Hanger, aircraft, and method for welding a panel and a longitudinal beam forming the hanger

Abstract

The present application relates to a pylon, an aircraft, and a method of welding a panel and a spar forming the pylon. The pylon includes a main structure formed by at least one spar and a panel assembled by welding. The pylon designed to support an aircraft engine includes a main structure (6) formed by at least one spar (7, 7A, 7B, 8) and a panel (9A, 9B), the panel (9A, 9B) including at least one end portion (10) provided with a notch, the spar (7, 7A, 7B, 8) being provided with an end (13) adapted to be positioned in the notch, and the panel (9A, 9B) and the spar (7, 7A, 7B, 8) being assembled by welding a part of the end (13) to a part of the notch. The welded main structure (6) can minimize the blanks of the parts associated with the spar and the panel by avoiding the generation of edges.

Description

Field of the Invention

[0001] The present invention relates to a pylon intended to support an aircraft engine under an aircraft wing, the pylon comprising a main structure formed by at least one longitudinal beam and a panel assembled by welding, and an aircraft provided with such a pylon. Background of the Invention

[0002] Generally, an aircraft, such as an airplane, especially a transport airplane, is propelled by an engine. Here, the engine refers to any type of propulsion device, such as a turboprop engine, a turbojet engine, etc. Each engine can be attached to the aircraft fuselage or other components, such as a tail unit, by a pylon under the wing (also called a wing surface).

[0003] The pylon generally supports the engine and transmits the forces generated by the operation of the engine to the wing surface of the aircraft. It also enables the transfer of fuel, electricity, hydraulics, and air between the engine and the aircraft.

[0004] To perform its functions, the pylon includes a rigid main structure preferably made of titanium. The main structure is formed by a plurality of ribs arranged continuously in the longitudinal direction and constitutes the framework of a "box section" type compartment. The ribs connect the upper and lower longitudinal beams, and the laterally arranged panels complete the box section. Each longitudinal beam is usually fixed to the side panel by its edge by means of bolt-type fixing devices.

[0005] The manufacture of the main structure generally requires the production of blanks corresponding to the side panels and the upper and lower longitudinal beams respectively. Each blank is machined to obtain the side panels and longitudinal beams forming the main structure. After machining, the edges of each side panel and each longitudinal beam are pierced over their entire length and then brought into contact to be fixed together by bolts.

[0006] The production of the main structure box section requires a large amount of raw materials, including a certain proportion of material waste, which especially results in high production costs due to the edges that must be manufactured.

[0007] Therefore, such a solution is not entirely satisfactory.

[0008] Documents US2014 / 151497 and EP3476740 disclose such pylons, in which the side panels are assembled to form the pylon. Summary of the Invention

[0009] The object of the present invention is to remedy this drawback. The present invention relates to a pylon intended to support an engine of an aircraft, especially an airplane, and comprising a main structure formed by at least one longitudinal beam and a panel.

[0010] According to the present invention, the panel includes at least one end portion in which a notch is formed, the longitudinal beam is provided with at least one end adapted to be positioned in the notch, and the panel and the longitudinal beam are assembled by welding at least a part of the end to at least a part of the notch.

[0011] Thanks to the present invention, the main structure is thus produced by welding its components, thereby minimizing the blanks of the parts associated with the longitudinal beam and the panel by avoiding resorting to the generation of edges. In addition, the welding of the end of the longitudinal beam in the notch of the end portion of the panel makes the assembly stronger and easier to produce.

[0012] The notch is advantageously formed by an adjacent member, the end of the longitudinal beam includes a contact surface, and at least a part of the adjacent member is adapted to the contact surface.

[0013] According to a first embodiment, the notch further includes a lip formed in a plane parallel to the longitudinal beam, and the lip forms an angle of approximately 90 degrees with the adjacent member.

[0014] According to a second embodiment, the notch further includes a lip formed in a plane parallel to the longitudinal beam, and the lip forms an angle greater than 90 degrees with the adjacent member.

[0015] In addition, according to the first embodiment, the end further includes a surface portion of the longitudinal beam that contacts the lip of the notch.

[0016] In addition, in the second embodiment, the end further includes a surface portion of the longitudinal beam, and the surface portion and the lip of the notch are spaced apart from each other.

[0017] According to a first specific embodiment, welding is generated at the surface where at least a part of the adjacent member is joined to the contact surface.

[0018] In a second specific embodiment, welding is generated on the surface where the adjacent member is joined to the contact surface and on a part of the surface where the lip of the notch is joined to the surface portion of the longitudinal beam.

