• 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 object of the invention is a method of assembling at least one panel (30) and frames (34) for producing a part of a fuselage of an aircraft, said method comprising a step consisting of to conform on bearing surfaces (54) of a tool (50) said panel (30), characterized in that it consists in keeping each frame (34) pressed against at least one sliding bearing surface (74) ) disposed in a transverse plane, said sliding bearing surfaces (74) of the various frames and the bearing surfaces (54) being integral with the same tool and positioned relative to each other, and to set up elements of final fasteners for connecting the panel (30) and the frames (34). The invention also proposes a tool for implementing the assembly method.
    公开号:FR3016606A1
    申请号:FR1450447
    申请日:2014-01-21
    公开日:2015-07-24
    发明作者:Mattia Denis De
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] METHOD FOR MANUFACTURING A PART OF A FUSELAGE OF AN AIRCRAFT AND TOOLS FOR CARRYING OUT SAID METHOD The present invention relates to a method of manufacturing a part of a fuselage of an aircraft and a tool for carrying out said method. For the remainder of the present application, a longitudinal axis corresponds to the axis which extends from the front tip to the rear tip of an aircraft. A longitudinal direction is a direction parallel to the longitudinal axis. A longitudinal plane corresponds to a plane containing the longitudinal axis. A transverse plane corresponds to a plane perpendicular to the longitudinal axis. A radial direction is a direction perpendicular to the longitudinal axis. A face or an inner surface corresponds to a face or surface oriented towards the inside of the fuselage and a face or an external surface corresponds to a face or surface oriented towards the outside of the fuselage. In known manner, the fuselage of an aircraft comprises a structure mainly providing the force recovery function on which is reported an envelope, also called skin, giving the aircraft its aerodynamic properties. According to an embodiment illustrated in Figures 1A and 1B, the skin comprises a plurality of juxtaposed panels 10, reinforced by smooth 12 attached to the inner face of the panels 10. The smooth 12 are arranged in longitudinal planes. The structure comprises frames 14 which are arranged in transverse planes and spaced in the longitudinal direction. In longitudinal planes, the frames 14 have a section called Z with a core 16 disposed in a transverse plane and two wings 18, 18 'connected to the core 16 and perpendicular to the core 16. To form the fuselage, the reinforced panels 10 and the frames 14 are connected by clips 20. Each clip 20 comprises at least two wings 22.1 and 22.2 interconnected so as to form an angle, a first flange 22.1 pressed against the inner face of a panel 10 and a second wing 22.2 pressed against the web 16 of a frame 14.
    [0002] As illustrated in Figure 1A, a clip 20 'may have a more complex shape and include a bracket 24 connecting two wings. The first flange 22.1 of each clip 20 is secured to the panel 10 by means of fasteners 26 such as bolts or rivets. These fasteners 26 comprise countersunk heads housed in milling provided at the outer face of the panel 10 so as not to alter the aerodynamic properties of the fuselage. The second flange 22.2 of each clip 20 is secured to the core 16 by means of fastening elements 28 such as bolts or rivets. According to a first operating mode, each panel 10 is made and reinforced by the flat rails 12. This solution makes it possible to simplify the manufacturing process of the reinforced panels. Thus, in the case of panels 10 and slats 12 made of composite material, it is possible to automate the manufacturing process of said reinforced panels, in particular by using automatic draping machines. Following, the flat panel 10 and reinforced by the smooth 12 is shaped on a first tool so as to give it its curved shape. This curved shape varies depending on the position of the panel 10 in the fuselage. At the end of this shaping step, the outer face of the panel 10 extends along a reference surface. Depending on the position of the panel in the fuselage, this reference surface is developable and approximately semi-cylindrical or it is not developable for the panels near the front tip or the rear tip of the aircraft. This first tool comprises a frame that supports at least one bearing surface against which is pressed the inner face of the panel 10. The frame and the bearing surfaces are designed so as to be rigid and retain their geometries during the deformation of the panel.
