'une lisse enIt is understood from the above description that the longitudinal junction of the invention has a total dimension corresponding to that of two smooth Ω placed end to end. It thus has the advantage of providing a regular pitch between the Ω smooth and the longitudinal junction. Indeed, the longitudinal junction 20 having a length twice that of a rail
Ω, la juxtaposition de lisses en Ω et de jonctions longitudinales 20 est régulière. Le lissage peut donc être uniforme malgré la présence de jonctions longitudinales.Ω, the juxtaposition of smooth Ω and longitudinal junctions 20 is regular. Smoothing can therefore be uniform despite the presence of longitudinal junctions.
Avec une telle technique, le lissage est relativement simple à effectuer car la jonction à double lisse en Ω peut être placée à la jointure des deux panneaux tout en conservant le lissage précédent puisque le pas entre deux lisses en Ω est conservé. Il est ainsi facile de modifier une découpe de panneaux en insérant une nouvelle jonction longitudinale puisqu'il suffit de remplacer deux lisses en Ω classiques par une jonction à double lisses.With such a technique, the smoothing is relatively simple to perform because the Ω double-smooth junction can be placed at the join of the two panels while maintaining the previous smoothing since the pitch between two smooth Ω is retained. It is thus easy to modify a panel cut by inserting a new longitudinal junction since it suffices to replace two smooth Ω conventional by a double smooth junction.
La jonction longitudinale 20 permet, en outre, que des éléments supplémentaires soient insérés sur la semelle centrale 23 afin d'offrir des fonctions supplémentaires, suivants les besoins, à ladite jonction.The longitudinal junction 20 further allows additional elements to be inserted on the center flange 23 to provide additional functions, as required, at said junction.
Sur la figure 9, on a représenté une vue en coupe d'une jonction longitudinale selon l'invention intégrant une lisse en T. Dans cet exemple, une lisse en T, référencée 30, a été montée sur la semelle centrale 23 de la jonction 20 pour permettre une éventuelle reprise d'autres éléments. Cette lisse en T peut être fixée sur la semelle centrale 23 par les mêmes éléments de fixation 7 que ceux fixant la semelle centrale sur les panneaux 1 et 2. On comprendra que, dans ce mode de réalisation, le pas de lissage reste identique à celui d'un lissage en Ω, car la lisse 30 en T est simplement installée au-dessus de la jonction longitudinale.FIG. 9 shows a sectional view of a longitudinal junction according to the invention incorporating a T-bar. In this example, a T-bar, referenced 30, has been mounted on the central sole 23 of the junction. 20 to allow possible recovery of other elements. This smooth T can be fixed on the central sole 23 by the same fasteners 7 as those fixing the central sole on the panels 1 and 2. On It will be understood that in this embodiment the smoothing pitch remains the same as that of Ω smoothing because the T-bar is simply installed above the longitudinal seam.
Ce mode de réalisation de la jonction longitudinale a été décrit pour une lisse en T. Il est bien entendu que d'autres types de lisses, par exemple une lisse en U, peuvent être installés à la place de la lisse en T.This embodiment of the longitudinal junction has been described for a T-bar. It is understood that other types of healds, for example a U-shaped bar, may be installed in place of the T-bar.
Sur la figure 10, on a représenté une vue en coupe d'une jonction longitudinale de l'invention intégrant une bride, appelé aussi strap. Dans cet exemple, un strap interne est positionné au-dessus de la semelle centrale 23 et fixé, via la semelle centrale 23, aux panneaux 1 et 2. Un strap est un élément de renfort apte à renforcer une structure. Un strap peut être interne, comme sur la figure 10, c'est-à-dire installé sur une face interne de la structure. Il peut aussi être externe, c'est-à-dire installé sur la face externe de la structure. Sur la figure 1 1 , on a représenté une vue en coupe d'une jonction longitudinale de l'invention intégrant une surépaisseur. Dans cet exemple, une surépaisseur est insérée dans la semelle