ARRANGEMENT FOR AN AIRCRAFT WITH ONE WING AND ONE BEAM PROPULUMN PYLON FOR COUPLING A PROPULUMN SYSTEM TO THE WING

Description

TECHNICAL FIELD

[0001] The present invention relates to an assembly for an aircraft comprising a wing and a jet engine mast for coupling a propulsion system to the wing, as well as an aircraft comprising a propulsion system and such an assembly for coupling the propulsion system to the wing. PREVIOUS STATE OF THE ART

[0002] Typically, an aircraft propulsion system includes, for example, a turbojet engine attached to a wing by means of an engine pylon. The engine pylon generally consists of a primary structure made up of a box girder consisting of an upper spar, a lower spar, and two side panels connecting the two spars, as well as internal ribs distributed along the box girder.

[0003] The turbofan engine is attached beneath the engine pylon by means of engine mounts which typically include, at the front, a forward engine mount, at the rear, a rear engine mount, and between the forward and rear engine mounts, a thrust-absorbing assembly comprising thrust rods fixed between the turbofan engine and the primary structure of the pylon, to absorb the thrust forces generated by the turbofan engine. The engine pylon is further attached to the wing structure by means of fittings through which the forces from the turbofan engine are transmitted to the wing structure.

[0004] Documents US4560122, US2022 / 194610, and FR3044297 describe such solutions for attaching a jet pylon to a wing. Specifically, document US4560122 includes an assembly with a wing having a forward spar and an underside panel attached to a lower portion of the forward spar, where the forward spar carries a first fitting and the underside panel carries a starboard and a port fitting. The assembly also includes a jet pylon having a primary structure, a starboard shackle attached to the starboard fitting, and a port shackle attached to the port fitting. The primary structure includes a first mounting bracket attached to the first fitting by a pivot joint, as well as a starboard mounting bracket attached by a pivot joint to the starboard shackle and a port mounting bracket attached by a pivot joint to the port shackle.Although the current installations are satisfactory, it is necessary to provide an installation where the transfer of forces is improved and where safety is improved, for example in the event of a breakage of a component of the fixing. DESCRIPTION OF THE INVENTION

[0005] An object of the present invention is to provide an assembly for an aircraft comprising a wing and a jet engine mast for coupling a propulsion system to the wing and which includes means of attachment to the wing which ensure an improved transfer of forces to the wing structure while also ensuring the transmission of these forces in the event of failure of a fastening element.

[0006] To this end, an assembly is proposed for mounting on an aircraft a propulsion system having a vertical median plane, said assembly comprising: a wing with a front spar and an underside panel fixed to a lower part of said front spar, where the front spar has a first fitting at the level of the vertical median plane and where said underside panel has a starboard fitting and a port fitting, a reactor mast comprising a primary structure, a first starboard shackle fixed to said starboard fitting by a first and a second pivot linkage about an axis extending globally perpendicular to the median plane, a first port shackle fixed to said port fitting by a fourth and a fifth pivot linkage about an axis extending globally perpendicular to the median plane.

[0007] A rear portion of said primary structure includes a first fixing bracket extending to the rear and at the level of the vertical median plane, said first fixing bracket being fixed to said first fitting by a seventh link having at least one degree of freedom in rotation around an axis extending globally parallel to the median plane.

[0008] The rear section also includes a starboard fixing clevis and a port fixing clevis extending on either side and to the rear of said rear section.

[0009] The starboard shackle is fixed by a third pivot joint to the first starboard shackle about an axis extending generally perpendicular to the median plane, and the port shackle is fixed by a sixth pivot joint to the first port shackle about an axis extending generally perpendicular to the median plane. Advantageously, the assembly further comprises: A second starboard shackle extending generally parallel to the first starboard shackle, said second starboard shackle being attached to said starboard fitting by said first and second connections and to said starboard shackle by said third connection; a second port shackle extending generally parallel to said first port shackle, said second port shackle being attached to said port fitting by said fourth and fifth connections and to said port fixing shackle by said sixth connection. Said first and second starboard shackles enclose said starboard fitting and said starboard fixing shackle, while said first and second port shackles enclose said port fitting and said port fixing shackle.

[0010] According to a particular aspect of the invention, each shackle comprises two plates joined and fixed against each other.

[0011] According to another particular aspect of the invention, said starboard and port fittings have an overall T-shaped section with a horizontal part fixed to the lower part of said forward spar and a vertical part in which the associated pivot connections are made.

