Assembly for an aircraft comprising a wing and a reactor mass for coupling a propulsion system to the wing

Abstract

The invention relates to an assembly (100) comprising a wing (104) and a reaction main rod (106) fixed to the wing (104). To achieve this, the main structure (202) of the reaction main rod comprises a first fixing lug and a starboard fixing lug (272) and a port fixing lug (273), whereas the wing (104) carries a first fitting and a starboard fitting (212) and a port fitting (213), said fixing lugs (272, 273) being joined to said fittings (212, 213) by means of a lock beam having three fixing points, whereas said first lug is fixed to said first fitting. By means of this arrangement, it is possible to ensure a better transmission of forces to the wing structure, while ensuring that these forces are transmitted in the event of breakage of the fastener part.

Description

Technical Field

[0001] The invention relates to an assembly for an aircraft comprising a wing and a reaction rod for coupling a propulsion system to the wing, and to an aircraft comprising a propulsion system and such an assembly for coupling a propulsion system to the wing. Background Art

[0002] Typically, for an aircraft, the propulsion assembly comprises, for example, a turbojet engine, which is fixed to the aircraft wing by means of a reaction rod. The reaction rod generally consists of a main structure formed by a caisson, which is composed of an upper longitudinal beam, a lower longitudinal beam and two side panels connecting the two longitudinal beams, as well as internal ribs distributed along the caisson.

[0003] The turbojet engine is fixed below the reaction machine main rod by means of an engine attachment, which conventionally includes a front engine attachment at the front, a rear engine attachment at the rear, and a thrust absorbing assembly between the front engine attachment and the rear engine attachment, the thrust absorbing assembly including a transfer rod fixed between the turbojet engine and the main structure of the main rod so as to absorb the thrust generated by the turbojet engine.

[0004] Furthermore, the reaction rod is fixed to the wing structure by means of a fitting, through which the forces from the turbojet engine are transmitted to the wing structure. Although the current arrangement is satisfactory, it is necessary to provide an embodiment that improves the force transmission and increases safety, for example in the event of a breakage of a component of the fixing. Summary of the invention

[0005] The object of the present invention is to provide an assembly for an aircraft comprising a wing and a reaction rod for coupling a propulsion system to the wing, the assembly comprising a wing fastening device which ensures a better transmission of forces to the wing structure while guaranteeing the transmission of these forces in the event of breakage of a component part of the fastening.

[0006] To this end, an assembly for installing a propulsion system with a vertical mid-plane on an aircraft is proposed, the assembly comprising:

[0007] - a wing having a front longitudinal beam and an inner camber panel fixed to a lower section of the front longitudinal beam, wherein the front longitudinal beam carries a first fitting at the level of a vertical mid-plane, and wherein the inner camber panel carries a starboard fitting and a port fitting;

[0008] - a reaction machine main rod, the reaction machine main rod comprising a main structure;

[0009] - a first starboard lock beam secured to said starboard fitting by means of a first pivot connection and a second pivot connection about an axis extending substantially perpendicular to the midplane;

[0010] - a first port lock beam secured to the port fitting by means of a fourth pivot connection and a fifth pivot connection about an axis extending substantially perpendicular to the midplane.

[0011] The rear portion of the main structure comprises a first fixing lug extending rearwards and at the level of the vertical mid-plane, which is fixed to the first fitting by a seventh connection having at least one degree of freedom of rotation about a vertical axis.

[0012] The aft portion also includes a starboard securing ear and a port securing ear extending on each side and to the aft portion of the aft portion.

[0013] The starboard securing ear is secured to the first starboard locking beam by a third pivot connection about an axis extending generally perpendicular to the midplane, and the port securing ear is secured to the first port locking beam by a sixth pivot connection about an axis extending generally perpendicular to the midplane.