[0019] According to the first embodiment, welding is generated continuously along the end of the longitudinal beam.

[0020] According to the second embodiment, welding is generated discontinuously along the end of the longitudinal beam.

[0021] Advantageously, the hanger includes a main structure formed by multiple pairs of panels and longitudinal beams, each pair includes a panel and a longitudinal beam, and as described above, the longitudinal beam and the panel of each pair are assembled by welding.

[0022] The present invention also relates to a method of welding a panel and a longitudinal beam, the panel and the longitudinal beam forming part of a hanger as described above.

[0023] According to the present invention, the method comprises the following steps:

[0024] - a step of creating a notch in an end portion of the panel;

[0025] - a step of positioning the end of the longitudinal beam in the notch in the panel; and

[0026] - a step of welding a part of the end of the longitudinal beam to at least a part of the notch.

[0027] Furthermore, the present invention relates to an aircraft, in particular an aeronautical vehicle, provided with a hanger as described above. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The drawings will clearly explain how the present invention can be reduced to practice. In those figures, the same reference numerals refer to similar elements.

[0029] Figure 1 A top view of an aircraft equipped with a hanger according to an embodiment is schematically shown.

[0030] Figure 2 is a schematic representation of the main structure of a hanger according to an embodiment.

[0031] Figure 3 A longitudinal beam and a panel assembled according to an embodiment are schematically shown in cross-section.

[0032] Figure 4A and Figure 4B Weld beads according to the first and second embodiments are schematically shown in cross-section.

[0033] Figure 5 A schematic representation showing an embodiment of the welding method is shown. DETAILED DESCRIPTION

[0034] The aircraft engine propels the latter (the aircraft). It is generally connected to the rest of the aircraft structure by a hanger 1 as shown in Figure 2 . In the context of the present invention, the aircraft can be an aeronautical vehicle, a flying wing, an aircraft without a fuselage, etc.

[0035] In the following, reference is made to Figure 1In a preferred application described, the aircraft is an aeronautical vehicle AC, in particular a transport aircraft. The aircraft AC includes a fuselage 2 to which two wings 3G, 3D are fixed on respective opposite sides. These wings 3G and 3D are also referred to as wing surfaces 3G, 3D. The aircraft AC also includes engines 4G, 5G and 4D, 5D for propelling the aircraft in a forward direction S. The pylon 1 described for illustrating the invention and shown in Figure 1 and Figure 2 is adapted to support each of the engines 4G, 5G, 4D, 5D under the wings 3G and 3D.

[0036] For the sake of facilitating the following description, three mutually orthogonal directions are introduced. The direction X corresponds to the longitudinal direction of the pylon 1 and is parallel to the longitudinal direction of the fuselage 2 of the aircraft AC oriented in the forward direction S of the aircraft AC. In addition, the transverse direction Y corresponds to a direction oriented transversely with respect to the pylon 1. The transverse direction Y also corresponds to the general direction in which the wings 3G and 3D of the aircraft AC extend. Finally, the vertical direction Z corresponds to the vertical direction of the pylon 1 and is parallel to the direction representing height.

[0037] In addition, the adjectives "front" and "rear" are defined respectively with respect to the longitudinal direction X in the forward direction S of the aircraft AC when the engine exerts thrust and in the direction opposite to the forward direction S. In addition, the adjectives "upper" and "lower" are defined respectively with respect to the vertical direction Z towards the wings 3G, 3D and towards the engines 4G, 5G, 4D, 5D. Finally, the adjectives "outer" and "inner" are defined respectively with respect to the transverse direction Y towards the tips of the wings 3G, 3D and towards the fuselage 2.

[0038] As Figure 2 shown, the pylon 1 includes a main structure 6 in the form of a box-shaped section extending along the longitudinal direction X. The main structure 6 is formed by an upper longitudinal beam 7. The upper longitudinal beam 7 includes a front upper longitudinal beam 7A and a rear upper longitudinal beam 7B, each having a generally elongated shape in the length direction X. The front upper longitudinal beam 7A and the rear upper longitudinal beam 7B are arranged continuously in the longitudinal direction X and are fixed together in the transverse direction Y by fixing means (not shown). For example, those fixing means are welds. The front upper longitudinal beam 7A and the rear upper longitudinal beam 7B extend in a plane substantially perpendicular to the vertical direction Z. The planes in which the front upper longitudinal beam 7A and the rear upper longitudinal beam 7B extend have a non-zero angle therebetween.

