• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a method for producing a fuselage panel of an aircraft which comprises a skin and at least one reinforcement connected to said skin, said method comprising the steps of shaping a metal plate (30) of in order to obtain the skin and overmolding one or more reinforcement (s) on said metal plate (30). The invention also relates to a mold for the implementation of the method and an aircraft fuselage panel obtained from the method.
    公开号:FR3037558A1
    申请号:FR1555614
    申请日:2015-06-19
    公开日:2016-12-23
    发明作者:Mathias Farouz-Fouquet
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a method of manufacturing an overmolding fuselage panel and a fuselage panel obtained from said method. BACKGROUND OF THE INVENTION The present invention relates to a method for producing an overmolding fuselage panel and to a fuselage panel obtained from said method. A fuselage of an aircraft comprises a skin attached to a structure composed of a first series of transverse reinforcements (called frames) arranged in transverse planes and a second series of longitudinal reinforcements (called rails) arranged in longitudinal planes. For the rest of the description, a longitudinal direction is parallel to a longitudinal axis which extends from the front tip to the rear tip of the aircraft. A longitudinal plane is a plane containing the longitudinal axis and a transverse plane is a plane perpendicular to the longitudinal axis. The fuselage of an aircraft generally comprises several sections arranged end to end and connected in pairs. Each section extends between two transverse planes and generally comprises several panels assembled together. Some sections of the fuselage comprise openings, such as portholes, which are delimited by frame-shaped reinforcements which are connected to the skin. According to a first embodiment, each fuselage panel of an aircraft comprises a metal plate, in particular made of aluminum alloy, which provides the function of the skin and metal reinforcements, in particular of aluminum alloy. The metallic skin forms a faraday cage which protects the aircraft against lightning. The different reinforcements are connected by connecting elements directly to the skin or via intermediate pieces such as brackets, wedges. These connecting elements are inserts such as bolts, rivets, screws, etc. This first embodiment is not fully satisfactory since it requires a large number of manipulations and hours of work. tends to increase the costs of the fuselage panels. In addition, it leads to substantially increase the mass of the aircraft. According to a second embodiment, a fuselage panel of an aircraft is made of composite material. Some reinforcements are connected to the skin by co-cooking which makes it possible to remove the reported connecting elements such as rivets, bolts and screws. Although this second embodiment makes it possible to reduce the weight of the aircraft's fuselage panels, it is not entirely satisfactory because it is relatively complex to implement. According to another disadvantage, the composite material panel does not have a suitable electrical conductivity, it is necessary to bring on the skin a metal coating in the form for example of a mesh to provide protection against lightning. This addition leads to annihilating a part of the mass gain generated by the use of composite material and to increase the complexity of implementation and thus ultimately the costs of the fuselage panels. The present invention aims to overcome the disadvantages of the prior art. To this end, the subject of the invention is a method for producing a fuselage panel of an aircraft which comprises a skin and at least one reinforcement connected to said skin, said skin being obtained by conforming a metal plate according to the geometry of said skin. The method is characterized in that at least one reinforcement is obtained by overmolding. This solution makes it possible to obtain protection against lightning, the skin being metallic, and to eliminate the connection elements reported to connect the reinforcement (s) to the metal plate, which tends to reduce the on-board weight.
    [0002] The overmolding comprises the steps of: positioning the metal plate in a mold which comprises a cavity with a geometry identical to that of said metal plate and at least one cavity with a geometry identical to that of the reinforcement (s) to be overmolded , or the cavity (s) opening into the cavity, - injection of a material into the fingerprint (s) so as to obtain the reinforcement (s) molded (s), - demolding of the metal plate equipped reinforcement (s) overmolded (s). Advantageously, the metal plate comprises, for at least one overmolded reinforcement, at least one orifice which passes through said metal plate and into which the material is injected. In this way, said overmolded reinforcement comprises for each orifice a protuberance embedded in the metal plate.
    [0003] Preferably, the orifice has a section that increases between a first surface of the metal plate on which is positioned the overmolded reinforcement and a second surface of the metal plate opposite to the first surface. Advantageously, the material is injected into the fingerprint (s) while passing through the orifice (s). The invention also relates to a mold for carrying out the method which is characterized in that it comprises a first shell which has a concave shape which corresponds to a first surface of the skin of the fuselage panel, a second shell which has a convex shape which corresponds to a second surface of the skin of the fuselage panel, at least one of the first and second shells being movable so as to occupy a closed position in which the first and second shells delimit a cavity having a geometry identical to that of the skin, and a spaced apart position, the second shell comprising at least one impression with a geometry identical to that of a reinforcement overmold on said skin.