[0014] Advantageously, the assembly further comprises:

[0015] - a second starboard lock beam, the second starboard lock beam extending substantially parallel to the first starboard lock beam, the second starboard lock beam being fixed to the starboard fitting via the first and second connecting portions, and fixed to the starboard fixing ear via the third connecting portion;

[0016] - a second port lock beam, which extends substantially parallel to the first port lock beam, the second port lock beam being fixed to the port fitting via the fourth and fifth connecting portions, and fixed to the port fixing ear via the sixth connecting portion.

[0017] The first starboard lock beam and the second starboard lock beam enclose the starboard fitting and the starboard fixing ear, while the first port lock beam and the second port lock beam enclose the port fitting and the port fixing ear.

[0018] According to a particular aspect of the invention, each locking beam comprises two plates fixed juxtaposed to each other.

[0019] According to another particular aspect of the invention, the starboard and port fittings each have a substantially T-shaped cross section, with a horizontal portion fixed to the lower section of the front longitudinal beam and an associated pivot connection made in the vertical section.

[0020] According to another specific aspect of the present invention, each of the starboard fitting and the port fitting is composed of two elements having a substantially Γ-shaped (half-T-shaped) cross section and being integral with each other.

[0021] According to a specific aspect of the present invention, the first fixing ear comprises two adjacent sub-ears fixed against each other.

[0022] According to a specific aspect of the present invention, the seventh connection portion between the first fixing ear and the first accessory includes a main shaft and a secondary shaft extending coaxially inside the main shaft.

[0023] According to a specific aspect of the invention, the rear section comprises a first port protrusion and a first starboard protrusion extending vertically in a plane substantially perpendicular to the vertical midplane, the first protrusion being arranged on each side of the main structure. For the first port protrusion, the assembly comprises a first rod, the first end of which is fixed to the first port protrusion by an eighth pivot connection. For the first starboard protrusion, the assembly comprises a second rod, the first end of which is fixed to the first starboard protrusion by a ninth pivot connection.

[0024] The port and starboard fittings include a second port protrusion and a second starboard protrusion, respectively, which extend vertically in a plane substantially perpendicular to the vertical midplane. The second protrusion extends in a lower section of the fitting, the second starboard protrusion is fixed to the second end of the first rod by a tenth pivot connection, and the second port protrusion is fixed to the second end of the second rod by an eleventh pivot connection.

[0025] According to a specific aspect of the present invention, the eighth pivot connection portion and the ninth pivot connection portion have matching connection axes, and at least one of the tenth pivot connection portion and the eleventh pivot connection portion has a gap.

[0026] The present invention also provides an aircraft comprising a propulsion system and assembly as described above, wherein the propulsion system is fixed to a reaction machine main rod. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The above and other features of the present invention will become more apparent upon reading the following description of exemplary embodiments given with reference to the accompanying drawings, in which:

[0028] Figure 1 is a side view of an aircraft according to the present invention;

[0029] Figure 2 is a perspective view of an assembly according to one embodiment of the present invention; and

[0030] Figure 3 is partially shown Figure 2 Rear view of the components. DETAILED DESCRIPTION

[0031] Figure 1 An aircraft 10 is shown comprising a propulsion system 102, such as a turbojet or a turboprop. The propulsion system 102 is connected to a wing 104 of the aircraft 10 by means of a reaction rod 106. The wing 104 and the reaction rod 106 form an assembly 100 according to the invention, and the propulsion system 102 is fixed to the reaction rod 106 using any suitable fixing means known to a person skilled in the art, such as those disclosed in document US-A-2016 / 0221682.

[0032] In the following descriptions, position-related terms are considered to relate to the aircraft in its normal flight position, i.e. Figure 1 As depicted, the positions “front” and “rear” are considered relative to the front and rear of the propulsion system 102 and relative to the forward direction of travel F of the aircraft 10 when the propulsion system 102 is in operation.

[0033] In the following description and conventionally, X denotes the longitudinal direction of the propulsion system, which is horizontal when the aircraft is on the ground, Y denotes the lateral direction, which is horizontal when the aircraft is on the ground, and Z denotes the vertical direction, which is vertical when the aircraft is on the ground, these three directions X, Y and Z being orthogonal to each other.

