ASSEMBLY OF A JET POST WITH AN AIRCRAFT WING.

Abstract

ASSEMBLY OF AN AIRCRAFT WING WITH AN ENGINE PITCH The invention relates to an assembly of an engine pylon with an aircraft wing, comprising: two reinforcement elements each being fixed to the front spar of the wing and connected by a joint to a male fitting integral with the pylon, each joint comprising a pivot axis extending orthogonally to the longitudinal median plane and arranged in the extension of the upper panel of the engine pylon and between the lower and upper panels of the wing; a stability retaining assembly configured to block the movements of the engine pylon in a direction orthogonal to the longitudinal median plane; at least one rear connecting rod, arranged under the lower panel and connecting the wing to the engine pylon.

Description

Title of the invention: ASSEMBLY OF A JET MAST WITH AN AIRCRAFT WING.

[0001] The present invention relates to an assembly of a reactor mast with an aircraft wing.

[0002] Patent application EP3939891 describes an assembly of a jet pylon with an aircraft wing. According to this patent application, and with reference to [Fig. 1], the jet pylon 1 comprises a primary structure in the form of an elongated box including a first lateral planar panel 2, a second lateral planar panel 3, an upper planar panel 4 forming the upper face of the box, a lower planar panel 6 forming the lower face of the box, and a rear rib (not visible) which forms a rear face of the box. Each of the side panels 2,3 includes, at the rear face of the box, an upper extension 2a,3a and a rear extension 2b, where each extension extends in the plane of the side panel 2,3 and extends the latter upwards, beyond the upper panel 3 in the case of the upper extension 2a,3a and extends the latter rearwards, beyond the rear rib in the case of the rear extension 2b.

[0003] The assembly of this reactor mast 1 with the wing 4 is carried out by means of:

[0004] - of a first and a second pair of upper connecting rods 7,8, where the connecting rods of the first pair of upper connecting rods 7 sandwich the first side panel 2 and link the upper extension 2a of the panel to a front spar 9 of the wing 5 and extend parallel to said side panel 2, where the connecting rods of the second pair of upper connecting rods 8 sandwich the second side panel 3 and link the upper extension 3a of said side panel 3 to the front spar 9 of the wing 5 and extend parallel to said side panel 3,

[0005] - of a first and a second pair of lower connecting rods 10 (only one pair of lower connecting rods (as seen in [Fig. 1]), where the connecting rods of the first pair of lower connecting rods 10 sandwich the first side panel 2 and link the rear extension 2b of said side panel 2 to the front spar 9 of the wing 5 and extend parallel to said side panel 2, where the connecting rods of the second pair of lower connecting rods sandwich the second side panel 3 and link the rear extension of said side panel 3 to the front spar 9 of the wing 5 and extend parallel to said side panel 3, and

[0006] - of a rear connecting rod 11 which connects the rear rib of the reactor mast 1 to the wing 5, in rear of the front spar 9 of the wing 5.

[0007] Such an assembly is fully satisfactory in terms of mechanical strength for to take over the forces from a turbojet engine when it is mounted under the engine pylon. The integration of large turbojet engines requires a modification of the assembly design described above to move the engine pylon closer to the wing in order to maintain acceptable ground clearance.

[0008] The invention meets this need in whole or in part and relates to an assembly of a jet pylon with a wing, the wing having a structure comprising a front spar located at the front of the wing, a plurality of ribs extending parallel to each other and transversely to said front spar, upper and lower skin panels fixed to the wing structure and forming an upper, respectively lower, skin of the wing, a longitudinal median plane separating the jet pylon into two parts, the jet pylon having the shape of an elongated box extending along a longitudinal axis and comprising a flat upper panel forming an upper face of the box, two lateral panels arranged on either side of the longitudinal median plane, and a flat lower panel forming an lower face of the box, and a rear rib extending perpendicularly to the longitudinal median plane and forming a rear face of the box,the assembly of the engine mast to the wing including: ,

[0009] two reinforcing elements, each being pressed and fixed against a front face of the front spar and located in the extension of a web of a wing rib, each being connected by a joint to a male fitting integral with the mast, the joints being arranged on either side of the longitudinal median plane, each joint comprising a joint axis extending orthogonally to the longitudinal median plane and arranged in the extension of the upper panel of the reactor mast and between the lower surface panel and the upper surface panel;

[0010] a stability maintenance assembly, comprising a first element fixed to the front spar and linked to a second element fixed to the engine pylon, and configured to block the movements of the engine pylon relative to the wing in a direction orthogonal to the longitudinal median plane;

[0011] at least one rear connecting rod, arranged under the lower wing panel, fixed on one side to the rear rib by a first articulation axis extending orthogonally to the longitudinal median plane, and on the other side to the wing structure by means of a second articulation axis extending orthogonally to the longitudinal median plane and located behind the front spar.

