METHOD FOR ASSEMBLING AN AIRCRAFT PYLON AND AIRCRAFT PYLON OBTAINED BY THIS METHOD

Abstract

A method for assembling an aircraft pylon including a primary structure and at least one internal system positioned at least partially within the primary structure, wherein the assembly method includes a first step of assembling a part of the primary structure so that the interior of the primary structure remains accessible, a step of mounting an internal systems module including at least one support and at least one internal system connected to the support, a second step of assembling the internal systems module and the partially assembled primary structure, a third step of assembling any element of the primary structure not assembled in the first assembly step, and an aircraft pylon assembled by such a method.

Claims

1. A method for assembling an aircraft pylon comprising: a primary structure comprising upper and lower spars and first and second lateral panels, a secondary structure capping the primary structure, at least one internal system positioned at least partially inside the primary structure, and at least one external system positioned between the primary structure and the secondary structure, wherein the assembly method comprises: a first step of assembling a subassembly comprising at least one of the upper and lower spars and at least one of the first and second lateral panels, a step of mounting an internal systems module comprising the at least one internal system and at least one support to which the at least one internal system is connected, a second step of assembling the internal systems module and the subassembly assembled in the first assembly step, and during the second assembly step, each of said at least one support for the internal systems module is connected to at least one of at least one upper or lower spar, or at least one first or second lateral panel of the subassembly assembled in the first assembly step, a third step of assembling any element of the primary structure not assembled in the first assembly step, and a step of installing and securing the external systems and the secondary structure.

2. The method for assembling an aircraft pylon as claimed in claim 1, wherein the upper and lower spars, the first and second lateral panels and the supports are pre-drilled before being assembled, and wherein during the first, second and third assembly steps, the upper and lower spars, the first and second lateral panels and the at least one support are positioned relative to one another in such a way that holes line up in order to be able to receive fasteners, and then the fasteners are installed.

3. The method for assembling an aircraft pylon as claimed in claim 1, wherein the internal systems module comprises multiple mutually independent supports.

4. The method for assembling an aircraft pylon as claimed in claim 1, wherein the internal systems module comprises multiple supports that are connected to one another by longitudinal stiffeners.

5. The method for assembling an aircraft pylon as claimed in claim 4, wherein each support is formed as a frame, the at least one internal system of the internal systems module comprises multiple internal systems, and the multiple internal systems are connected to the at least one support or the longitudinal stiffeners by connectors, so as to keep the internal systems from moving relative to the at least one support and relative to the longitudinal stiffeners.

6. The method for assembling an aircraft pylon as claimed claim 1, wherein the at least one support of the internal systems module comprises at least one through-hole through which there passes the at least one internal system and first and second parts that meet at a junction plane, the first and second parts comprising, for each through-hole, first and second semi-cylindrical shapes delimiting the through-hole when the first and second parts meet.

7. The method for assembling an aircraft pylon as claimed in claim 6, wherein the internal system passing through the through-hole is cylindrical at least in line with the through-hole, and the through-hole is cylindrical and has a diameter substantially equal to that of the internal system.

8. The method for assembling an aircraft pylon as claimed in claim 6, wherein each of the first and second parts of the support comprises a comb made of elastomeric material, having a semi-cylindrical shape for each through-hole.

9. An aircraft pylon obtained by the assembly method as claimed in claim 1, wherein the aircraft pylon comprises: a primary structure, and an internal systems module comprising: at least one internal system, and at least one support to which the internal system is connected, said internal systems module being positioned inside the primary structure, and each support of the internal systems module being connected to the primary structure.

10. The aircraft pylon as claimed in claim 9, wherein each support comprises at least one through-hole through which there passes an internal system and first and second parts that meet at a junction plane, and wherein the first and second parts comprise, for each through-hole, first and second semi-cylindrical shapes delimiting the through-hole when the first and second parts meet.

11. The aircraft pylon as claimed in claim 10, wherein the internal system passing through the through-hole is cylindrical at least in line with the through-hole, and wherein the through-hole is cylindrical and has a diameter substantially equal to that of the internal system.

12. The aircraft pylon as claimed in claim 10, wherein each of the first and second parts of the support comprises a comb made of elastomeric material, having a semi-cylindrical shape for each through-hole.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Other features and advantages will emerge from the following description of the invention, which description is given solely by way of example, with reference to the appended drawings in which:

[0035] FIG. 1 is a side view of an aircraft,

[0036] FIG. 2 is a side view of a primary structure of a pylon connecting an engine to a wing, illustrating one embodiment,

[0037] FIG. 3 is an exploded perspective view of a primary structure of a pylon, illustrating one embodiment of the prior art,

[0038] FIG. 4 is a cross section through an aircraft pylon, illustrating an embodiment of the prior art,