[0034] The reactor main shaft 106 and the propulsion system 102 , which in this case is a turboprop engine with a propeller 102 a , but which could be of the twin-flow turbofan type with a nacelle, have a vertical median plane XZ.

[0035] Figure 2 An assembly 100 according to the invention is shown. The reaction bar 106 comprises a rigid structure forming a caisson, also called main structure 202. The main structure 202, here shown in section along a plane parallel to the ZY plane, is conventionally formed by an upper longitudinal beam 204, a lower longitudinal beam 206 and two side panels, starboard and port, connecting the two longitudinal beams 204 and 206.

[0036] In this example, the shape of the main structure 202 is configured so that the reaction rod 106 has a substantially rectangular rear section 203 located at the rear end of the reaction rod 106 in the travel direction F.

[0037] The wing structure 104 comprises a front longitudinal beam 210, an upper surface panel 214 and a lower surface panel 216, both of which are fixed to the front longitudinal beam 210 and extend substantially in a horizontal plane XY. Of course, in order to ensure the rigidity of the wing, its structure comprises other elements (not shown), such as ribs distributed between the upper surface panel 214 and the lower surface panel 216.

[0038] In this case, the front longitudinal beam 210 adopts Figure 2 and Figure 3 The profile form of the middle inverted Z-shaped step shape has a substantially horizontal upper wing 210a (also called a high section) and a lower wing 210b (also called a low section), and a central section 210c extending vertically substantially perpendicular to the middle plane and substantially parallel to the plane YZ. The upper surface panel 214 is fixed above the upper wing 210a of the longitudinal beam 210, and the lower surface panel 216 is fixed below the lower wing 210b of the longitudinal beam 210. The fixing of the front longitudinal beam 210 to the panels 214 and 216 is achieved by any suitable means, such as welding parts, bolts, etc. Therefore, the upper surface panel 214 is fixed to the upper section of the front longitudinal beam 210, and the lower surface panel 216 is fixed to the lower section of the front longitudinal beam 210. The central section 210c is located at a horizontal position of the leading edge 104 of the wing.

[0039] To allow the reaction rod 106 to be fixed to the wing 104, the front longitudinal beam 210 carries a first fitting 211a, called the central fitting, fixed at the level of the vertical median plane XZ, more specifically, in this example, at the central section 210c of the front longitudinal beam 210. The lower surface panel 216 carries a starboard fitting 212 and a port fitting 213 fixed to the outer side of the lower surface panel 216. In this example, the starboard fitting 212 and the port fitting 213 are fixed at the level of the lower section 210b of the front longitudinal beam 210, substantially vertically aligned.

[0040] The assembly 100 comprises a first starboard locking beam 282 fixed to the starboard fitting 212 by means of a first pivot connection 292a and a second pivot connection 292c, the axis of rotation of which is substantially horizontal. More precisely, the axes of the connections 292a and 292c extend substantially perpendicular to the median plane XZ.

[0041] The assembly also comprises a first port lock beam 283 fixed to the port fitting 213 by means of a fourth pivot connection 293a and a fifth pivot connection 293c, the axis of rotation of which is substantially horizontal. More precisely, the axes of the connections 293a and 293c extend substantially perpendicularly to the median plane XZ.

[0042] In order to allow the reaction machine main rod 106 to be fixed to the wing 104, the rear section 203 of the main structure 202 includes a first fixing ear 211b, which extends to the rear and is in a horizontal position of the vertical middle plane XZ. More precisely, the first fixing ear 211b extends at the top of the rear section 203 and is positioned opposite to the first accessory 211a. The first fixing ear 211b is fixed to the first accessory 211a by a seventh connection 211c, which has at least one degree of freedom to rotate around a vertical axis extending parallel to the vertical axis Z. The seventh connection 211c can be in the form of a pivot connection or a pivot sliding connection. In the embodiment of the invention proposed here, the first accessory 211a takes the form of a recessed ear and the first fixing ear 211b takes the form of a lug inserted into the recessed ear.