[0012] According to yet another particular aspect of the invention, each starboard and port fitting consists of two elements having a cross-section generally in Γ and being joined together.

[0013] According to a particular aspect of the invention, said first fixing screed comprises two sub-screeds joined and fixed against each other.

[0014] According to a particular aspect of the invention, the seventh connection between said first fixing clevis and said first fitting comprises a main axis and a secondary axis extending coaxially and inside said main axis.

[0015] According to a particular aspect of the invention, said aft portion comprises a first port protrusion and a first starboard protrusion extending vertically in a plane generally perpendicular to the vertical median plane, said first protrusions being arranged on either side of said primary structure. For the first port protrusion, the assembly comprises a first connecting rod, the first end of which is fixed to said first protrusion by an eighth pivot joint. For the first starboard protrusion, the assembly comprises a second connecting rod, the first end of which is fixed to said first starboard protrusion by a ninth pivot joint.

[0016] The port and starboard fittings each have a second port and a second starboard projection extending vertically in a plane generally perpendicular to the vertical median plane. These second projections extend along the lower part of the fittings, the second starboard projection being fixed to a second end of the first connecting rod by a tenth pivot joint, and the second port projection being fixed to a second end of the second connecting rod by an eleventh pivot joint.

[0017] According to a particular aspect of the invention, said eighth and ninth pivot links have an adjusted link axis and at least one of said tenth and eleventh pivot links has play.

[0018] The invention also proposes an aircraft comprising a propulsion system and an assembly as described above, where the propulsion system is attached to the reactor mast. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The features of the invention mentioned above, as well as others, will become clearer upon reading the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which: [ Fig. 1 ] is a side view of an aircraft according to the invention; [ Fig. 2 ] is a perspective view of an assembly according to an embodiment of the invention; and [ Fig. 3 ] is a rear view partially illustrating the entire Fig. 2 . DETAILED DESCRIPTION OF A METHOD OF IMPLEMENTATION

[0020] There Fig. 1 The figure shows an aircraft 10 comprising a propulsion system 102, for example of the turbojet or turboprop type. The propulsion system 102 is connected to a wing 104 of the aircraft 10 by means of a jet engine pylon 106. The wing 104 and the jet engine pylon 106 form an assembly 100 according to the invention, and the propulsion system 102 is attached to the jet engine pylon 106 by any suitable fastening means known to those skilled in the art, such as those disclosed in US-A-2016 / 0221682.

[0021] In the following description, terms relating to a position are taken with reference to an aircraft in its normal flight position, that is, as it is represented on the Fig. 1 and the "forward" and "rear" positions are taken with respect to the front and rear of the propulsion system 102 and with respect to the forward direction F of the aircraft 10 when the propulsion system 102 is operating.

[0022] In the following description, and by convention, X is called the longitudinal direction of the propulsion system which is horizontal when the aircraft is on the ground, Y is called the transverse direction which is horizontal when the aircraft is on the ground, and Z is called 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.

[0023] The reactor mast 106 and the propulsion system 102 have a vertical midplane XZ and the propulsion system 102 is here a turboprop with a propeller 102a, but it could be of the turbofan type with a nacelle.

[0024] There Fig. 2 Figure 100 shows the assembly according to the invention. The reactor mast 106 includes a rigid structure forming a box and also called the primary structure 202. The primary structure 202, illustrated here in section along a plane parallel to the ZY plane, is conventionally formed of an upper spar 204, a lower spar 206 and two starboard and port side panels connecting the two spars 204 and 206.

[0025] The shape of the primary structure 202 is in this example configured so that the reactor mast 106 has a rear part 203 substantially rectangular, located at the rear end of the reactor mast 106 along the direction of advancement F.

[0026] The wing structure 104 comprises a leading edge spar 210, an upper wing panel 214, and an lower wing panel 216, both of which are attached to the leading edge spar 210 and extend generally in horizontal XY planes. Of course, to ensure the wing's rigidity, its structure includes other elements (not shown) such as ribs distributed between the upper wing panel 214 and the lower wing panel 216.