    [0004] Preferably, the first shell comprises at least one feed channel of material to be injected, said channel being positioned so as to open into an orifice provided in a metal plate which forms the skin and which is positioned in the cavity delimited by the first and second shells in the closed position. The invention also relates to a fuselage panel of an aircraft comprising at least one overmoulded reinforcement obtained from the method. Other features and advantages will become apparent from the following description of the invention, a description given by way of example only, with reference to the accompanying drawings, in which: FIG. 1A is a perspective view of a first shell of an injection mold 25 which illustrates a first embodiment of the invention, FIG. 1B is a perspective view of a second shell of an injection mold which illustrates a first embodiment of the invention, FIG. 2 is a section of an injection mold which illustrates another embodiment of the invention; FIG. 3 is a perspective view of a fuselage panel of an aircraft made from the method of the invention FIG. 4 is a section along the line IV-IV of FIG. 3, FIG. 5 is a cross section of a section of a fuselage of an aircraft obtained by assembling fuselage panels made from of the process of the invention, - Figure 6 e 5 is a section along the line VII-VII of FIG. 5; FIG. 8 is a perspective view which illustrates a detail of FIG. In Figure 3, there is shown in 10 a fuselage panel of an aircraft. As illustrated in Figure 5, several panels 10 may be assembled to form a section 12. The sections 12 are assembled end to end to form a fuselage of an aircraft. The fuselage comprises a skin 14 with an inner surface 141 facing inwardly of the fuselage and an outer surface 14E facing outwardly of the fuselage. This skin 14 is attached to a structure 16 which comprises longitudinal reinforcements 18 (called smooth) and transverse reinforcements 20 (called frames). According to one embodiment, the longitudinal reinforcements 18 are arranged in longitudinal planes and are pressed against the inner surface 141 of the skin 14. According to the configurations, a longitudinal reinforcement 18 has a cross-section (in a transverse plane) in the form of del, L, Omega. Other shapes are conceivable for the longitudinal reinforcement section 18. Each transverse reinforcement 20 forms a ring disposed in a transverse plane and has shapes permitting the passage of the longitudinal reinforcements 18. According to a first variant, the transverse reinforcements 20 comprise cutouts to allow the passage of the longitudinal reinforcements 18. According to another variant shown in Figures 3, 5 to 8, each transverse reinforcement 20 is spaced from the skin 14 and comprises tabs 22 to connect to the skin 14, said tabs 22 being spaced apart to allow the longitudinal reinforcements 18 to pass through. According to an embodiment illustrated in FIGS. 6 and 7, the transverse reinforcement has a Z-shaped section, the central portion of the Z-shaped disposed in a transverse plane being extended. by L-shaped tabs 22. Other shapes are conceivable for the section of the transverse reinforcements 20. As illustrated in FIGS. 5 and 8, the reinforcements, including transverse reinforcements 20, comprise protrusions 24 which provide the fastening function to secure at least one element to the structure of the aircraft. As illustrated in FIG. 3, the fuselage of an aircraft also comprises openings 26 closed by fixed elements such as in the case of a porthole or closed by movable elements as in the case of a door. Each opening 26 is delimited by at least one reinforcement 28 which extends around the periphery of the opening and which is secured to the skin 14. Depending on the function of the opening, the reinforcements 28 have different sections. As illustrated in FIG. 3, the fuselage panel 10 comprises a portion of the fuselage skin 14, longitudinal reinforcing segments 18, transverse reinforcing segments 20 and possibly other reinforcements such as for example to frame an opening 26 For the remainder of the description, the term reinforcement covers all types of reinforcements connected to the skin of the fuselage of an aircraft, such as, for example, a transverse reinforcement or a transverse reinforcement segment, a longitudinal reinforcement or a reinforcement segment. longitudinal, or any other reinforcement or reinforcing part. According to the invention, the skin 14 is metallic. According to one embodiment, the skin 14 is made of aluminum alloy. Thus, the skin 14 forms a protection against lightning. According to the invention, the method of producing a fuselage panel of an aircraft comprises the steps of: Conformation of a metal plate 30 according to the geometry of the skin 14 of the fuselage panel 10 to be obtained, and overmoulding of at least one reinforcement 18, 20, 28. The overmolding step makes it possible to connect the overmolded reinforcement (s) 18, 20, 28 without resorting to reported connection elements such as rivets, bolts, screws or others. The overmolding comprises the steps of: positioning the metal plate 30 in a mold 32 which comprises a cavity whose geometry is identical to that of said metal plate 30 and at least one cavity 34 whose geometry is identical to that of the reinforcement or reinforcement (s) 25 18, 20, 28 overmolding, or fingerprint (s) 34 opening into the cavity, injection of a material in the fingerprint (s) 34 so as to obtain at least one overmolded reinforcement 18, 20 , 28, demolding of the metal plate 30 equipped with or overmolded reinforcement (s) 18, 20, 28.