[0043] This fixing point between the reaction rod 106 and the wing 104 absorbs axial forces along the X axis and lateral forces along the Y axis. This fixing point also absorbs moments about the Y axis.

[0044] The rear section 203 further includes a starboard fixing ear 272 and a port fixing ear 273 extending to the rear of the rear section 203. More specifically, in this example, the starboard fixing ear 272 and the port fixing ear 273 extend at the lower section and both sides of the rear section 203.

[0045] The starboard fixing ear 272 is fixed to the starboard locking beam 282 by a third pivot connection 292e about a substantially horizontal axis, and the port fixing ear 273 is fixed to the port locking beam 283 by a sixth pivot connection 293e about a horizontal axis. More precisely, the axes of the third pivot connection 292e and the sixth pivot connection 293e extend substantially perpendicular to the median plane XZ, that is, substantially parallel to the transverse axis Y. Furthermore, the axes of the connections 292e and 293e may extend substantially coaxially.

[0046] Thus, the two fixing points of the starboard fixing lug 272 and the port fixing lug 273, located on both sides of the lower longitudinal beam 206 of the main structure 202, are connected to the starboard fitting 212 and the port fitting 213, which are integral with the wing 104, through two first starboard locking beams 282 and port locking beams 283 with three fixing points (i.e. the associated pivot connection mentioned above). In this way, the transmission of forces from the propulsion system 102 and through the reaction rod 106 towards the wing 104 is optimized. More precisely, these different fixing points of the reaction rod 106 to the wing 104 ensure the transmission of vertical forces (along the Z axis) and axial forces (along the X axis). These fixing points also absorb the moments about the X and Z axes. This particular embodiment also allows to accurately determine the path of the forces through the reaction rod 106 towards the wing 104.

[0047] In this example, the first starboard lock beam 282 and the first port lock beam 283, the starboard ear 282 and the port ear 283, and the starboard fitting 212 and the port fitting 213 each have a hole into which the shaft is inserted to form the pivot connection parts 292a, 292c, 292e and 293a, 293c, 293e.

[0048] In this example, the first starboard lock beam 282 and the first port lock beam 283 have a substantially triangular shape. Therefore, the first pivot connection portion 292a and the second pivot connection portion 292c are respectively arranged in the first high angle portion 292b and the second high angle portion 292d of the first starboard lock beam, and the third pivot connection portion 292e is arranged in the third low angle portion 292f of the first port lock beam 282. Similarly, the fourth pivot connection portion 293a and the fifth pivot connection portion 293c are respectively arranged in the fourth high angle portion 293b and the fifth high angle portion 293d of the first port lock beam 213, and the sixth pivot connection portion 293e is arranged in the sixth low angle portion 293f of the first port lock beam 283.

[0049] The implementation of a triangular lock beam specifically allows the assembly 100 to be compatible with the use of an aerodynamically shaped fairing covering at least a portion of the reactor mast 106 .

[0050] According to this embodiment of the present invention, the assembly 100 includes a second starboard lock beam 282', which extends substantially parallel to the first starboard lock beam 282, and is fixed to the starboard fitting 212 through the first connection portion 292a and the second connection portion 292c, and is fixed to the starboard fixing plate through the third connection portion 292e. Similarly, the assembly 100 includes a second port lock beam 283', which extends substantially parallel to the first port lock beam 283, and is fixed to the port fitting 213 through the fourth connection portion 293a and the fifth connection portion 293c, and is fixed to the port fixing plate 273 through the sixth connection portion 293e. In addition, the first starboard lock beam 282 and the second starboard lock beam 282' enclose the starboard fitting 212 and the starboard fixing plate 272, while the first port lock beam 283 and the second port lock beam 283' enclose the port fitting 213 and the port fixing plate 273.

[0051] Thus, each of the starboard fitting 212 and the port fitting 213 is connected to the starboard fixing ear 272 and the port fixing ear 273 respectively by two locking beams 282, 282' and 283, 283'.

[0052] The doubling of the starboard and port lock beams allows doubling the paths taken by the forces transmitted from the propulsion system 102 to the wing 104. This also allows ensuring the continuity of force transmission in the event of a break in one of the lock beams or the fixing point of these lock beams at the horizontal position of the reaction rod 106 or the wing 104.