[0012] 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:

[0013] [Fig-1] already discussed, is a perspective and side view of an assembly of a reactor mast with an aircraft wing according to the prior art;

[0014] [Fig.2] is a side view of an aircraft illustrating the assembly of a reactor pylon with an aircraft wing according to the invention;

[0015] [Fig.3] is a perspective view of the rear of the reactor mast intended to be assembled with a wing of the aircraft shown in [Fig.2], according to an embodiment of the invention;

[0016] [Fig.4] is a perspective view of the front of the wing with which it is intended to come assemble the reactor mast shown in [Fig.3];

[0017] [Fig.5] is a top perspective view of the reactor mast assembly presented in [Fig.3] with the front of the wing shown in [Fig.4];

[0018] [Fig.6] is a top perspective view of the assembly of a reactor mast with a wing according to another embodiment of the invention.

[0019] With reference to [Fig.2], an aircraft 100 comprises a propulsion system 101 with an unfaired fan-driven turbojet 102 fixed under a wing 103 of the aircraft by means of a reactor mast 104 assembled with the wing 103 and fixed to the latter by means of a reactor mast fixing system to the wing 105.

[0020] In the following description, and by convention, X is called the horizontal axis, Y is called the transverse axis, and Z is called the vertical axis, these three axes X, Y and Z being orthogonal to each other.

[0021] Terms relating to a position are taken with respect to the direction of advance F of the aircraft when the turbojet 102 produces a thrust.

[0022] The wing 103 comprises a structure 106 having a plurality of structural elements, including in particular a front spar 106a at the front of the wing, a rear spar 106b at the rear of the wing, and a plurality of ribs N, all extending parallel to each other and joining the two spars 106a-b to which they are attached. Each of the front and rear spars 106a-b has a beam shape and extends generally in a plane parallel to the YZ plane. The ribs N all have a streamlined shape and extend generally in planes parallel to the XZ plane. In other words, the ribs N extend transversely to the two spars 106a-b.

[0023] As is known, the wing structure 106 is covered by an upper surface panel 107e, which forms the upper outer skin of the wing, and an lower surface panel 107i, which forms the lower outer skin of the wing 103 and faces the ground. The upper and lower surface panels 107e, 107i are attached to the wing structure 106, in particular to the leading spar 106a. The upper and lower surface panels are shown only in [Fig. 2], and only a portion of them, located between two consecutive N-ribs, is visible. The portion of the upper and lower surface panels located forward of the leading spar 106a is not shown to avoid cluttering the figures.

[0024] The reactor mast 104 extends conventionally longitudinally along a longitudinal axis L, oriented generally parallel to the horizontal axis X. The longitudinal median plane V is the plane parallel to the longitudinal axis L, orthogonal to the ground (i.e. to the horizontal) and which divides the reactor mast 104 into two parts.

[0025] With reference to [Fig. 3], the reactor mast 104 is in the form of an elongated box comprising an internal structure covered with panels, including a first planar side panel 104a located on one side of the longitudinal median plane V, a second planar side panel 104b located on the other side of the longitudinal median plane V, a planar upper panel 104s which forms the upper face of the box, and a planar lower panel 104i which forms the lower face of the box and faces the ground. In a plane XZ, the upper panel 104s is oriented at an angle between 0 and 20° with respect to the longitudinal axis L.

[0026] The internal structure of the mast includes a rear rib 104n located at the rear end of the box, which extends perpendicularly to the longitudinal median plane V and closes the box to form the rear face R of the latter.

[0027] The engine pylon 104 supports the turbojet 102 (visible only in [Fig. 2]) by means of engine mounts 110a-c attached to the lower panel 104i, which may be of conventional design. These engine mounts will not be described further since they are not part of the invention.