[0027] The front spar 210 here takes the form of a profile shaped like an inverted Z-step on the Figs. 2 And 3The wing consists of an upper wing 210a (also called the upper section) and a lower wing 210b (also called the lower section), which are generally horizontal, and a central section 210c, which is generally perpendicular to the median plane and extends generally vertically parallel to the YZ plane. The upper wing panel 214 is attached above the upper wing 210a to the spar 210, and the lower wing panel 216 is attached below the lower wing 210b to the spar 210. The attachment of the front spar 210 to the panels 214 and 216 is achieved by any suitable means, such as welding, bolting, etc. The upper surface panel 214 is thus fixed to the upper part of the front spar 210 and the lower surface panel 216 is fixed to the lower part of the front spar 210. The central part 210c is at the level of the leading edge of the wing 104.

[0028] To allow the attachment of the reactor pylon 106 to the wing 104, the forward spar 210 carries a first fitting 211a, called the central fitting, fixed at the level of the vertical median plane XZ and more specifically here to the central part 210c of the forward spar 210. The lower wing panel 216 carries a starboard fitting 212 and a port fitting 213 which are fixed to the outer face of the lower wing panel 216. In this example, the starboard fittings 212 and port fittings 213 are fixed at the level, that is to say generally in the vertical alignment, of the lower part 210b of the forward spar 210.

[0029] Assembly 100 comprises a first starboard shackle 282 fixed to the starboard fitting 212 by a first 292a and a second 292c pivot joints whose axis of rotation is generally horizontal. More precisely, the axes of the joints 292a and 292c extend generally perpendicularly to the median plane XZ.

[0030] The assembly also includes a first port shackle 283 fixed to the port fitting 213 by a fourth 293a and a fifth 293c pivot joints about an axis whose axis of rotation is generally horizontal. More precisely, the axes of the joints 293a and 293c extend generally perpendicularly to the median plane (XZ).

[0031] To allow the attachment of the engine pylon 106 to the wing 104, the rear portion 203 of the primary structure 202 includes a first attachment bracket 211b that extends rearward and at the level of the vertical median plane XZ. More precisely, the first attachment bracket 211b extends across the top of the rear portion 203 and is located opposite the first fitting 211a. The first attachment bracket 211b is fixed to the first fitting 211a by a seventh link 211c having at least one degree of freedom in rotation about a vertical axis extending parallel to the vertical axis Z. The seventh link 211c may be in the form of a pivot joint or a pivot-sliding joint. In the embodiment of the invention presented here, the first fitting 211a takes the form of a female clevis and the first fixing clevis 211b takes the form of a male clevis inserted into the female clevis.

[0032] This attachment point between the reactor mast 106 and the wing 104 allows the axial forces to be absorbed along the X-axis and the lateral forces along the Y-axis. This attachment point also allows the moment to be absorbed around the Y-axis.

[0033] The rear part 203 also includes a starboard fixing clevis 272 and a port fixing clevis 273 which extend to the rear of the rear part 203. More particularly here, the starboard fixing clevises 272 and port 273 extend in the lower part and on either side of said rear part 203.

[0034] The starboard shackle 272 is attached by a third pivot joint 292e to the starboard shackle 282 around a generally horizontal axis, and the port shackle 273 is attached by a sixth pivot joint 293e to the port shackle 283 around a horizontal axis. More precisely, the axes of the third and sixth pivot joints 292e and 293e extend generally perpendicularly to the median plane XZ, that is, generally parallel to the transverse axis Y. The axes of the joints 292e and 293e may also extend generally coaxially.

[0035] Thus, the two attachment points of the starboard 272 and port 273 clevises, located on either side of the lower spar 206 of the primary structure 202, are connected to the starboard 212 and port 213 fittings attached to the wing 104 by two shackles, starboard 282 and port 283, each with three attachment points (namely, the associated pivot joints described previously). In this way, the transmission of forces from the propulsion system 102, passing through the engine pylon 106 to the wing 104, is optimized. More precisely, these various attachment points of the engine pylon 106 to the wing 104 ensure the transfer of vertical forces (along the Z-axis) and axial forces (along the X-axis). These attachment points also allow for the absorption of moments about the X and Z axes.This particular implementation also makes it possible to determine precisely the paths taken by the forces through the reactor mast 106 to the wing 104.

[0036] In this example, the first starboard shackles 282 and port 283, the starboard shackle 282 and port 283 and the starboard fittings 212 and port 213 each have a bore into which a pin is threaded so as to form the pivot links 292a, 292c, 292e and 293a, 293c, 293e.