    [0005] According to one embodiment, all the reinforcements 18, 20, 28 made by overmolding are obtained during a same material injection step.
    [0006] Depending on the material injected, the opening of the mold 32 will be carried out only after a cooling phase of the injected material. Preferably, the injected material is a resin or a plastic material. The choice of the material will depend in particular on the desired mechanical characteristics for the over-molded reinforcement (s). As illustrated in Figures 1A, 1B and 2, the mold 32 is made of at least two parts, a first shell 36 (visible in Figure 1A) and a second shell 38 (visible in Figure 1B) movable one by relative to the other, so as to occupy a closed position in which they delimit a cavity sealed to the injected material and a spaced position in which they allow the insertion of the metal plate 30 into the cavity and the demolding of said plate metal 30 equipped with or overmolded reinforcement (s). The first and second shells 36 and 38 comprise surfaces 40, called joint planes, which are pressed against each other so as to obtain a cavity sealed to the injected material.
    [0007] These first and second shells 36 and 38 are mounted on an injection press which ensures the movement of at least one of the shells 36 and 38. The injection press is not further described because it is known to the skilled person. According to a first configuration illustrated in FIGS. 1A, 1B and 2, the first shell 36 comprises a concave shape which corresponds to the outer surface 14E of the skin and the second shell 38 comprises a convex shape which corresponds to the inner surface 141 of the skin and one or more impressions 34. According to a first embodiment illustrated in FIG. 2, the overmolded reinforcements have forms without undercut to allow demolding. In another embodiment, the overmolded reinforcements have undercut shapes. In this case, the mold 32 comprises at least one element movable relative to at least one shell, in particular the second shell 38, such as upstands, drawers, cores for example, to allow the demolding. Advantageously, the second shell 38 shown in FIG. 1B thus comprises three rising wedges 42a, 42b, 42c, movable between two positions: a molding position, in which the rising wedges 42b and 42c are represented, and an ejection position in which is represented the wedge 42a. The shims 42b and 42c are shown in the molding position, in which they define, with the second shell 38, a molding surface having an undercut shape, here the Z-shape for molding the reinforcements 20. During demolding, these wedges move away from the rest of the second shell 38, along with the molded part, along an oblique trajectory defined by their guide rods, which allows them to disengage the molded forms against undercut. The shim 42a is thus shown in its demolding position, linked to the remainder of the second shell 38 by its guide rods. Furthermore, centering elements may be provided to ensure accurate positioning of the first and second shells 36 and 38. Preferably, at least one of the shells 36 or 38 comprises at least one ejector to promote demolding of the panel.
    [0008] According to one embodiment, the ejectors comprise metal rods moving relative to the shells during demolding. These elements, which are known to those skilled in the art, are not described in more detail. The mold 32 also comprises at least one channel 44 for feeding the fingerprint (s) 34 and vents to expel gases during the injection of material.
    [0009] Preferably, each channel 44 comprises a nozzle 46 configured to control the flow of the material towards the fingerprint (s) 34. Advantageously, this nozzle 46 is controlled. According to another characteristic of the invention, the metal plate 30 comprises at least one form for improving the resistance of the connection between the overmolded reinforcement (s) and the metal plate 30. For this purpose, the plate metal 30 comprises, for each overmolded reinforcement, at least one orifice 48 which passes through said metal plate 30 and into which the material is injected. Thus, for each orifice 48, the overmolded reinforcement 18, 20, 28 comprises a protrusion 50 embedded in the metal plate 30. For each overmoulded reinforcement, the number of orifices 48 is determined as a function of the desired shear strength. Preferably, each orifice 48 has a section that increases between a first surface of the metal plate 30 (which corresponds to the inner surface 141 of the skin) on which is positioned the overmoulded reinforcement 18, 20, 28 and a second surface of the metal plate 30 opposite the first surface (which corresponds to the outer surface 14E of the skin). This configuration makes it possible to increase the tensile strength and overall the strength of the bond between the overmolded reinforcement (s) and the metal plate 30 which forms the skin 14.
    [0010] The orifices 48 have a section at the inner surface 141 less than the width of the over-molded reinforcement so that the orifices 48 are concealed under the overmolded reinforcements. According to a configuration, the supply channels 44 open at the level of the orifices 48. Thus, the material is injected into the fingerprint (s) 34 while passing through the orifice (s) 48, which ensures a better filling of the orifices 48 with the material and therefore a stronger connection by embedding between the protuberances 50 of the overmolded reinforcement and the metal plate 30. If the connection between the overmolded reinforcement (s) and the metal plate 30 is not sufficiently strong, Reported connecting members such as rivets, bolts, screws for example are provided for reinforcing said connection. These connection elements are much fewer than for the prior art because they serve only to strengthen if necessary the connection between the overmoulded reinforcements and the metal plate 30 which is obtained by the overmoulding technique and which is already reinforced thanks to the presence of the orifices 48. Preferably, the overmolded reinforcements comprise inserts 52 such as bushings, for example threaded or not, to allow the attachment of elements to the structure of the aircraft or to connect the panels together so as to form sections. Thus, according to one embodiment, the transverse reinforcement segments 20 comprise inserts 52 at each of their ends to make it possible to connect two successive transverse reinforcement segments using a fishplate 54, for example.