[0028] With reference to figures 4 and 5, the system for attaching the reactor mast to the wing 105 links, on the one hand, the rear face R of the box to the front spar 106a of the wing and on the other hand, the rear face R of the box to the structure of the wing 106, behind the front spar 106a.

[0029] According to the invention, each connection between the rear face R of the box and the front longitudinal member 106a is made:

[0030] - on the one hand through two reinforcement elements SI, S2 fixed to the front longitudinal member 106a and located on either side of the longitudinal median plane V, where each reinforcement element SI, S2 is respectively connected by a joint Al, A2 to a male fitting 122,132 integral with the reactor mast 104 where each joint Al, A2 is arranged in the extension of the upper panel 104s of the reactor mast 104 and between the intrados panel 107i and the extrados panel 107e.

[0031] - on the other hand through a stability maintenance assembly 140 (visible only at [Fig.5]) arranged between the two reinforcement elements SI, S2, and configured to block the movements of the reactor mast 104 relative to the wing 103 in a direction orthogonal to the longitudinal median plane V.

[0032] Each of the reinforcement elements SI, S2 is pressed against the front face of the wing's leading spar 106a and attached to it by screwing or welding. Each reinforcement element SI, S2 extends along the entire height of the spar 106a, such that each reinforcement element SI, S2 is in contact with the upper wing panel 107e and the lower wing panel 107i. Each of the reinforcement elements SI, S2 is located in line with the web of a wing rib N 103.

[0033] A first reinforcement element SI is located in the extension of a first rib NI, and a second reinforcement element S2 is located in the extension of a second rib N2.

[0034] It should be noted that here, the first and second ribs NI, N2 are directly consecutive. Alternatively, these two ribs NI, N2 could be separated from each other by at least one other rib N.

[0035] Similarly, each of the reinforcement elements SI, S2 comprises a female connector 121, 131 with which a respective male connector 122, 132 is articulated. Each female connector 121, 131 is thus arranged between the lower surface 170i and the upper surface 107e of the wing.

[0036] A first female connector 121 is formed by a three-pronged clevis, located on the front face of the first reinforcing element SI. Among the three prongs, there are two end prongs 121a,c and a central prong 121b between the two end prongs 121a,c. The prongs 121a-c are parallel to each other, parallel to the longitudinal median plane V and all extend towards the front of the wing 103. The prongs 121a-c are located in the extension of the web of the first wing rib NI.

[0037] A second female connector 131 is formed identically to the first female connector 121, that is, by a three-pronged clevis 131a-c, located on the front face of the second reinforcing element S2. Among the three prongs 131a-c of the second reinforcing element S2, there are two end prongs 131a,c and a central prong 131b between the two end prongs 131a,c. The prongs of the second female connector 131 all extend towards the front of the wing 103 and are all parallel to the prongs of the first female connector 121. The prongs of the second female connector 131 are located in line with the web of the second wing rib N2.

[0038] Each branch of the first or second female fitting 121,131 includes a through bore T (represented only in [Fig.4]) whose bore axis is orthogonal to the longitudinal median plane V. The bores of the three branches 121a-c of the first female fitting 121 and of the three branches 131a-c of the second female fitting 131 are all coaxial, and parallel to the ground (XY plane) to allow the articulation of the reactor mast 104 to the front spar 106a.

[0039] Here, as can be seen in [Fig.2], in a case where the wing 103 has a dihedral angle, the branches of the first and second female fitting 121,131 are offset in height as can be seen in [Fig.4].

[0040] On one side of the reactor mast 104, a first male fitting 122 is located opposite the first female fitting 121, and on the second side of the reactor mast 104, a second male fitting 132 is located opposite the second female fitting 131.

[0041] Each male fitting 122,132 here takes the form of two ears 01, 02 extending parallel to each other, parallel to the longitudinal median plane V and extending longitudinally between the lower panel 104i and the upper panel 104s of the reactor mast 104 and each projecting beyond the rear rib 104n, rearward, towards the wing 103. The ears 01, 02 all extend orthogonally to the rear face R of the box, therefore to the YZ plane.