[0037] In this example, the first starboard shackle 282 and the first port shackle 283 have an overall triangular shape. Thus, the first 292a and second 292c pivot links are arranged respectively in the first 292b and second 292d upper corners of the first starboard shackle, and the third pivot link 292e is arranged in the third lower corner 292f of the first starboard shackle 282. Similarly, the fourth 293a and fifth 293c pivot links are arranged respectively in the fourth 293b and fifth 293d upper corners of the first port shackle 213, and the sixth pivot link 293e is arranged in the sixth lower corner 293f of the first port shackle 283.

[0038] The implementation of triangular shackles makes it possible in particular to make the assembly 100 compatible with the use of an aerodynamically shaped fairing covering at least part of the reactor mast 106.

[0039] According to this embodiment of the invention, assembly 100 comprises a second starboard shackle 282' which extends generally parallel to the first starboard shackle 282 and which is fixed to the starboard fitting 212 by the first 292a and second 292c connections and to the starboard fixing clevis by the third connection 292e. Similarly, assembly 100 comprises a second port shackle 283' which extends generally parallel to the first port shackle 283 and which is fixed to the port fitting 213 by the fourth 293a and fifth 293c connections and to the port fixing clevis 273 by said sixth connection 293e. In addition, the first 282 and second 282' starboard shackles enclose the starboard fitting 212 and the starboard fixing clevis 272 while the first 283 and second 283' port shackles enclose the port fitting 213 and the port fixing clevis 273.

[0040] Thus, each starboard fitting 212 and port fitting 213 is connected respectively to the starboard fixing clevis 272 and to the port fixing clevis 273 by two shackles, respectively 282, 282' and 283, 283'.

[0041] Doubling the starboard and port shackles multiplies the paths taken by the forces passing from the propulsion system 102 to the wing 104. This also ensures continuity of force transfers in the event of breakage of one of the shackles or of a point of attachment of these shackles at the level of the reactor mast 106 or the wing 104.

[0042] In this example, the first and second starboard shackles 282 and 282' are essentially identical. The same is true for the first and second port shackles 283 and 283'. However, it is possible to use different shapes for the first and second shackles.

[0043] According to this embodiment, each shackle 282, 282', 283, 283' comprises two plates 282a, 282a', 282b, 282b', 283a, 283a', 283b, 283b' joined and fixed against each other. More specifically, the first starboard shackle 282 comprises two plates 282a and 282b, the second starboard shackle 282' comprises two plates 282a' and 282b', the first port shackle 283 comprises two plates 283a and 283b, and the second port shackle 283' comprises two plates 283a' and 283b'. Preferably, the plates of each shackle are identical.

[0044] The implementation of two plates joined and fixed to each other to form each shackle makes it possible to multiply the paths taken by the forces passing from the propulsion system 102 to the wing 104 and to ensure continuity of force transfers in the event of a break in one of the plates of each shackle or in a point of attachment of these plates.

[0045] According to this embodiment, the starboard 212 and port 213 fittings have a generally T-shaped cross-section with a horizontal portion fixed to the lower part 210b of the forward spar 210 and a vertical portion in which the associated pivot joints are formed. More specifically, the vertical portion of the starboard fitting 212 has two bores into which pins are inserted to form the first 292a and second 292b joints, respectively.

[0046] Similarly, the vertical part of the port fitting 213 has two bores into which pins are threaded to form the fourth 293a and the fifth 293b links respectively.

[0047] Preferably, each starboard fitting 212 and port fitting 213 consists of two elements, respectively 212a, 212b and 213a, 213b, having an overall cross-section in the shape of Γ. The two elements of each fitting are joined together. More precisely, the joining of the two elements of each fitting is achieved by the vertical portions of Γ which together form the vertical portion of the T-shaped section of the fitting, while the horizontal portions of these Γ-shaped elements are arranged opposite each other and together form the horizontal portion of the T-shaped section of the fitting.

[0048] The implementation of two elements fixed to each other to form each fitting makes it possible to multiply the paths taken by the forces passing from the propulsion system 102 to the wing 104 and to ensure continuity of force transfers in the event of failure of one of the elements of each fitting.

[0049] According to this embodiment, the first mounting bracket 211b comprises two sub-brackets 2111 and 2113 joined and fixed to each other. In this example, the two sub-brackets 2111 and 2113 are identical. The use of two sub-brackets 2111 and 2113 fixed to each other to form the first mounting bracket 221b makes it possible to multiply the paths taken by the forces transmitted from the propulsion system 102 to the wing 104 and to ensure continuity of force transfers in the event of failure of one of the sub-brackets of the first mounting bracket 211b.