[0039] The main structure 6 further includes a lower longitudinal beam 8 having a generally elongated shape in the longitudinal direction X. The upper longitudinal beam 7 and the lower longitudinal beam 8 are connected by two side panels extending in a plane that can be substantially perpendicular to the transverse direction Y. Those side panels include an inner side panel 9A (hereinafter referred to as "inner panel 9A") and an outer side panel 9B (hereinafter referred to as "outer panel 9B"). In a preferred embodiment, the inner panel 9A and the outer panel 9B are arranged in planes inclined to each other.

[0040] As Figure 2 shown, each of the side panels is provided with an end portion 10 extending generally along the longitudinal direction X. The end portion 10 includes an upper part 10A and a lower part 10B arranged opposite to each other in the vertical direction Z.

[0041] In a preferred embodiment, notches 17 are formed in the upper parts 10A of the inner panel 9A and the outer panel 9B so as to face the upper longitudinal beam 7. Notches 17 are also formed in the lower parts 10B of the inner panel 9A and the outer panel 9B so as to face the front upper longitudinal beam 7A and the rear upper longitudinal beam 7B. Each notch 17 formed in the lower part 10B extends in the direction in which the lower longitudinal beam 8 extends. Each notch 17 formed in the upper part 10A extends in the direction in which the front upper longitudinal beam 7A and the rear upper longitudinal beam 7B extend.

[0042] As Figure 3 、 4A and 4B shown, each notch 17 formed in the upper part 10A is formed by an adjacent member 12. The adjacent members 12 of the upper edges 10A of the inner panel 9A and the outer panel 9B face each other. In a similar manner, each notch 17 formed in the lower part 10B of each of the inner panel 9A and the outer panel 9B includes an adjacent member 12 (not shown), against which the lower longitudinal beam 8 is arranged.

[0043] In addition, the adjacent member 12 of the notch 17 in the upper part 10A is configured to contact the upper longitudinal beam 7. The adjacent member 12 of the lower part 10B is adapted to contact the lower longitudinal beam 8. The adjacent member 12 is adapted to prevent any movement of the upper longitudinal beam 7 and the lower longitudinal beam 8 in the transverse direction Y, and contacts to form a welding line and close the main structure 6.

[0044] As Figure 3 、 4AAs shown in FIGS. 4A and 4B, the notch 17 also includes a lip 11. In the context of the present invention, the lip 11 refers to the surface that forms the notch 17 with the adjacent member. The lip 11 of the notch 17 formed in the upper part 10A extends in a direction parallel to the direction in which the upper longitudinal beam 7 extends. The lip 11 of the notch 17 formed in the lower part 10B extends in a direction parallel to the direction in which the lower longitudinal beam 8 extends. In the first embodiment, the lip 11 and the adjacent member 12 are arranged at an angle of approximately 90 degrees in a plane. In a second embodiment (not shown), the lip 11 and the adjacent member 12 form an angle greater than 90 degrees. Then, the adjacent member 12 extends in a plane parallel to the plane in which the inner panel 9A or the outer panel 9B extends.

[0045] In addition, the upper longitudinal beam 7 is provided with two ends 13 that are substantially parallel to each other. The lower longitudinal beam 8 is also provided with two ends 13 that are substantially parallel to each other. As Figure 3 , 4A and as shown in FIGS. 4A and 4B, each end 13 of the upper longitudinal beam 7 and the corresponding lower longitudinal beam 8 is adapted to be positioned partially or entirely in the notch 17 formed in each of the upper part 10A of the inner panel 9A and the outer panel 9B and the corresponding lower part 10B. In a preferred embodiment, each end 13 is formed by a contact surface 15, and at least a part of the adjacent member 12 is adapted to the contact surface 15.

[0046] In addition, each end 13 of the upper longitudinal beam 7 and the corresponding lower longitudinal beam 8 also includes a surface portion 14. In the first embodiment, when the end 13 is positioned in the notch 17, the surface portion 14 does not contact the lip 11. The lip 11 and the surface portion 14 are spaced apart from each other. As Figure 3 shown in FIGS. 4A and 4B, only the contact surface 15 of each end 13 contacts the adjacent member 12 arranged facing them. In the second embodiment, the surface portion 14 contacts the lip 11 of the upper part 10A and the corresponding lower part 10B. The thickness of the upper longitudinal beam 7 in the vertical direction Z also represents the height of the contact surface 15 in the vertical direction Z. In addition, the adjacent member 12 is adapted to the contact surface 15 such that the height value of the adjacent member 12 is substantially equal to the height value of the contact surface 15.