[0042] Here on each side of the longitudinal median plane V, and identically for each male fitting 122,132:

[0043] - an outermost ear 02 of each male fitting 122,132 extends into the pro the length of the side panel 104a-b of the reactor mast 104 and is made in one piece with said side panel,

[0044] - the other ear 01 is located between the outermost ear 02 and the median plane gitudinal V and is integral with the rear rib 104n, protrudes beyond the rear face R and extends towards the wing 103 parallel to the ear 02. The ear 01 is either formed integrally with the rear rib 104n, or is an added fitting, welded or screwed, to the rear rib.

[0045] This design, with two lugs 01, 02 arranged on two separate parts, allows for a double load path. Thus, a joint A1, A2 will remain operational even if one of the two lugs 01, 02 of the male fitting 122, 132 of the joint breaks.

[0046] Each of the ears 01,02 includes a through bore Tl and the through bores Tl of the ears are coaxial. Furthermore, the coaxial bores are located in the upper part of the reactor mast 104, in line with the upper panel 104s.

[0047] Here, on each side of the longitudinal median plane V, the male fitting 122,132 is inserted into a respective female fitting 121,131. More precisely, the lugs 01, 02 of the first, respectively second male fitting 122,132 are inserted between the branches 121a-c, 131a-c of the first, respectively second female fitting 121,131 with on each side of the central branch 121b,131b of said respective female fitting 121,131, a lug 01,02 inserted in the space between the central branch 121b,131b and an end branch 121a,c-131a,c.

[0048] With male fittings 122,132 inserted into the respective female fittings 121,131, here, the lateral dimension of the reactor mast 104, i.e. its dimension in the YZ plane, is determined by the gap between the first and second rib NI, N2.

[0049] The connection of the first female fitting 121 with the first male fitting 122 is ensured by the insertion of a pivot pin L1 into the bores Tl of the lugs 01, 02 of the first male fitting 122 as well as into the bores T of the arms 121a-c of the first female fitting 121.

[0050] Similarly, the connection of the second female fitting 131 with the second male fitting 132 is ensured by the insertion of a pivot pin L2, in the coaxial bores Tl of the ears 01, 02 of the second male fitting 132 as well as in the bores T of the branches 131 ac of the second female 131.

[0051] Each of the articulation axes L1, L2 is thus located in the extension of the upper panel 104s of the reactor mast 104 and between the extrados 107e and intrados 107i panels.

[0052] The joints Al, A2 allow the resumption of forces in X and Z.

[0053] Each of the articulation axes L1, L2 is immobilized in translation by any means known.

[0054] For example, where the articulation axis L1, L2 is in the form of a hollow cylindrical shaft, a screw-nut type locking system (not shown) is used. In this case, such a locking system comprises, for each of the joints A1, A2: - an end sleeve inserted into each of the through bores T of the end branches 121a,c-131a,c of the clevis; - a bearing inserted in each of the bores Tl of the two ears 01, 02; and - a screw and a nut and two flat washers.

[0055] The articulation axis L1, L2 is on the one hand fitted sliding into each of the end sleeves, and, on the other hand, fitted in force into the bearing inserted into each of the bores T1 of the two ears 01, 02 in order to allow a pivoting of the bearing relative to the clevis along a connecting axis.

[0056] On one side of the yoke, the screw is inserted into the pivot axis L1, L2, and a first flat locking washer is inserted onto the screw and interposed between the screw head and an end sleeve. On the other side of the yoke, a second flat locking washer is fitted onto the screw shank and interposed between the other end sleeve and a threaded end of the screw. A clamping nut is tightened to the specified torque on the threaded end of the screw to hold the washers against the end sleeves. The end sleeves and bearings are thus axially immobilized along the connecting axis due to the compression between the clamping nut in contact with the second locking washer and the screw head in contact with the first locking washer.

[0057] With reference to figures 3 to 5, the stability support assembly 140 is of the "spigot" type and includes a stud 141 attached to the front spar 106a and extending horizontally forward, and an oblong hole 142 made in a shoe 150 fixed to the rear rib 140n of the box, and into which the stud 141 fits.

[0058] Here, and for the purpose of redundancy to meet safety requirements, the shoe 150 is made in two identical parts, symmetrical to each other with respect to the longitudinal median plane V, and each part is screwed to the rear rib 104n.

[0059] The stability maintenance assembly 140 is disposed between the two elements of reinforcement SI, S2. Here, the stud 141 projects forward out of a base 143 having a flat face pressed and fixed against the front longitudinal member 106a.