    [0003] The frames 14 are arranged one by one on a second tool. This second tool makes it possible to position the frames 14 according to their reference positions in the fuselage. This second tool comprises a frame that supports portions of rings called couples, one for each frame. Each pair comprises a bearing surface against which is pressed the frame core to position it in a transverse plane and three pins to position and immobilize the frame in said transverse plane. Once the frames are positioned, the panel 10 reinforced and shaped according to the reference surface is positioned relative to the frames 14.
    [0004] At the end of the positioning of the panel 10 relative to the frames 14, the clips 20, the frames and the panel are assembled. For each clip 20, a first flange 22.1 of the clip abuts against the inner face and a second flange 22.2 of the clip abuts against the core 16 of the frame. The clips are positioned to be distributed along each frame. To facilitate this implementation, the second tool comprises for each clip a stop which allows to position it along the frame. Prior to the installation of the fastening elements 26, 28, the clips are held in position by means of pins. To control the contact force between the assembled parts, a clamping force is applied to the parts to be assembled every ten points of attachment. The clearance between the parts to be assembled must be of the order of 0.3 mm for a force of 20 daN. If this clearance is greater than 0.3 mm, shims are arranged between the pieces. This method of measuring under load the clearance between said parts makes it possible to control the internal stresses induced during assembly. Finally, the fixing elements 26, 28 are laid to ensure the connection between the clip 20 and the panel 10, and between the clip 20 and the frame 14. This first procedure is difficult to automate. According to a first constraint, it is necessary to provide a first automatic laying means disposed inside the fuselage to install the fastening elements 28 ensuring the connections between the clips and the frames and a second means of automatic installation outside. fuselage to install the fasteners 26 between the panel and the clips that must be placed from outside the fuselage due to the presence of countersinking. According to another constraint, the second tool must allow the maintenance of the elements to be assembled, namely the panel, the frames and the clips according to their reference positions. Given these constraints, this assembly is performed by operators equipped with drilling unit.
    [0005] According to a second operating mode described in document EP-2,404,824, the frames are arranged one by one on a tool according to their reference positions in the fuselage. For this purpose, the tool comprises a frame which supports portions of rings called couples, one for each frame. Each pair comprises a bearing surface against which is pressed the frame core to position it in a transverse plane and three pins to position the frame in said transverse plane. Once the frames are positioned, the flat panel 10 and reinforced by the rails is deformed on the frames that replace the first tool of the first operating mode. Following, the panel and frames are assembled through connecting elements. According to this document, the frames have a particular section, hollow and each include a face pressed against the panel so that it is possible to delete the clips. Although in theory, this second procedure can automate the assembly by using an automatic means of fixing fasteners from outside the fuselage, it is not satisfactory for the following reasons. According to a first drawback, this operating mode does not make it possible to control the internal stresses induced during the assembly of the panel and the frames, especially if the panel has a non-developable reference surface.
    [0006] At the points of contact between the frame and the panel, it is not possible to determine the contact force between the frame and the panel and in this way to control the stresses induced during assembly. It is the same for areas where the clearance is less than 0.3 mm under load. If the clearance between the frame and the panel under load is greater than 0.3 mm, it is necessary to set shims. It is then necessary to remove the panel to put in place the holds then to reposition it after the setting up of the holds. However, in the case of a panel with a non-developable reference surface, it is very difficult to reposition it in the same way. According to another disadvantage, when the contact surfaces of the parts to be assembled are coated with a sealant, the latter prevents the parts from sliding relative to each other to refine their relative position. Finally, according to another disadvantage, the frames must be rigid so as not to deform when conforming the panel. Therefore, frames with a Z-section can not be used because this section does not provide sufficient torsional and flexural inertia. One could to stiffen them increase the number of pins used to position each frame on its couple. However, in this case, as for frames with a hollow section, it is not possible to control the internal stresses induced during assembly. Also, the present invention aims to overcome the disadvantages of the prior art.