    [0011] If the panel 10 comprises at least one opening 26, the metal plate 30 comprises as many cutouts as openings 26, each cutout having a geometry in accordance with that of the corresponding opening. The shells 36 and 38 are in contact with each other in each opening 26 and an impression 34 is provided all around the opening 26.
    权利要求:
    Claims (8)
    [0001]
    REVENDICATIONS1. A method of producing a fuselage panel of an aircraft which comprises a skin (14) and at least one reinforcement (18, 20, 28) connected to said skin, said skin (14) being obtained by conforming a metal plate ( 30) according to the geometry of said skin (14), the method being characterized in that at least one reinforcement (18, 20, 28) is obtained by overmolding.
    [0002]
    2. Method according to claim 1, characterized in that the overmolding comprises the steps of: positioning the metal plate (30) in a mold (32) which comprises a cavity with a geometry identical to that of said metal plate (30) and at least one cavity (34) with a geometry identical to that of the reinforcement (s) (18, 20, 28) to be overmolded, the cavity (s) (34) opening into the cavity, injection molding a material in the fingerprint (s) (34) so as to obtain the overmoulded reinforcement (s) (18, 20, 28) for demolding the metal plate (30) equipped with the reinforcement (s) ) overmolded (18, 20, 28).
    [0003]
    3. Method according to claim 2, characterized in that the metal plate (30) comprises for at least one overmoulded reinforcement (18, 20, 28), at least one orifice (48) which passes through said metal plate (30) and in which is injected the material, so that said overmoulded reinforcement (18, 20, 28) comprises for each orifice (48) a protuberance (50) embedded in the metal plate (30).
    [0004]
    4. Method according to claim 3, characterized in that the orifice (48) has a section which increases between a first surface of the metal plate (30) on which is positioned the overmoulded reinforcement (18, 20, 28) and a second surface of the metal plate (30) opposite to the first surface.
    [0005]
    5. Method according to claim 3 or 4, characterized in that the material is injected into the fingerprint (s) (34) through the or openings (48).
    [0006]
    6. Mold for carrying out the method according to one of the preceding claims, characterized in that it comprises a first shell (36) which has a concave shape which corresponds to a first surface of the skin (14) of the panel a second shell (38) which has a convex shape which corresponds to a second surface of the skin (14) of the fuselage panel, at least one of the first and second shells (36, 38) being mobile so as to occupy a closed position in which the first and second shells (36, 38) delimit a cavity having a geometry identical to that of the skin (14), and a spaced apart position, the second shell (38) comprising at least one imprint (34) with a geometry identical to that of a reinforcement overmold on said skin 5 (14).
    [0007]
    7. Mold according to claim 6, characterized in that the first shell (36) comprises at least one channel (44) for supplying material to be injected, said channel (44) being positioned so as to open into an orifice (48). ) provided in a metal plate (30) which forms the skin (14) and which is positioned in the cavity defined by the first and second shells (36, 38) in the closed position.
    [0008]
    Aircraft fuselage panel comprising at least one overmoulded reinforcement obtained from the method according to one of claims 1 to 5.
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    同族专利:
    公开号 | 公开日
    US20160368585A1|2016-12-22|
    EP3106382A1|2016-12-21|
    FR3037558B1|2017-05-26|
    EP3106382B1|2017-11-08|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    法律状态:
    2016-06-27| PLFP| Fee payment|Year of fee payment: 2 |
    2016-12-23| PLSC| Search report ready|Effective date: 20161223 |
    2017-06-21| PLFP| Fee payment|Year of fee payment: 3 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1555614A|FR3037558B1|2015-06-19|2015-06-19|METHOD FOR MANUFACTURING AN OVERMOLDING FUSELAGE PANEL AND FUSELAGE PANEL THUS OBTAINED|FR1555614A| FR3037558B1|2015-06-19|2015-06-19|METHOD FOR MANUFACTURING AN OVERMOLDING FUSELAGE PANEL AND FUSELAGE PANEL THUS OBTAINED|
    EP16305718.5A| EP3106382B1|2015-06-19|2016-06-14|Method for manufacturing a fuselage panel by overmoulding and fuselage panel thus obtained|
    US15/186,643| US20160368585A1|2015-06-19|2016-06-20|Process for the manufacture of a fuselage panel by overmolding and fuselage panel so obtained|
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