[0060] The major axis of the oblong hole 142 is parallel to the vertical direction Z. The center and the major axis of the oblong hole 142 are in the longitudinal median plane V. The diameter of the stud 141 is such that it is free to move parallel to the vertical direction Z and it remains constrained parallel to the transverse direction Y where the width of the oblong hole 142 on the minor axis is equal to the diameter of the stud 141.

[0061] The stability maintenance assembly 140 allows the forces to be taken up in Y, that is to say in the directions orthogonal to the median plane perpendicular to V.

[0062] In the embodiment illustrated in Figures 2 and 3, the connection between the rear rib 104n and the wing structure 106 behind the front spar 106b and under the lower wing panel 107i is ensured by a pair of rear connecting rods 160a-b (visible in [Fig.2]), whose connecting rods, of straight shape, include two through bores distributed at the two ends of the connecting rod.

[0063] The pair of rear connecting rods 160a-b links the skid 150 to the wing structure 106 and each rear connecting rod 160a-b is oriented in X / Z.

[0064] The shoe 150 includes a leg 151 extending rearward and downward in the longitudinal median plane V. The leg 151 of the shoe includes a through bore, the axis of which is perpendicular to the longitudinal median plane V. The through bore is located at the free end of the leg 151. A spherical bearing (not shown) is fitted to the bore of the leg 151 of the shoe.

[0065] Particularly visible in [Fig.2], the arrangement of the elements is such that the free end of the attachment tab is located under the front wing spar 106a. Each of the rear connecting rods 160a-b thus extends under the lower wing panel 107i (as a reminder, the part of the lower wing panel 107i located in front of the front wing spar 106a is not shown in the figures).

[0066] The connection between each rear connecting rod 160a-b and the wing 103 passes through a fitting 161 which is integral (screwed or welded) with the structure of the wing 106, and fixed to the outer face of the lower wing panel 107i.

[0067] The fitting 161 is arranged here between the first and second ribs NI, N2 mentioned above. The fitting 161 has a downward-facing tab 162 extending parallel to the longitudinal median plane V. The tab 162 of the fitting 161 includes a through bore, equipped with a spherical bearing (not shown), the bore axis of which is orthogonal to the longitudinal median plane V. The thickness of the tab 162 of the fitting fixed to the wing's underside panel 108 is identical to the thickness of the tab 151 of the skid 150 fixed to the rear rib 104n of the wing box.

[0068] The rear connecting rods 160a-b sandwich, on the one hand, the lug 151 of the shoe 150 and on the other hand, the lug 162 of the fitting 161 fixed to the intrados panel 107 of the wing.

[0069] Each rear connecting rod 160a-b is articulated, at one point with the leg 151 of the shoe 150 at another point, with the leg of the fitting 161 fixed to the intrados panel 107.

[0070] The fixing of the pair of rear connecting rods 160a-b with each of the lugs 151, 162 is carried out in a similar manner and is ensured by an articulation axis Axl, Ax2 oriented perpendicularly to the longitudinal median plane V, and which is fitted into a ball bearing equipping the through bore of the respective lug 151, 162 and, on either side of this ball bearing, into a sleeve (not shown) mounted in the through bore of a rear connecting rod 160a-b.

[0071] Thus, the pair of rear connecting rods 160a-b is fixed, on the one hand to the rear rib 104n by a first articulation axis Axl extending orthogonally to the longitudinal median plane V, and, on the other hand to the wing structure 106 by means of a second articulation axis Ax2, extending orthogonally to the longitudinal median plane V and located behind the front spar 106a.

[0072] The rear connecting rods 160a-b allow the forces to be taken up mainly in X and to a lesser extent in Z.

[0073] For example, where the first and second pivot axes Axl, Ax2 are in the form of a hollow cylindrical shaft, a screw-nut type locking system (not shown) is used in each case. Such a system comprises a screw, a nut, and two flat washers. In this case, identically for each pivot axis Axl, Ax2, at the first rear connecting rod 160a, a screw is inserted into the pivot axis Axl, Ax2, and a first flat locking washer is inserted onto the screw and interposed between the screw head and an end sleeve. At the second rear connecting rod, a second flat locking washer is fitted onto the screw shank and interposed between the other end sleeve and a threaded end of the screw. A locknut is tightened to the specified torque on the threaded end of the screw to hold the washers against the end sleeves.The end sleeves and the ball joint bearing are thus axially immobilized along the connecting axis due to the compaction between the clamping nut in contact with the second locking washer and the screw head in contact with the first locking washer.