    [0007] For this purpose, the subject of the invention is a method of assembling at least one panel and frames for producing part of a fuselage of an aircraft, said method comprising a step consisting in support surfaces of a tooling said panel, the method being characterized in that it consists in keeping each frame pressed against at least one sliding bearing surface disposed in a transverse plane, said sliding bearing surfaces of the various frames and the support surfaces being integral with the same tool and positioned relative to each other, and to set up definitive fasteners for connecting the panel and the frames. This method makes it possible to automate the assembly as the second operating mode of the prior art by using a means for automatically attaching the fastening elements arranged outside the fuselage. According to another advantage, unlike the second operating mode of the prior art, the presence of the bearing surfaces makes it possible not to use the frames as tools so that it is possible to use frames with Z-sections. According to another advantage, the fact that the frames are in abutment against a sliding bearing surface makes it possible to control the internal stresses induced during assembly. Advantageously, the method consists in positioning each frame with respect to its sliding bearing surface after forming said panel. Unlike the second embodiment, it is simpler to position the frames one after the other with respect to the panel than to position the panel relative to all the frames simultaneously. Preferably, each frame is positioned by immobilizing it along its line of curvature (Lc) while allowing translational movement in a radial direction. According to this procedure, each frame is positioned relative to a positioning means arranged equidistant from the ends of said frame and its ends are unwound so as to come into contact with the panel. According to another characteristic, the method consists in using at least one clamping to keep each frame pressed against the sliding bearing surface, said clamping comprising a counter-support in contact with the frame which allows a translational movement of said frame in the direction radial. According to another characteristic, the method consists in using straps to keep the panel pressed against the bearing surfaces.
    [0008] The invention also relates to a tool for implementing the assembly method. This tooling is characterized in that it comprises bearing surfaces with at least one radius of curvature in a transverse plane for forming the panel, and for each frame, at least one sliding bearing surface disposed in a transverse plane, said sliding bearing surfaces of the various frames and the bearing surfaces being integral with said tool and positioned relative to each other. Advantageously, for each frame, the tooling comprises a pair with a rigid structure which extends in a transverse plane with a bearing surface at the periphery and on one of its faces at least one sliding bearing surface parallel to a plane transverse. Preferably, each pair comprises at least one positioning means for immobilizing a frame along its line of curvature while allowing translational movement in a radial direction. According to one embodiment, each pair comprises a single positioning means arranged equidistant from the ends of each frame. According to a feature of the invention, each pair comprises at least one clamping to keep each frame against the sliding bearing surface, said clamping comprising a counter-support which allows a translational movement of said frame in the radial direction. According to one embodiment, the counter-support is in the form of a roller pivotally mounted on a pivot axis disposed in a transverse plane and perpendicular to the radial direction. According to a feature of the invention, the tooling includes straps for holding the board against the bearing surfaces. According to one embodiment, the tooling comprises a frame with an upper cross member and a lower cross member, each bearing surface comprising a strip of material extending from the top cross member to the lower cross member and the straps being arranged in a manner with respect to the bearing surfaces. Other features and advantages will emerge from the following description of the invention, a description given by way of example only, with reference to the appended drawings, in which: FIG. 1A is a perspective view of part of a fuselage of an aircraft, FIG. 1B is a section along plane P of FIG. 1A, FIG. 2A is a side view of a frame equipped with clips, FIG. 2B is a section along line BB of FIG. 2A, FIG. 3 is a perspective view of a tool that illustrates the invention prior to the installation of a panel, FIG. 4 is a perspective view of the tool visible in FIG. in place of a panel and frames, FIG. 5 is a section along a longitudinal plane of part of the tooling shown in FIG. 3, FIG. 6 is a front view of a positioning means of FIG. a frame which illustrates an embodiment of the invention. In FIGS. 2A, 2B, 3 to 5, there is shown at 30 a panel of a part of a fuselage of an aircraft. For the description, once assembled, the panel 30 extends over one half of a section of the fuselage and has a semi-cylindrical shape with a radius of curvature in a transverse plane. Of course, the invention is not limited to this form. Thus, the panel 30 may have a so-called non-developable shape with a double radius of curvature. This panel 30 includes an inner face 301 and an outer face 30E and is reinforced by smooth 32 fixed on the inner face 301. It is delimited by a high edge 30H, a low edge 30B and side edges 31, 31 '. As an indication, each side edge is arranged in a transverse plane. The high edge 30H corresponds to a portion of an upper generatrix of the fuselage. The bottom edge 30B corresponds to a portion of a lower generatrix of the fuselage. According to one embodiment, the panel 30 and the rails 32 are made of composite material.