[0050] According to this embodiment, the seventh connection 211c between the first fixing bracket 211b and the first fitting 211a comprises a main axis (not shown) and a secondary axis (not shown) extending coaxially and inside the main axis. In this example, the main axis and the secondary axis extend parallel to the vertical axis Z.

[0051] More specifically, the first fitting 211a and the first fixing clevis 211b each have a bore into which the main axis is threaded to form the seventh pivot joint 211c. The secondary axis is threaded into the main axis so as to ensure continuity of force transfers in the event of failure of the main axis.

[0052] As illustrated on the Fig. 3Figure 100, which partially represents the assembly from a rear view, also includes a set of two connecting rods 275a and 275b designed to react to forces from the propulsion system 102 that could generate an oscillating movement on the reactor mast 106. In this example, the rear portion 203 of the primary structure 202 has a first port-side projection 274a and a first starboard-side projection 274b. In this example, each first projection 274a and 274b is ear-shaped and extends vertically and perpendicularly to the side walls 208 of the primary structure 202, that is, in a plane perpendicular to the vertical median plane XZ. More precisely, the first projections 274a and 274b extend approximately half the height of their respective side walls 208.

[0053] The port fittings 213 and starboard fittings 212 each have a second port protrusion 274c and a second starboard protrusion 274d, respectively. In this 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 this example, the second protrusions 274c, 274d extend along the vertical portion of the T-shaped section of each fitting.

[0054] In this example, the first projections 274a and 274b face each other. Similarly, the second projections 274c and 274d also face each other. The set of connecting rods 275a, 275b crosswise connects the fittings 212 and 213 to the rear part 203 of the primary structure 202. More precisely, the first connecting rod 275a connects the first port projection 274a to the second starboard projection 274d, while the second connecting rod 275b connects the first starboard projection 274b to the second port projection 274c. The first 275a and second 275b connecting rods are therefore crossed and extend substantially in two parallel planes perpendicular to the vertical median plane XZ. The two parallel planes are slightly spaced apart to facilitate the crossing of the first 275a and second 275b connecting rods.

[0055] The ends of the first connecting rod 275a are secured to the first port extension 274a and the second starboard extension 274d respectively by an eighth 284a and a ninth 284b pivot joint. The ends of the second connecting rod 275b are secured to the first starboard extension 274b and the second port extension 274c respectively by a tenth 284c and an eleventh 284d pivot joint. Optionally, the first connecting rod 275a is said to be "engaged" while the second connecting rod 275b is said to be "standby". This means that the connecting axes of the eighth 284a and ninth 284b pivot links are adjusted and therefore react to the stresses under load, so that the first connecting rod 275a represents the so-called "main" force path for the transmission of forces having a component substantially oriented along the transverse direction Y.At least one of the tenth 284c and eleventh 284d pivot links has a play which allows in case of breakage of the first connecting rod 275a, to engage the second connecting rod 275b so that it is the second connecting rod 275b which reacts to the forces.

[0056] The second connecting rod 275b thus represents the so-called "secondary" load path. For example, the twelfth 284c and thirteenth 284d pivot joints each have a connecting axis carried respectively by the first starboard projection 274b and by the second port projection 274c. At least one of the bores provided at the ends of the second connecting rod 275b and cooperating with these connecting axes has, for example, an oblong shape so that the second connecting rod 275b is mounted with clearance at the level of at least one of the tenth 284c and eleventh 284d pivot joints.