[0053] In this example, the first starboard lock beam 282 and the second starboard lock beam 282' are substantially identical. The same applies to the first port lock beam 283 and the second port lock beam 283'. However, it is conceivable to provide different shapes for the first and second lock beams.

[0054] According to the present embodiment, each lock beam 282, 282', 283, 283' comprises two plates 282a, 282a', 282b, 282b', 283a, 283a', 283b, 283b', juxtaposed and fixed to each other. More specifically, the first starboard lock beam 282 comprises two plates 282a and 282b, the second starboard lock beam 282' comprises two plates 282a' and 282b', the first port lock beam 283 comprises two plates 283a and 283b, and the second port lock beam 283' comprises two plates 283a' and 283b'. Preferably, the plates of each lock beam are identical.

[0055] The embodiment of two plates juxtaposed and fixed to each other to form each locking beam makes it possible to multiply the path taken by the forces across the propulsion system 102 towards the wing 104 and ensure the continuity of the force transmission in the event of a rupture of one of the plates of each locking beam or one of the fixing points of these plates. According to this embodiment, the starboard fitting 212 and the port fitting 213 have a substantially T-shaped cross section, in which the horizontal section is fixed to the lower section 210b of the front longitudinal beam 210 and the relevant pivot connection is made in the vertical section. More specifically, the vertical section of the starboard fitting 212 includes two holes into which the shaft is inserted to form the first connection 292a and the second connection 292b, respectively.

[0056] Similarly, the vertical section of the port side fitting 213 includes two holes into which the shaft is inserted to form a fourth connection portion 293a and a fifth connection portion 292b, respectively.

[0057] Preferably, each starboard fitting 212 and each port fitting 213 are respectively composed of two elements 212a, 212b and 213a, 213b having a substantially Γ-shaped cross section. The two elements of each fitting are integral with each other. Specifically, the two elements of each fitting are fixed to each other by vertical sections of Γ, which together form the vertical section of the T of the fitting, while the horizontal sections of these Γ-shaped elements are arranged opposite to each other and together form the horizontal section of the T of the fitting.

[0058] The embodiment of two elements fixed to each other to form each fitting allows multiplication of the paths taken by the forces transmitted from the propulsion system 102 to the wing 104 and ensures continuity of force transmission in the event of a rupture of one of the elements of each fitting.

[0059] According to the present embodiment, the first fixing ear 211b includes two sub-plates 2111 and 2113 fixed to each other in parallel. In the present example, the two sub-plates 2111 and 2113 are identical. The implementation of the two sub-plates 2111 and 2113 fixed to each other to form the first fixing plate 221b allows the path taken by the force transmitted from the propulsion system 102 to the wing 104 to be multiplied, and ensures the continuity of force transmission in the event of a rupture of one of the sub-plates of the first fixing ear 211b.

[0060] According to this embodiment, the seventh connection portion 211c between the first fixing ear 211b and the first fitting 211a includes a main shaft (not shown) and a secondary shaft (not shown) extending coaxially in the main shaft. In this example, the main shaft and the secondary shaft extend parallel to the vertical axis Z.

[0061] More specifically, the first fitting 211a and the first fixing ear 211b each have a hole into which the main shaft is inserted to form the seventh pivot connection 211c. The secondary shaft is inserted into the main shaft to ensure continuity of force transmission when the main shaft is broken.

[0062] like Figure 3 As shown, which partially represents the assembly in a rear view, the assembly 100 also includes a set of two rods 275a, 275b, which can react the forces from the propulsion system 102 and can generate an oscillating motion on the reactor main rod 106. In this example, the rear section 203 of the main structure 202 includes a first port protrusion 274a and a first starboard protrusion 274b. In this example, each first protrusion 274a, 274b has an ear-like shape and extends vertically perpendicular to the side wall 208 of the main structure 202, in other words, extends in a plane perpendicular to the vertical median plane XZ. More specifically, in this example, the first protrusions 274a and 274b extend approximately to half the height of their corresponding side wall 208.