[0039] FIG. 5 is an exploded perspective view of a primary structure of an aircraft pylon, illustrating one embodiment of the invention,

[0040] FIG. 6 is a perspective view of part of a primary structure of a pylon, illustrating a first step of a method for assembling an aircraft pylon,

[0041] FIG. 7 is a perspective view of an internal systems module of an aircraft pylon, illustrating a first embodiment of the invention,

[0042] FIG. 8 is a front view of a support of an internal systems module, illustrating an embodiment of the invention,

[0043] FIG. 9 is a perspective view of the part of the primary structure that can be seen in FIG. 6, in which the internal systems module, shown in FIG. 7, is positioned,

[0044] FIG. 10 is a perspective view of the primary structure shown in FIG. 9, at the end of its assembly process,

[0045] FIG. 11 is a perspective view of an internal systems module of an aircraft pylon, illustrating a second embodiment of the invention,

[0046] FIG. 12 is a perspective view of a part of the primary structure of an aircraft pylon, in which the internal systems module, shown in FIG. 11, is positioned, and

[0047] FIG. 13 is a perspective view of the primary structure shown in FIG. 12, at the end of its assembly process.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0048] FIGS. 5, 10, 13 show a primary structure 50 of an aircraft pylon which comprises:

[0049] an upper spar 52,

[0050] a lower spar 54,

[0051] a front reinforcement 56 which connects a front end of the upper spar 52 and a front end of the lower spar 54,

[0052] a rear reinforcement 58 which connects a rear end of the upper spar 52 and a rear end of the lower spar 54,

[0053] first and second lateral panels 60, 62, which connect the upper and lower spars 52, 54 which are arranged on either side of the front and rear reinforcements 56, 58.

[0054] According to one embodiment, the primary structure 50 comprises at least one intermediate reinforcement 64, connecting the upper and lower spars 52, 54, in the form of a frame arranged in a transverse plane.

[0055] The aircraft pylon also comprises a secondary structure that caps the primary structure 50 and is spaced apart therefrom, at least one internal system 66 positioned at least partially within the primary structure 50, and at least one external system positioned outside the primary structure 50, between the latter and the secondary structure.

[0056] As illustrated in FIGS. 5, 7 and 11, the aircraft pylon comprises multiple internal systems 66 such as pipes, cable bundles, a fire extinguishing system, a drainage system. The internal systems 66 and the external systems are not described further since they may be identical to those of the prior art.

[0057] A method for assembling an aircraft pylon comprises a first step of assembling at least one upper or lower spar 52, 54 and at least one of the first and second lateral panels 60, 62 that are connected by fasteners so as to obtain a subassembly.

[0058] According to a first approach, shown in FIGS. 6 and 9, the upper spar 52 and a first lateral panel 60 are assembled.

[0059] According to a second approach, shown in FIG. 13, the upper and lower spars 52, 54 and a first lateral panel 60 are assembled.

[0060] According to one configuration, during this first assembly step, the front and/or rear reinforcements 56, 58, and possibly at least one intermediate reinforcement 64, are assembled and connected by means of fasteners to at least one of the upper and lower spars 52, 54, and to at least one of the first and second lateral panels 60, 62.

[0061] Whatever the approach, at the end of this first assembly step, at least one first or second lateral panel 60, 62 or at least one upper or lower spar 52, 54 is not assembled, making the interior of the primary structure 50 largely accessible and facilitating the installation of the internal systems 66.

[0062] According to a so-called “hole-to-hole” assembly approach, the elements of the subassembly among the upper and lower spars 52, 54, the first and second lateral panels 60, 62, the front, rear and intermediate reinforcements 56, 58, 64 are pre-drilled prior to the first assembly step and are not counter-drilled during this first assembly step. Thus, during this first assembly step, the elements of the subassembly are positioned relative to one another in such a way that holes for the fasteners are aligned, then these fasteners are installed.

[0063] In parallel with the first assembly step, the method for assembling the pylon includes a step of mounting an internal systems module 68 comprising at least one internal system 66 and at least one support 70 to which the internal system 66 is connected. A support 70 is an element distinct from the primary structure 20.

[0064] According to a first embodiment, shown in FIGS. 7 and 9, the internal systems module 68 comprises multiple mutually independent supports 70 that are offset with respect to one another along the longitudinal direction.

[0065] As illustrated in detail in FIG. 8, each support 70 is positioned in a transverse plane and comprises at least one through-hole 72 through which an internal system 66 passes. According to another feature, the internal system 66 passing through the through-hole 72 is cylindrical, at least in line with the through-hole. In this case, the through-hole 72 is also cylindrical and has a diameter substantially equal to that of the internal system 66 in order to immobilize it in a transverse plane.