Claims

1. Assembly (100) for mounting on an aircraft (10) a propulsion system (102) having a vertical median plane (XZ), said assembly (100) comprising: - a wing (104) with a front longeron (210) and an intrados panel (216) fixed to a lower section (210b) of said front longeron (210), in which the front longeron (210) carries a first fitting (211a) and in which said intrados panel (216) carries a starboard fitting (212) and a port fitting (213), - a reactor mast (106) comprising a primary structure (202), - a first starboard shackle (282) fixed to said starboard fitting (212), - a first port shackle (283) fixed to said port fitting (213), a rear part (203) of said primary structure (202) comprising a first fixing lug (211b) extending rearwardly and at the vertical median plane (XZ) level, said first fixing lug (211b) being fixed to said first fitting (211a) by a seventh connection (211c) having at least one degree of freedom in rotation about a vertical axis, said rear part (203) also comprising a starboard fixing lug (272) and a port fixing lug (273) extending on either side and to the rear of said rear part (203), wherein said starboard fixing lug (272) is fixed by a third pivot connection (292e) to said first starboard shackle (282) about an axis extending generally perpendicularly to the median plane (XZ) and wherein said port fixing lug (273) is fixed by a sixth pivot connection (293e) to said first port shackle (283) about an axis extending generally perpendicularly to the median plane (XZ) characterized in that said first fitting (211a) is disposed at the vertical median plane level (XZ), in that said first starboard shackle (282) fixed to said starboard fitting (212) by a first pivot connection (292a) and a second pivot connection (292c) about an axis extending generally perpendicularly to the median plane (XZ), and in that said first port shackle (283) fixed to said port fitting (213) by a fourth pivot connection (293a) and a fifth pivot connection (293c) about an axis extending generally perpendicularly to the median plane (XZ).

2. Assembly (100) according to claim 1, characterized in that it further comprises: - a second starboard shackle (282') extending generally parallel to said first starboard shackle (282), said second starboard shackle (282') being fixed to said starboard fitting (212) by said first connection (292a) and second connection (292c) and to said starboard fixing lug (272) by said third connection (292e), - a second port shackle (283') extending generally parallel to said first port shackle (283), said second port shackle (283') being fixed to said port fitting (213) by said fourth connection (293a) and fifth connection (293c) and to said port fixing lug (273) by said sixth connection (293e), wherein said first starboard shackle (282) and second starboard shackle (282') enclose said starboard fitting (212) and said starboard fixing lug (272), and wherein said first port shackle (283) and second port shackle (283') enclose said port fitting (213) and said port fixing lug (273).

3. Assembly (100) according to claim 2, characterized in that each shackle (282, 282', 283, 283') comprises two plates (282a, 282a', 282b, 282b', 283a, 283a', 283b, 283b') juxtaposed and fixed to one another.

4. Assembly (100) according to any of claims 1 to 3, characterized in that said starboard fitting (212) and port fitting (213) have a generally T-shaped section, respectively, with a horizontal part fixed to the lower section (210b) of said front longeron (210) and a vertical section in which the associated pivot connections are made.

5. Assembly (100) according to Claim 4, characterized in that each starboard fitting (212) and each port fitting (213) is made up of two elements (212a, 212b and 213a, 213b) having a generally Γ-shaped section, respectively, and being integral with one another.

6. Assembly (100) according to any of claims 1 to 5, characterized in that said first fixing lug (211b) comprises two sub-plates (2111, 2113) juxtaposed and fixed against one another.

7. Assembly (100) according to any of claims 1 to 6, characterized in that the seventh connection (211c) between said first fixing lug (211b) and said first fitting (211a) comprises a main axis and a secondary axis extending coaxially and within said main axis.

8. Assembly (100) according to any of claims 1 to 6, characterized in that said rear section (203) comprises a first port protrusion (274a) and a first starboard protrusion (274b) extending vertically in a plane generally perpendicular to the vertical median plane (XZ), said first protrusions (274a, 274b) being disposed on either side of said primary structure (202), for the first port protrusion (274a), the assembly (100) comprises a first rod (275a), a first end of which is fixed to said first port protrusion (274a) by an eighth pivot connection (284a), for the first starboard protrusion (274b), the assembly (100) comprises a second rod (275b), a first end of which is fixed to said first starboard protrusion (274b) by a ninth pivot connection (284b), and in that said port fittings (213) and starboard fittings (213) respectively comprise a second port protrusion (274c) and a second starboard protrusion (274d) extending vertically in a plane generally perpendicular to the vertical median plane (XZ), said second protrusions (274c, 274d) extending at the lower section of the fittings (212, 213), the second starboard protrusion (274d) being fixed to a second end of said first rod (275a) by a tenth pivot connection (284b) and said second port protrusion (274c) being fixed to a second end of said second rod (275b) by an eleventh pivot connection (284b).

9. Assembly (100) according to Claim 7, characterized in that said eighth pivot connection (284a) and ninth pivot connection (284b) have a fitted connection axis and in that at least one of said tenth pivot connection (284c) and eleventh pivot connection (284d) has a clearance.

10. Aircraft (10) comprising a propulsion system (102) and an assembly (100) according to any of claims 1 to 9, wherein the propulsion system (102) is fixed to the reactor mast (106).