[0074] The jet engine mounting system to the wing 105 according to the invention, with the direct articulation of the box to the front spar 106a of the wing, makes it possible to obtain a compact assembly of the jet engine 104 to the wing 106. Indeed, the articulation axes L1 and L2 of the articulation of the reinforcement elements SI, S2 to the rear rib 104n of the jet engine 104 are located in the extension of the upper panel 104s of the jet engine 104 and between the lower surface panels 107i and upper surface panels 107e, that is to say in the area of ​​the leading edge of the wing, which makes it possible to maximize the ground clearance of a turbojet fixed under the jet engine 104.

[0075] The invention allows, with an equivalent turbojet engine, to increase the ground clearance by at least the length of the upper connecting rods, allowing, in patent application EP3939891, the reactor mast to be fixed to the front wing spar.

[0076] With the system for attaching the engine mast to the wing 105 according to the invention, the ground clearance of a turbojet engine attached under the engine mast 104 will be greater as the coaxial bores of the male connecting portions 121,131 are arranged close to the upper part of the front spar 106a of the mast.

[0077] An advantage of the system for attaching the reactor mast to the wing 105 according to the invention is that the primary structure of the reactor mast 104 is unique and can be commonly set up for a starboard wing or a port wing.

[0078] In another embodiment of the invention, and with reference to [Fig. 6], the stability support assembly 170 is no longer of the "spigot" type arranged between the two reinforcement elements S1, S2, but comprises a connecting rod, called the lateral connecting rod 171, linking a lateral panel of the fuselage box 104b to the forward spar 106a. The lateral panel 104b linked to the forward spar is the one facing the exterior of the aircraft. Indeed, otherwise, the lateral connecting rod could hinder the integration of systems (not shown) originating from the fuselage 100 and running to the turbojet engine 102 along the forward spar 106a.

[0079] Here, the lateral connecting rod 107 has a two-pronged yoke at each of its two ends, and each prong includes a through bore. The through bores of the two prongs located on the same end of the connecting rod are coaxial.

[0080] The connection between the lateral connecting rod 170 and the front wing spar 106a is made via a fitting 172 integral with the front wing spar 106a, screwed or welded to its front face, and positioned at a distance from both of the two reinforcing elements S1, S2. The fitting 172 has a tab extending forward and parallel to the ground. The tab has a through bore equipped with a ball bearing.

[0081] The connection between the lateral connecting rod 170 and the side panel 104b is achieved via a fitting 173 that is fixed (screwed or welded) to the side panel 104b. Here, the fitting 173 has a tab extending outwards from the housing and parallel to the ground. The tab has a through bore equipped with a spherical bearing.

[0082] The lateral connecting rod 170 is fixed to each of the lugs in a similar manner and is secured by a clevis-type connection with a vertical pivot pin. The lug of the fitting 172, 173 is inserted between two arms of the lateral connecting rod 170 and the pin is fitted into the spherical bearing fitted to the through bore of the lug and, on either side of this spherical bearing, into a sleeve (not shown) mounted in the through bore of one arm of the connecting rod.

[0083] A locking system, for example of the screw-nut type, is used to axially lock the sleeves and the bearing.

[0084] The stability maintenance assembly 170, in this embodiment with a lateral connecting rod, allows the Y-shaped forces to be taken up.