    [0009] Other materials could be considered. To obtain a portion of the fuselage, the reinforced panel 30 is fixed on frames 34 arranged in parallel planes (corresponding to transverse planes PT) and spaced in a direction (corresponding to the longitudinal direction DL). According to one embodiment, illustrated in Figures 2A and 2B, each frame 34 comprises a profile which extends along a line of curvature Le corresponding approximately to a semicircle. This profile has a section Z. Thus, each frame comprises a core 36 with at each end of the wings 38, 38 'substantially perpendicular to the core 36. According to one variant, the frames 34 are metallic. However, they can be made of composite material.
    [0010] The frames 34 and the panel 30 are connected by clips 40. According to an embodiment illustrated in FIG. 2B, each clip 40 comprises at least two wings 42.1 and 42.2 connected so as to form an angle, a first wing 42.1, called soleplate, pressed against the inner face 301 of a panel 30 and a second flange 42.2 pressed against the core 36 of a frame 34. The sole 42.1 of each clip 40 is secured to the panel 30 by means of connecting elements 44 such only bolts or rivets (some are visible in Figure 4). These connecting elements 44 comprise milled heads housed in milling provided at the outer face 30E of the panel 30 to not alter its aerodynamic properties. The second flange 42.2 of each clip 40 is secured to the core 36 by means of connecting elements 46 such as bolts or rivets.
    [0011] According to one variant, these clips are metallic. However, other materials could be considered. The panel 30, the frames 34 and the clips 40 are not further described because they may be identical to those of the first procedure of the prior art. As illustrated in Figure 3, prior to assembly, the panel 30 is made and reinforced by the smooth 32 flat. This solution makes it possible to simplify the process for producing the reinforced panels. Thus, in the case of panels 30 and smooth 32 composite material, can automate the manufacturing process of said panels including using automatic draping machines. As illustrated in Figures 2A and 2B, the frames 34 have a profile which follows a reference line of curvature Lc in a transverse plane, said line of curvature Lc being a function of the location of the frame in the fuselage. Prior to assembly with the panel or panels, the clips 40 are fixed on the frames 34 with the final fixing elements 46. According to one embodiment, each frame is bent along its reference line of curvature Lc and the clips 40 are fixed by means of automatic installation of the fixing elements 46. The invention is not limited to the embodiments described above. concerning the panel 30 and the frames. Thus, the panel 30 can be reinforced with other elements than smooth. In addition, according to another variant, the frames 34 are connected directly with the panel 30, without the intermediary of clips. In this case, the frames are called integral.
    [0012] For the remainder of the description, the term frame, an integral frame directly connected to the panel or the assembly formed by a frame equipped with clips.
    [0013] Whatever the variant, a frame 34 comprises flanges 42.1 which are pressed against the inner face 301 of the panel 30 and which are connected to said panel 30 by fixing elements 44. Advantageously, prior to assembly with the panel or panels , the flanges 42.1 comprise at least one pilot hole 48 which will be used for the establishment of a pin to immobilize each flange 42.1 relative to the panel 30 during the installation of the final fasteners 44. Preferably, each sole 42.1 comprises at least two pilot holes 48 (visible in FIG. 2B). Once the panel 30 and the frames 34 are assembled, the outer surface 30E of the panel 30 must be positioned according to a reference surface with close tolerances. Similarly, each frame must be positioned according to a reference position with close dimensional tolerances. To assemble the panel 30 and the integral frames 34, a tooling 50 is used which comprises a frame 52 which supports a plurality of bearing surfaces 54 and pairs 56, one for each integral frame 34. During assembly, the internal face 301 of the panel is pressed against the bearing surfaces 54 which are connected to the frame 52 in a sufficiently rigid manner to allow the deformation of the panel of a flat geometry to a curved geometry. For this purpose, the bearing surfaces 54 have such geometries that when the panel 30 is in abutment, it has a curved geometry consistent with that of the corresponding fuselage part. Therefore, the bearing surfaces 54 have at least one radius of curvature in a transverse plane. Thus, when the inner surface 301 of the panel 30 is pressed against said bearing surfaces 54, certain points of the panel 30 are positioned within a tolerance range with respect to their reference positions.