centrale 23. Cette surépaisseur 50 peut être réalisée en matériau composite, au moyen d'un pli supplémentaire permettant de renforcer la jonction longitudinale 20 à proximité de la jointure 6. La semelle centrale est alors réalisée de façon à être plus épaisse, ce qui lui permet d'assurer des fonctions supplémentaires ou bien de renforcer la jonction entre les panneaux en cas de transfert de forces particulièrement important.In Figure 10, there is shown a sectional view of a longitudinal junction of the invention incorporating a flange, also called strap. In this example, an internal strap is positioned above the central sole 23 and fixed, via the central sole 23, to the panels 1 and 2. A strap is a reinforcing element capable of reinforcing a structure. A strap may be internal, as in Figure 10, that is to say installed on an inner face of the structure. It can also be external, that is to say installed on the external face of the structure. In Figure 1 1, there is shown a sectional view of a longitudinal junction of the invention incorporating an extra thickness. In this example, an extra thickness is inserted into the central sole 23. This extra thickness 50 can be made of composite material, by means of an additional fold to strengthen the longitudinal junction 20 near the joint 6. The central sole is then made to be thicker, which allows it to provide additional functions or to strengthen the junction between the panels in case of transfer of forces particularly important.
On remarquera que, dans tous les exemples des figures 8 à 10, on a représenté les éléments de fixation 7 de la jonction longitudinale répartis sur l'ensemble des semelles latérales et centrale. Par contre, dans l'exemple de la figure 1 1 , on a représenté uniquement les éléments de fixation des semelles centrale 23 et latérale 25. Dans cet exemple, la première semelle latérale 24 ne comporte pas d'élément de fixation ; elle est co-bondée avec le panneau 1.It will be noted that, in all the examples of FIGS. 8 to 10, there is shown the fastening elements 7 of the longitudinal junction distributed over the set of lateral and central flanges. On the other hand, in the example of FIG. 11, only the fastening elements of the central and lateral flanges 23 are shown. In this example, the first lateral flange 24 does not comprise a fixing element; it is co-packed with panel 1.
En effet, la jonction 20 telle qu'elle vient d'être décrite est réalisée d'une seule et même pièce, suivant les techniques conventionnelles de fabrication de lisses en Ω ; seule la forme du moule de fabrication change afin d'obtenir la forme en double Ω. Il est donc possible de co-bonder une des semelles latérales de la jonction à double lisse en oméga sur un des panneaux, ce qui permet de supprimer une rangée d'éléments de fixation et donc de diminuer la masse globale de l'aéronef. Ce mode de réalisation entraine, en outre, un gain de temps lors de l'assemblage des panneaux.Indeed, the junction 20 as just described is made of one and the same piece, according to conventional manufacturing techniques of smooth Ω; only the shape of the manufacturing mold changes in order to obtain the double Ω shape. It is therefore possible to co-bond one of the lateral flanges of the omega double-smooth junction on one of the panels, thereby eliminating a row of fasteners and therefore to reduce the overall mass of the aircraft. This embodiment also results in a saving of time during assembly of the panels.
La jonction longitudinale que vient d'être décrite permet de réaliser l'assemblage longitudinal en bout à bout de tous les panneaux du fuselage, quel que soit la section de fuselage considérée. En effet, mêmes les sections du fuselage fortement coniques ou celle comportant des jonctions orbitales peuvent être réalisées, avec la jonction longitudinale de l'invention, sans nécessiter de cales biaises. The longitudinal junction just described allows the longitudinal assembly end to end of all the panels of the fuselage, regardless of the fuselage section considered. Indeed, even sections of the fuselage strongly conical or that with orbital junctions can be made with the longitudinal junction of the invention, without the need for bias wedges.