[0066] According to one embodiment, each support 70 comprises first and second parts 74, 76 that meet at a junction plane PJ, the first and second parts 74, 76 comprising, for each through-hole 72, first and second semi-cylindrical shapes 74.1, 76.1 delimiting the through-hole 72 when the first and second parts 74, 76 meet at the junction plane PJ. According to one configuration, after assembly of the pylon, the first part 74 is connected to the first lateral panel 60 and the second part 76 is connected to the second lateral panel 62. According to this configuration, the junction plane PJ is parallel to the first and second lateral panels 60, 62 when the support 70 is installed in the primary structure 50 and equidistant from the first and second lateral panels 60, 62.

[0067] According to one embodiment, each of the first and second parts 74, 76 of each support 70 comprises multiple elements that are joined together. Thus, each of the first and second parts 74, 76 comprises a plate 78, a bracket 80 positioned at a first side of the plate 78 configured to be connected to the first or second panel 60, 62, and a comb 82 positioned at a second side of the plate 78, opposite the first side. This comb 82 has a first flange connected to the plate 78 and a second flange in which there is formed a semi-cylindrical shape 74.1, 76.1 for each through-hole 72. The various elements of each of the first and second parts 74, 76 can be made of metal. According to one configuration, the comb 82 is made of an elastomer material in order to make the connection between the support 70 and the internal system 66 more flexible. This configuration makes it possible to increase the manufacturing tolerances of the support 70.

[0068] According to a second embodiment, shown in FIGS. 11 and 12, the internal systems module 68 comprises multiple supports 70 that are offset with respect to one another along the longitudinal direction, and connected to one another by longitudinal stiffeners 84. According to this second embodiment, the supports 70 and the longitudinal stiffeners 84 form a rigid structure.

[0069] According to this second embodiment, each support 70 is in the form of a frame. The various internal systems 66 are connected to the supports 70 and/or to the longitudinal stiffeners 84 by appropriate connectors 86 in order to prevent each of the internal systems 66 from moving relative to the supports 70 and relative to the longitudinal stiffeners 84.

[0070] When the internal systems module 68 is finished, the method for assembling the pylon comprises a second step of assembling the internal systems module 68 and the subassembly assembled during the first assembly step. During this second assembly step, the internal systems module 68 is positioned relative to the subassembly and connected, using fasteners, to at least one upper or lower spar 52, 54, and/or at least one first or second lateral panel 60, 62 of the subassembly assembled in the first assembly step.

[0071] Whatever the embodiment of the internal systems module 68, all of the internal systems 66 are positioned in the primary structure in a single step, which helps to reduce in particular the time for assembling the pylon.

[0072] Each support 70 is connected to at least one upper or lower spar 52, 54, and/or at least one first or second lateral panel 60, 62 of the subassembly assembled in the first assembly step. According to a so-called “hole-to-hole” assembly approach, the supports 70 and the upper and lower spars 52, 54, to which the supports 70 are connected, are pre-drilled. Thus, each of the supports 70 is positioned relative to the elements of the subassembly assembled in the first assembly step in such a way that holes for fasteners are aligned, then these fasteners are installed.

[0073] The assembly method comprises a third assembly step that aims to close the primary structure 50 by assembling, using fasteners, the elements among the upper and lower spars 52, 54, the first and second lateral panels 60, 62, the front, rear and intermediate reinforcements 56, 58, 64 not assembled during the first assembly step. According to the first operating approach, shown in FIGS. 6, 9 and 10, the lower spar 54 and the second lateral panel 62 are connected to the upper spar 52, to the first lateral panel 60, to the front, rear and intermediate reinforcements 56, 58, 64 and to the supports 70 of the internal systems module 68.

[0074] According to the second operating approach, shown in FIGS. 12 and 13, the second lateral panel 62 is connected to the upper and lower spars 52, 54, to the front, rear and intermediate reinforcements 56, 58, 64 and to the supports 70 of the internal systems module 68.

[0075] According to a so-called “hole-to-hole” assembly approach, the elements assembled during the third assembly step are pre-drilled and are not counter-drilled during this third assembly step. Thus, the assembled elements are positioned relative to one another in such a way that holes for the fasteners are aligned, then these fasteners are installed.

[0076] The first, second and third steps of the method for assembling the pylon, described above, are carried out in this chronological order: the first step, then the second step and finally the third step.

[0077] Finally, the method for assembling the pylon comprises a step of installing and securing the external systems and the secondary structure.

[0078] At the conclusion of the assembly process, the aircraft pylon comprises a primary structure 50 and an internal systems module 68 comprising at least one internal system 66 and at least one support 70 to which the internal system 66 is connected, the internal systems module 68 being positioned inside the primary structure 50, each support 70 of the internal systems module 68 being connected to the primary structure 50. All of the internal systems 66 are integrated into the same internal systems module 68 and are positioned in the primary structure all at the same time.

[0079] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.