    [0014] According to one embodiment, each bearing surface 54 comprises a strip of material 58 with lateral edges 60, 60 'arranged in transverse planes. To give an order of magnitude, the lateral edges 60, 60 'are separated by a distance of the order of 3 to 15 cm. According to one embodiment, the frame 52 comprises a frame with uprights 62, 62 'connected by a high cross 64H and a lower cross 64B. For a given panel 30, the high cross 64H extends in a profile identical to that of the top edge 30H of the panel and the lower cross member 64B extends in a profile identical to that of the bottom edge 30B of the panel.
    [0015] Each strip of material 58 extends from the top rail 64H to the bottom rail 64B and has a curvature which is a function of the curvature of the panel 30 in the transverse plane occupied by the material web 58. The tooling 50 comprises also means for holding the panel 30 against the bearing surfaces 54. According to one embodiment, these holding means comprise straps 66 which are stretched between the upper cross member 64H and the lower cross member 64B of the frame 52. The tooling comprises as many straps 66 as support surfaces 54. Preferably, the straps 66 are arranged opposite the bearing surfaces 54 (in the same transverse planes), so that the panel 30 is positioned between a strap and a support surface. Advantageously, the tooling 50 comprises means for positioning the panel 30 relative to the tooling 50. Preferably, the positioning means comprise at least one pin 67 and at least one point support 67 '. According to one embodiment, the pin 67 is integral with the tool and comprises a cylindrical pin with an axis perpendicular to said bearing surface. In addition, the panel 30 comprises an orifice 68 with a diameter substantially equal to the diameter of the pin. Thus, the spindle 67 makes it possible to immobilize in translation the panel 30 with respect to the tooling 50. The spindle leaves only one degree of freedom, namely a rotation around the spindle. This last degree of freedom is removed by the one-off support 67 '.
    [0016] According to one embodiment, the point support 67 'is secured to the tool and comprises a cylindrical pin with an axis perpendicular to said bearing surface. In addition, the panel 30 comprises an oblong hole 70 in which the stud is housed, the width of the oblong hole being substantially equal to the diameter of the stud. Other variants are conceivable for the positioning means.
    [0017] Preferably, the panel comprises pilot holes 72 (visible in FIG. 3) positioned so as to coincide with the pilot holes 48 of the flanges of the frames. These pilot holes 72 have a diameter greater than that of the pilot holes 48 of the soles. According to one characteristic of the invention, each pair 56 comprises at least one sliding bearing surface 74.
    [0018] According to one embodiment, each pair 56 comprises a single sliding bearing surface 74 which extends over approximately an arc of 180 °. In a variant, each pair 56 comprises several disjointed and coplanar sliding bearing surfaces.
    [0019] For each pair, the sliding bearing surface (s) extends (ent) in a transverse plane. The bearing surfaces 54 and the sliding bearing surfaces 74 are integral with the same tool and positioned relative to each other so that once mounted, the frames are correctly positioned relative to the panel 30. According to a embodiment, each pair 56 comprises at least one sliding bearing surface 74 and at least one bearing surface 54. Each pair 56 comprises a rigid structure connected to the frame which extends in a transverse plane with peripherally a surface 54 and on one of its faces at least one sliding bearing surface 74 parallel to a transverse plane. During assembly, the frame 34 is pressed against the sliding bearing surface 74. In the case of a frame with a Z-shaped section, the core 36 of the frame is pressed against the sliding bearing surface 74. According to one embodiment, the sliding bearing surface 74 comprises a coating or is made of a material promoting sliding, such as polyacetal. The tooling 50 also comprises for each pair 56 at least one clamping 76 for keeping the frame pressed against the sliding bearing surface 74. Advantageously, each pair comprises several clamps 76 distributed along the line of curvature Lc.