[0047] In a preferred embodiment, the inner panel 9A, the outer panel 9B, and the upper longitudinal beam 7 and the corresponding lower longitudinal beam 8 are assembled by welding each end portion 10 of the inner panel 9A and the outer panel 9B to the end 13 of the upper longitudinal beam 7 and the lower longitudinal beam 8 that is in contact with it. This welding is a so-called edge-to-edge welding.

[0048] As Figure 4A and Figure 4BAs shown, welding produces a weld bead 16 that connects the end 13 of the upper longitudinal beam 7 (or the lower longitudinal beam 8) to the end portion 10 of the inner panel 9A and the end portion 10 of the outer panel face 9B. Welding also produces a heat-affected zone (not shown) common to the welded-together end 13 and notch 17. The weld bead 16 extends on the surface where the adjacent member 12 and the contact surface 15 join. This joining surface is arranged in a plane that is substantially parallel to the plane in which the inner panel 9A (and correspondingly the outer panel 9B) extends. The weld bead 16 extends in the direction in which the longitudinal beams 7 and 8 extend, which corresponds to the direction of the neutral fiber. Such an orientation minimizes the fatigue of the weld bead 16 and thus the risk of welding weakening. This also limits the force transmission between the panels 9A, 9B and each longitudinal beam 7, 8. The load on the weld bead 16 is not large.

[0049] In addition, in a preferred embodiment, each end of the upper longitudinal beam 7 and correspondingly the lower longitudinal beam 8 is assembled by welding to the upper part 10A and correspondingly the lower part 10B. Thus, welding is produced in a manner symmetric with respect to the inner panel 9A and the outer panel 9B, such that the deformation of the main structure 6 in use is balanced. This balance minimizes the risk of premature welding failure. Therefore, there is no need to use auxiliary heat treatment to prevent premature wear of some parts of the main structure 6.

[0050] In addition, the lip 11 of the notch 17 enables prevention of the welding material from being projected into the main structure 6.

[0051] In the first embodiment, the weld bead 16 has a depth in a direction inclined with respect to the vertical direction Z, and its minimum value can be less than or equal to the height value of the adjacent member 12, as Figure 4A shown. In this first embodiment, the surface portion 14 of the upper longitudinal beam 7 and correspondingly the lower longitudinal beam 8 contacts the lip 11 of the notch 17. In a variant of this first embodiment, as Figure 3 shown, the surface portion 14 does not contact the lip 11.

[0052] In the second embodiment, the weld bead 16 has a depth that reaches the lip 11, as Figure 4B shown. The weld extends in the plane in which the lip 11 is arranged. In this second embodiment, the surface portion 14 of the longitudinal beams 7, 8 can contact the lip 11. Then, the welding extends on the surface where the lip 11 and the surface portion 14 join. In a variant of this second embodiment, the surface portion 14 does not directly contact the lip 11. As Figure 3 shown, the surface portion 14 and the lip 11 are spaced apart from each other.

[0053] When welding is produced at the joint surface between the adjacent part 12 and the contact surface 15 and the surface portions 14 of the longitudinal beams 7, 7A, 7B, 8 do not contact the lip 11, this enables tolerances to be retained to prevent possible deformation of the main structure 6. On the other hand, when the surface portions 14 of the longitudinal beams 7, 7A, 7B, 8 contact the lip 11, it is not possible to maintain the tolerance of deformation at the welding level.

[0054] Welding is produced at a smaller thickness in order to minimize the thermal energy introduced into the materials forming the upper longitudinal beam 7 and the lower longitudinal beam 8 and the inner panel 9A and the outer panel 9B.

[0055] Furthermore, as described above, the upper longitudinal beam 7 includes a front upper longitudinal beam 7A and a rear upper longitudinal beam 7B. The front upper longitudinal beam 7A and the rear upper longitudinal beam 7B are arranged in a plane at a non-zero angle.

[0056] In a specific embodiment, welding is continuously produced along the ends 13 of the front upper longitudinal beam 7A and the rear upper longitudinal beam 7B. In another specific embodiment, welding is discontinuously produced along the ends 13 in the direction in which the lower longitudinal beam 8 extends (in the longitudinal direction X) and in the direction in which the upper longitudinal beam 7 extends (in a direction at an angle to the longitudinal direction X).

[0057] The welding is continuous in the vertical direction Z.