Claims

REVENDICATIONS
1 - Structure de fuselage d'aéronef comportant au moins un premier et un deuxième panneaux (1 , 2) en matériaux composites, placés côte-à-côte le long d'une jointure (6) et assemblés l'un à l'autre par l'intermédiaire d'au moins une jonction longitudinale (20), caractérisée en ce que la jonction longitudinale consiste en une double lisse en Ω comportant :1 - Aircraft fuselage structure comprising at least first and second panels (1, 2) of composite materials, placed side by side along a joint (6) and assembled to one another via at least one longitudinal junction (20), characterized in that the longitudinal junction consists of a double smooth Ω comprising:
- un premier et un second éléments en Ω (21 , 22) comprenant chacun une tête (21 a, 22a) et deux âmes (21 b, 21 c, 22b, 22c),a first and a second Ω element (21, 22) each comprising a head (21a, 22a) and two cores (21b, 21c, 22b, 22c),
- une première semelle latérale (24) située dans la continuité de la première âme (21 b) du premier élément en Ω,a first lateral soleplate (24) located in the continuity of the first core (21b) of the first element in Ω,
- une deuxième semelle latérale (25) située dans la continuité de la dernière âme (22c) du second élément en Ω, et - une semelle centrale (23) ayant une longueur double de celle de la première (24) ou de la deuxième (25) semelle latérale et reliant la deuxième âme (21 c) du premier élément en Ω avec la première âme (22b) du second élément en Ω, ladite semelle centrale recouvrant la jointure entre les deux panneaux.a second lateral soleplate (25) located in the continuity of the last core (22c) of the second element in Ω, and - a central sole (23) having a length twice that of the first (24) or second ( 25) and connecting the second core (21c) of the first element in Ω with the first core (22b) of the second element in Ω, said central sole covering the joint between the two panels.
2 - Structure selon la revendication 1 , caractérisée en ce que la semelle centrale (23) est réalisée d'une seule pièce avec les éléments en Ω (21 , 22) et les première et deuxième semelles latérales (24, 25).2 - Structure according to claim 1, characterized in that the central sole (23) is formed integrally with the elements in Ω (21, 22) and the first and second lateral flanges (24, 25).
3 - Structure selon la revendication 1 ou 2, caractérisée en ce que la semelle centrale (23) est fixée sur chaque panneau au moyen d'éléments de fixations (7) placés de part et d'autre de la jointure.3 - Structure according to claim 1 or 2, characterized in that the central sole (23) is fixed on each panel by means of fasteners (7) placed on either side of the joint.
4 - Structure selon l'une quelconque des revendications 1 à 3, caractérisée en ce que la jonction longitudinale comporte une troisième lisse4 - Structure according to any one of claims 1 to 3, characterized in that the longitudinal junction comprises a third smooth
(30) montée sur la semelle centrale.(30) mounted on the central sole.
5 - Structure selon la revendication 4, caractérisée en ce que la troisième lisse (30) est une lisse en T. 6 - Structure selon l'une quelconque des revendications 1 à 4, caractérisée en ce que la jonction longitudinale comporte une bride (40) interne ou externe montée sur la semelle centrale.5 - Structure according to claim 4, characterized in that the third rail (30) is a T-rail. 6 - Structure according to any one of claims 1 to 4, characterized in that the longitudinal junction comprises an inner or outer flange (40) mounted on the central sole.
7 - Structure selon l'une quelconque des revendications 1 à 4, caractérisée en ce que la jonction longitudinale comporte une surépaisseur (50) intégrée dans la semelle centrale.7 - Structure according to any one of claims 1 to 4, characterized in that the longitudinal junction comprises an extra thickness (50) integrated into the central sole.
8 - Fuselage d'aéronef comportant au moins deux tronçons assemblés par une jonction circonférentielle, caractérisé en ce que chaque tronçon comporte une structure selon l'une quelconque des revendications 1 à 7.8 - aircraft fuselage comprising at least two sections assembled by a circumferential junction, characterized in that each section comprises a structure according to any one of claims 1 to 7.
9 - Aéronef, caractérisé en ce qu'il comporte au moins une structure selon l'une quelconque des revendications 1 à 7. 9 - Aircraft, characterized in that it comprises at least one structure according to any one of claims 1 to 7.
EP09805809A 2009-01-08 2009-12-31 Longitudinal joint for aircraft fuselage panels made of composite materials Withdrawn EP2373539A1 (en)

Applications Claiming Priority (2)

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FR0950087A FR2940785B1 (en) 2009-01-08 2009-01-08 LONGITUDINAL JUNCTION FOR AIRCRAFT FUSELAGE PANELS IN COMPOSITE MATERIALS
PCT/FR2009/052726 WO2010079282A1 (en) 2009-01-08 2009-12-31 Longitudinal joint for aircraft fuselage panels made of composite materials

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US20120025023A1 (en) 2012-02-02
FR2940785A1 (en) 2010-07-09
CN102317153A (en) 2012-01-11
WO2010079282A1 (en) 2010-07-15
FR2940785B1 (en) 2012-10-26

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