    [0020] According to one embodiment, each clamping 76 comprises a counter-support 78 movable between an active position in which the abutment 78 is in contact with the frame 34 and keeps it pressed against the sliding bearing wall 74 and an unobstructed position in which the counter-support 78 is removed from the frame so as to allow its assembly and disassembly. Preferably, the clamping 76 comprises a yoke 80 fixed relative to the tooling 50 and a lever 82 which pivots relative to the yoke 80 and which supports the abutment 78. Each clamping 76 comprises a locking and unlocking system. to maintain the support 78 in the active position. Preferably, the counter-support 78 allows a sliding of the frame in a radial direction. According to one embodiment, the counter-support comprises a coating or is made of a material promoting sliding, such as polyacetal.
    [0021] According to another embodiment illustrated in FIG. 5, the abutment support 78 is in the form of a roller pivotally mounted on a pivot axis 84 arranged in a transverse plane and perpendicular to a radial direction 86. the frame being able to translate in the radial direction 86 while still being held pressed against the sliding bearing surface 74. A radial direction at a given point corresponds to a direction perpendicular to the tangent to the line of curvature at the given point. Advantageously, the tooling 50 comprises for each pair 56 at least one positioning means 88 of the frame 36. Preferably, each positioning means 88 immobilizes the frame along the line of curvature Lc but allows a translation movement in the radial direction 86 to allow a radial adjustment of the frame position. According to an embodiment illustrated in FIG. 6, each positioning means 88 comprises a pin 90 integral with the tooling and the frame 36 comprises an oblong orifice 92 in which the pin 90 is housed. The oblong orifice 92 has a width substantially equal to the diameter of the pin and a length greater than the diameter of the pin so as to allow the frame to move radially. Preferably, each pair comprises a single positioning means 88 arranged equidistant from the ends of the frame. The assembly method is now described: In a first step, the panel 30 is positioned on the tooling 50. For this purpose, the panel 30 is bent so as to be pressed against the bearing surfaces 54. The panel 30 is positioned relative to the tool 30 by the pin 67 and point support 67 '. The straps 66 are positioned to hold the panel 30 against the bearing surfaces 54. This clamping of the panel gives it a high rigidity when said panel is subjected to a force perpendicular to its surface. Following, the frames are set up one after the other. Each of them is first positioned by the positioning means 88 and then pressed against the sliding bearing surface 74 and maintained plated by the clamps 76. Following, at each sole, the frame 36 is connected to the panel 30 by pins that pass through the pilot holes 48 and 72. To control the internal stresses induced during assembly, the pins exert a clamping force on the skin and the sole of the order of 20daN. According to the invention, the clamping forces applied to the frame do not cause twisting in that said frame is held pressed against the sliding bearing surfaces and can slide radially. The clearance between the soles and the panel 30 is measured to determine if rigging is needed. If the measured clearance is less than a given value of the order of 0.3 mm, it is considered that the stresses produced by the final fixing elements to make up the game will be acceptable. In the opposite case, if the clearance is greater than the given value, a wedging is carried out between the parts to be assembled to reduce the clearance. By following, the drilling and milling of all the holes intended for the implementation are carried out. place definitive fasteners.
    [0022] Once these machining operations are carried out, the frames are dismantled to clean the surfaces of the soles and to coat them with an interposing mastic. Each frame is then reassembled starting from the positioning means 88 located equidistant from the ends of said frame, then unwinding each of said ends. The frames are held in position by the clamps 76.