[0063] The port fitting 213 and the starboard fitting 212 carry a second port protrusion 274c and a second starboard protrusion 274d, respectively. In the present example, each second protrusion 274c, 274d also has an ear-like shape and extends vertically in a plane perpendicular to the vertical median plane XZ. In the present example, the second protrusions 274c, 274d extend over the vertical section of the T-shape of each fitting.

[0064] In this example, the first protrusion 274a and 274b are opposite to each other. Similarly, the second protrusion 274c and 274d are also opposite to each other. This group of rods 275a, 275b connects the accessories 212 and 213 to the rear section 203 of the main structure 202 in a cross manner. More specifically, the first rod 275a connects the first port protrusion 274a to the second starboard protrusion 274d, and the second rod 275b connects the first starboard protrusion 274b to the second port protrusion 274c. Therefore, the first rod 275a and the second rod 275b cross and extend substantially in two parallel planes perpendicular to the vertical middle plane XZ. The two parallel planes are slightly spaced apart to facilitate the first rod 275a and the second rod 275b to cross.

[0065] The ends of the first rod 275a are respectively coupled to the first port protrusion 274a and the second starboard protrusion 274d through the eighth pivot connection 284a and the ninth pivot connection 284b. The ends of the second rod 275b are respectively coupled to the first starboard protrusion 274b and the second port protrusion 274c through the tenth pivot connection 284c and the eleventh pivot connection 284d.

[0066] Optionally, the first rod 275a is referred to as "engaged" and the second rod 275b is referred to as "standby". This means that the connecting axis of the eighth pivot connection 284a and the ninth pivot connection 284b is adjusted, thereby reacting to the force under stress, so that the first rod 275a represents the so-called "main" force path for force transmission, with a component oriented substantially transversely in the Y direction. At least one of the tenth pivot connection 284c and the eleventh pivot connection 284d has a gap, which allows the second rod 275b to engage in the event of a rupture of the first rod 275a, so that the second rod 275b reacts to the force.

[0067] Thus, the second rod 275b represents a so-called "secondary" force path. For example, the twelfth pivot connection 284c and the thirteenth pivot connection 284d each have a connecting axis carried by the first starboard protrusion 274b and the second port protrusion 274c, respectively. At least one of the holes made at the end of the second rod 275b and cooperating with these connecting axes has, for example, an oblong shape, so that the second rod 275b is mounted with clearance at least at the level of one of the tenth pivot connection 284c and the eleventh pivot connection 284d.

Claims

1. An assembly (100) for mounting a propulsion system (102) having a vertical mid-plane (XZ) on an aircraft (10), the assembly (100) comprising: - a wing (104) having a front longitudinal beam (210) and an inner camber panel (216) fixed to a lower section (210b) of the front longitudinal beam (210), wherein the front longitudinal beam (210) carries a first fitting (211a) at the level of a vertical midplane (XZ), and wherein the inner camber panel (216) carries a starboard fitting (212) and a port fitting (213); - a reaction machine main rod (106), said reaction machine main rod comprising a main structure (202); - a first starboard locking beam (282) fixed to the starboard fitting (212) by means of a first pivot connection (292a) and a second pivot connection (292c) about an axis extending substantially perpendicular to the median plane (XZ); - a first port lock beam (283) fixed to the port fitting (213) by means of a fourth pivot connection (293a) and a fifth pivot connection (293c) about an axis extending substantially perpendicular to the median plane (XZ); The rear portion (203) of the main structure (202) comprises a first fixing ear (211b) extending rearwards and at the level of the vertical midplane (XZ), the first fixing ear (211b) being fixed to the first accessory (211a) by a seventh connection (211c), the seventh connection having at least one degree of freedom of rotation about a vertical axis, The rear portion (203) further comprises a starboard fixing ear (272) and a port fixing ear (273) extending on each side and to the rear of the rear portion (203), wherein the starboard fixing ear (272) is fixed to the first starboard locking beam (282) by a third pivot connection (292e) around an axis extending substantially perpendicular to the middle plane (XZ), and wherein the port fixing ear (273) is fixed to the first port locking beam (283) by a sixth pivot connection (293e) around an axis extending substantially perpendicular to the middle plane (XZ).