Claims

Demands

1. Assembly of a jet pylon (104) with a wing (103), the wing (103) having a structure (106) comprising a front spar (106a) located at the front of the wing (103), a plurality of ribs (N) extending parallel to each other and transversely to said front spar (106a), upper (107e) and lower (107i) wing panels attached to the wing structure (106) and forming an upper and lower skin, respectively, of the wing (103), a longitudinal median plane (V) dividing the jet pylon (104) into two parts, the jet pylon (104) having an elongated box shape extending along a longitudinal axis (L) and comprising a flat upper panel (104s) forming a top face of the box, two side panels (104a-b) arranged on either side and on the other side of the longitudinal median plane (V), and a flat lower panel (104i) forming a lower face of the box,and a rear rib (104n) extending perpendicularly to the longitudinal median plane (V) and forming a rear face (R) of the box, the assembly of the reactor mast (104) to the wing (103) comprising:, - two reinforcement elements (SI, S2), each being plated and fixed against a front face of the front spar (106a) and located in the extension of a web of a rib (NI, N2) of the wing (103), each being connected by a joint (Al, A2) to a male fitting (122,132) integral with the engine pylon (104), the joints (Al, A2) being arranged on either side of the longitudinal median plane (V), each joint (Al, A2) comprising a joint axis (Ll, L2) extending orthogonally to the longitudinal median plane (V) and arranged in the extension of the upper panel (104s) of the engine pylon (104) and between the lower surface panel (107i) and the upper surface panel (107e) of the wing (103); - a stability maintenance assembly (140,170), comprising a first element (141,172) fixed to the front spar (106a) and linked to a second element (142, 173) fixed to the engine pylon (104), and configured to block the movements of the engine pylon (104) relative to the wing (103) in a direction orthogonal to the longitudinal median plane (V); - at least one rear connecting rod (160a-b), arranged under the intrados panel (107i), fixed on one side to the rear rib (104n) by a first articulation axis (Axl) extending orthogonally to the longitudinal median plane (V), and on the other hand to the wing structure (106) by means of a second articulation axis (Ax2) extending orthogonally to the longitudinal median plane (V) and located behind the front spar (106a). characterized in that each male fitting (122, 132) takes the form of a clevis comprising two lugs (01, 02), parallel to each other, each projecting beyond the rear rib (104n) towards the rear orthogonally to the rear face (R) of the box, and each reinforcing element (SI, S2) comprises a female fitting (121, 131) taking the form of a three-pronged clevis (121a-c,131a-c) whose prongs are located on the front face of the reinforcing element and extend parallel to each other towards the reinforcing element (SI, S2), with two end prongs (121a,c-131a,c) and a central prong (121b,131b) located between the two end prongs,and where on each side of the longitudinal median plane (V), the lugs (01,02) of a male fitting (122,132) are inserted between the branches (121a-c,131a-c) of a female fitting (121,131), with on each side of the central branch of said female fitting, a lug (01, 02) inserted in the space between the central branch (121b,131b) and an end branch (121a,c-131a,c), each of the branches (121a-c,131a-c) and of the lugs (01,02) comprising a through bore (T, Tl) whose bore axis is orthogonal to the longitudinal median plane (V) and the through bores (T, Tl) are all coaxial.

2. Assembly according to claim 1, characterized in that on each side of the longitudinal median plane (V), a first ear (02), the outermost, of a male fitting (122,132) extends in the continuation of the side panel (104a-b) of the reactor mast (104) and is made in one piece with said side panel (104a-b), while a second ear (01) is located between the first ear (02) and the longitudinal median plane (V), the second ear (01) being integral with the rear rib (104n).

3. Assembly according to any one of claims 1 to 2, characterized in that a shoe (150) is fixed to the rear rib (104n) and comprises a hooking tab (151) extending in the median plane Ion- gitudinal (V), rearward and downward of the rear rib (104n), the hooking tab (151) comprising a through bore into which the first articulation axis (Axl) is inserted.

4. Assembly according to claim 3, characterized in that the assembly comprises a fitting (161) integral with the wing structure (106) and fixed to an outer face of the intrados panel (107i), the fitting (161) comprising a tab (162) oriented downwards and extending parallel to the longitudinal median plane (V), said tab (162) comprising a through bore in which the second articulation axis (Ax2) is inserted.

5. Assembly according to any one of claims 3 to 4, characterized in that the stability maintenance assembly (140) comprises a stud (141) integral with the front longitudinal member (106a) and arranged between the two reinforcement elements (SI, S2), and an oblong hole (142) made in the shoe (150) and into which the stud (141) fits, the oblong hole having a center and a major axis arranged in the longitudinal median plane (V).

6. Assembly according to any one of claims 1 to 4, characterized in that the stability maintenance assembly (170) comprises a connecting rod (171) linking a first fitting (173) integral with a side panel (104b) of the reactor mast (104) to a second fitting (172) integral with the front spar (106a).