    [0023] Once the frames are flanged, the final fasteners are put in place. As for drilling-milling, the establishment of the final fasteners can be achieved by an automatic machine acting from the outer face of the panel. After the establishment of the final fasteners, the straps 66 are removed and the clamps 76 are positioned in the disengaged position so as to remove the entire panel / frames of the tool 50. The method of the invention allows to assemble at least one panel and frames in an automated manner, realizing during a first phase the fixing of the clips on the frames, then during a second phase the fixation of the panel (s) on the frames equipped with clips .
    [0024] In addition, this method makes it possible to control the internal stresses induced during assembly. According to another advantage, it is easier to position the frames one after the other with respect to the panel than to position the panel relative to all frames.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. A method of assembling at least one panel (30) and frames (34) for forming part of a fuselage of an aircraft, said method comprising a step of conforming on bearing surfaces ( 54) of a tool (50) said panel (30), said bearing surfaces (54) having at least one radius of curvature in a transverse plane, the frames in a reference line of curvature (Lc), characterized in it consists in keeping each frame (34) pressed against at least one sliding bearing surface (74) arranged in a transverse plane, said sliding bearing surfaces (74) of the various frames and the bearing surfaces ( 54) being integral with the same tool and positioned relative to each other, and to set up definitive fasteners (44) for connecting the panel (30) and the frames (34).
    [0002]
    2. A method of assembly according to claim 1, characterized in that it consists in positioning each frame (34) relative to its sliding bearing surface after forming said panel (30).
    [0003]
    3. A method of assembly according to claim 2, characterized in that it consists in positioning each frame (34) by immobilizing it along its line of curvature (Lc) while allowing a translation movement in a radial direction (86). ).
    [0004]
    4. A method of assembly according to claim 3, characterized in that each frame is positioned relative to a positioning means (88) arranged equidistant from the ends of said frame and its ends are unwound so as to come into contact with the panel .
    [0005]
    5. A method of assembly according to claim 3 or 4, characterized in that it consists in using at least one clamping (76) to maintain plated each frame (34) against the sliding bearing surface (74), said clamping (76) comprising a counter-support (78) in contact with the frame which allows a translational movement of said frame in the radial direction (86).
    [0006]
    6. A method of assembly according to one of the preceding claims, characterized in that it consists of using straps (66) to keep the plate (30) pressed against the bearing surfaces (54).
    [0007]
    7. Tooling for carrying out the assembly method according to one of the preceding claims, said method consisting in assembling at least one panel (30) and frames (34) for the realization of a part of a fuselage. of an aircraft, characterized in that the tooling comprises bearing surfaces (54) with at least one radius of curvature in a transverse plane to form the panel (30), and for each frame at least one surface of sliding support (74) arranged in a transverse plane, said sliding bearing surfaces (74) of the various frames and the bearing surfaces (54) being integral with said tool and positioned relative to each other.
    [0008]
    8. Tooling according to claim 7, characterized in that, for each frame (34), the tool comprises a pair with a rigid structure which extends in a transverse plane with a bearing surface (54) at its periphery and on one of its faces at least one sliding bearing surface (74) parallel to a transverse plane.
    [0009]
    9. Tooling according to claim 7 or 8, characterized in that each pair comprises at least one positioning means (88) for immobilizing a frame (34) along its line of curvature (Lc) while allowing a translational movement. in a radial direction (86).
    [0010]
    10. Tooling according to claim 9, characterized in that each pair comprises a single positioning means (88) arranged equidistant from the ends of each frame.
    [0011]
    11. Tooling according to claim 9 or 10, characterized in that each pair comprises at least one clamping (76) to keep each frame (34) pressed against the sliding bearing surface (74), said clamping (76) comprising a against-support (78) which allows a translational movement of said frame in the radial direction (86).
    [0012]
    12. Tool according to claim 11, characterized in that the abutment (78) is in the form of a roller pivotally mounted on a pivot axis (84) disposed in a transverse plane and perpendicular to the radial direction ( 86).
    [0013]
    13. Tooling according to one of claims 7 to 12, characterized in that it comprises straps (66) to keep the plate (30) pressed against the bearing surfaces (54).