2. The assembly (100) according to claim 1, characterized in that The components also include: - a second starboard lock beam (282'), the second starboard lock beam (282') extending substantially parallel to the first starboard lock beam (282), the second starboard lock beam (282') being fixed to the starboard fitting (212) via the first pivot connection (292a) and the second pivot connection (292c), and being fixed to the starboard fixing ear (272) via the third pivot connection (292e); - a second port lock beam (283'), the second port lock beam extending substantially parallel to the first port lock beam (283), the second port lock beam (283') being fixed to the port fitting (213) via the fourth pivot connection (293a) and the fifth pivot connection (293c), and being fixed to the port fixing ear (273) via the sixth pivot connection (293e); The first starboard lock beam (282) and the second starboard lock beam (282') enclose the starboard fitting (212) and the starboard fixing ear (272), and the first port lock beam (283) and the second port lock beam (283') enclose the port fitting (213) and the port fixing ear (273).

3. The assembly (100) according to claim 2, characterized in that Each locking beam (282, 282', 283, 283') comprises two plates (282a, 282a', 282b, 282b', 283a, 283a', 283b, 283b') fixed juxtaposed to each other.

4. The assembly (100) according to claim 1, characterized in that The starboard fitting (212) and the port fitting (213) each have a substantially T-shaped cross section, wherein a horizontal portion is fixed to the lower section (210b) of the front longitudinal beam (210), and an associated pivot connection is made in the vertical section.

5. The assembly (100) according to claim 4, characterized in that Each starboard fitting (212) and each port fitting (213) is composed of two elements (212a, 212b and 213a, 213b) each having a substantially Γ-shaped cross section and being integral with each other.

6. The assembly (100) according to claim 1, characterized in that The first fixing ear (211b) comprises two sub-plates (2111, 2113) juxtaposed and fixed against each other.

7. The assembly (100) according to claim 1, characterized in that The seventh connecting portion (211c) between the first fixing ear (211b) and the first accessory (211a) comprises a main shaft and a secondary shaft extending coaxially within the main shaft.

8. The assembly (100) according to claim 1, characterized in that The rear portion (203) comprises a first port protrusion (274a) and a first starboard protrusion (274b) extending vertically in a plane substantially perpendicular to the vertical middle plane (XZ), the first port protrusion (274a) and the first starboard protrusion (274b) being arranged on both sides of the main structure (202), For the first port protrusion (274a), the assembly (100) includes a first rod (275a), a first end of the first rod being fixed to the first port protrusion (274a) via an eighth pivot connection (284a), For the first starboard protrusion (274b), the assembly (100) includes a second rod (275b), a first end of the second rod being fixed to the first starboard protrusion (274b) via a ninth pivot connection (284b), And wherein, the port side fitting (213) and the starboard side fitting (213) respectively include a second port side protrusion (274c) and a second starboard side protrusion (274d), which extend vertically in a plane substantially perpendicular to the vertical middle plane (XZ), the second port side protrusion (274c) and the second starboard side protrusion (274d) extend in the lower section of the port side fitting (213) and the starboard side fitting (213), the second starboard side protrusion (274d) is fixed to the second end of the first rod (275a) via a tenth pivot connection (284b), and the second port side protrusion (274c) is fixed to the second end of the second rod (275b) via an eleventh pivot connection (284d).

9. The assembly (100) according to claim 8, characterized in that The eighth pivot connection (284a) and the ninth pivot connection (284b) have matching connection axes, and wherein at least one of the tenth pivot connection (284c) and the eleventh pivot connection (284d) has a gap.

10. An aircraft (10) comprising a propulsion system (102) and an assembly (100) according to claim 1, wherein: The propulsion system (102) is fixed to the reactor shaft (106).

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