[0058] As Figure 5 shown below, a method for welding the panels 9A, 9B to the longitudinal beams 7, 7A, 7B, 8 is described. The method includes the following steps:

[0059] - Step E1 of producing notches 17 in each end portion 10 of the inner panel 9A and the outer panel 9B. The notches 17 are directly produced in the blanks of those panels 9A and 9B;

[0060] - Step E2 of positioning the ends 13 of the longitudinal beams 7, 7A, 7B, 8 in the notches 17 of the panels 9A, 9B; and - Step E3 of edge-to-edge type welding of the ends 13 to the notches 17.

[0061] Furthermore, the design of the hanger 1 simplifies the production of the main structure 6. The edge-to-edge welding of the panels and the longitudinal beams has the following advantages:

[0062] - Reducing the mass of the main structure 6 by the absence of bolt-type fixing devices and the absence of edges;

[0063] - Saving the cost of bolt-type fixing devices; and

[0064] - The possibility of performing non-destructive testing during the production of the main structure.

[0065] In addition, edge-to-edge welding can reduce raw material waste. In fact, the notches 17 where the welding occurs are directly formed in the blanks of the panels 9A, 9B. Since there are no edges, such blanks have small dimensions. In addition, the longitudinal beams 7, 7A, 7B, 8 do not require special machining because they are positioned in the notches 17.

Claims

1. A pylon for supporting an engine of an aircraft, the pylon (1) comprising a main structure (6) formed by at least one longitudinal beam (7, 7A, 7B, 8) and a panel (9A, 9B), It is characterized in that The panel (9A, 9B) comprises at least one end portion (10) in which a notch (17) including a lip (11) is formed. The longitudinal beam (7, 7A, 7B, 8) is provided with at least one end (13) adapted to be positioned in the notch (17). The panel (9A, 9B) and the longitudinal beam (7, 7A, 7B, 8) are assembled by welding at least a part of the end (13) of the longitudinal beam (7, 7A, 7B, 8) to at least a part of the notch (17). The end (13) includes a surface portion (14) of the longitudinal beam (7, 7A, 7B). The surface portion (14) and the lip (11) of the notch (17) are opposite to each other and spaced apart from each other along the vertical direction (Z) of the pylon.

2. The pylon according to claim 1, It is characterized in that The notch (17) is formed by an adjacent member (12). The end (13) of the longitudinal beam (7, 7A, 7B, 8) includes a contact surface (15). At least a part of the adjacent member (12) is adapted to the contact surface (15).

3. The pylon according to claim 2, Characterized in that, The lip (11) is arranged in a plane parallel to the longitudinal beam (7, 7A, 7B). The lip (11) and the adjacent member (12) form an angle approximately equal to 90 degrees.

4. The pylon according to claim 2, It is characterized in that The notch (17) further includes a lip (11) arranged in a plane parallel to the longitudinal beam (7, 7A, 7B). The lip (11) and the adjacent member (12) form an angle greater than 90 degrees.

5. The pylon according to claim 2, It is characterized in that The welding is produced on the joint surface of at least a part of the adjacent member (12) and the contact surface (15).

6. The pylon according to any one of claims 1 to 5, It is characterized in that The welding is produced continuously along the end (13) of the longitudinal beam (7, 7A, 7B, 8).

7. The pylon according to any one of claims 1 to 5, It is characterized in that The welding is produced discontinuously along the end (13) of the longitudinal beam (7, 7A, 7B, 8).

8. The pylon according to any one of claims 1 to 5, It is characterized in that It includes a main structure (6) formed by multiple pairs of panels (9A, 9B) and longitudinal beams (7, 7A, 7B, 8). Each pair includes a panel (9A, 9B) and a longitudinal beam (7, 7A, 7B, 8). The longitudinal beam (7, 7A, 7B, 8) and the panel (9A, 9B) in each pair are assembled by welding.

9. A method of welding a panel (9A, 9B) and a longitudinal beam (7, 7A, 7B, 8) forming a part of the pylon (1) according to any one of claims 1 to 8, the method comprising the following steps: - Step (E1) of generating the notch (17) in the end portion (10) of the panel (9A, 9B); - Step (E2) of positioning the end (13) of the longitudinal beam (7, 7A, 7B) in the notch (17) in the panel (9A, 9B); and - Step (E3) of welding a part of the end (13) of the longitudinal beam (7, 7A, 7B) to at least a part of the notch (17).

10. An aircraft, comprising a suspension bracket (1) according to any one of claims 1 to 8.

11. The aircraft according to claim 10, It is characterized in that wherein the aircraft is an aeronautical craft (AC).

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