    [0014]
    14. Tooling according to claim 13, characterized in that it comprises a frame (52) with a high cross member (64H) and a lower cross member (64B), in that each bearing surface (54) comprises a band of material (58) extending from the top rail (64H) to the bottom rail (64B), and in that the straps (66) are disposed opposite the bearing surfaces (54).
    [0015]
    15. Tooling according to one of claims 7 to 14, characterized in that it comprises means for positioning the panel (30) relative to the tooling.
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    FR3000470A1|2014-07-04|SELF-ADHESIVE AIRCRAFT SKIN FOR AIRCRAFT FUSELAGE COMPRISING CLOSED SECTION LOWERS AND METHOD OF MANUFACTURING THE SAME
    EP0561657A1|1993-09-22|Fixing device for facing plates
    EP0373021A1|1990-06-13|Procedure of the fabrication of a light-construction device to support longish elements, means provided for the realisation of this procedure and device obtained thereby
    WO2014096741A1|2014-06-26|Stiffener for an aircraft fuselage, method for manufacturing same, and aircraft fuselage equipped with such a stiffener
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    同族专利:
    公开号 | 公开日
    CN104787299A|2015-07-22|
    US20150202824A1|2015-07-23|
    FR3016606B1|2016-02-19|
    CN104787299B|2018-09-04|
    US10029414B2|2018-07-24|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP2530021A2|2011-05-31|2012-12-05|Airbus Operations GmbH|Assembling jig for at least one section of an aircraft fuselage|
    CN201008935Y|2006-12-05|2008-01-23|成都飞机工业（集团）有限责任公司|Wallboard rivet-bonding flexible assembly frame|
    EP2404824B1|2010-07-08|2015-09-09|Airbus Opérations SAS|Aircraft structure and Method for producing such a structure|
    FR2976916B1|2011-06-27|2013-07-26|Airbus Operations Sas|DEVICE AND METHOD FOR ASSEMBLING TWO TRUNCONS OF AIRCRAFT FUSELAGE|
    CN103447792B|2013-08-08|2016-02-10|上海飞机制造有限公司|Large complicated shape is faced the wall and meditated plate Flexible Measurement & Control fixture system and investigating method|US10493705B2|2015-11-13|2019-12-03|GM Global Technology Operations LLC|Additive manufacturing of a body component on a tube frame|
    JP6513584B2|2016-02-02|2019-05-15|三菱重工業株式会社|Holding jig fixing device|
    EP3511252B1|2018-01-11|2020-12-16|Airbus Operations GmbH|Production system for the automated assembly of vehicle components and method for controlling a production system|
    GB2585474B|2019-05-23|2022-02-16|Bae Systems Plc|A method and apparatus for producing at least part of a structural frame of a vehicle|
    EP3741685A1|2019-05-23|2020-11-25|BAE SYSTEMS plc|A method and apparatus for producing at least part of a structural frame of a vehicle|
    CN112977849A|2020-10-06|2021-06-18|许昌学院|Fastening type horn mechanism and application thereof in unmanned aerial vehicle|
    法律状态:
    2015-01-22| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-21| PLFP| Fee payment|Year of fee payment: 3 |
    2017-01-20| PLFP| Fee payment|Year of fee payment: 4 |
    2018-01-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-01-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-01-21| PLFP| Fee payment|Year of fee payment: 8 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1450447A|FR3016606B1|2014-01-21|2014-01-21|METHOD FOR MANUFACTURING A PART OF A FUSELAGE OF AN AIRCRAFT AND TOOLS FOR CARRYING OUT SAID METHOD|FR1450447A| FR3016606B1|2014-01-21|2014-01-21|METHOD FOR MANUFACTURING A PART OF A FUSELAGE OF AN AIRCRAFT AND TOOLS FOR CARRYING OUT SAID METHOD|
    US14/600,442| US10029414B2|2014-01-21|2015-01-20|Method for producing part of an aircraft fuselage and tool for implementing said method|
    CN201510029058.3A| CN104787299B|2014-01-21|2015-01-21|The method of a part for manufacturing airframe and the tool for implementing this method|
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