ASSEMBLY OF AN AIRCRAFT WING WITH AN ENGINE POST
The aircraft reactor mast assembly redesign using a novel fixing system with parallel connecting rods anchored to the wing's front spar resolves obstruction issues, enabling efficient integration of pneumatic systems by maintaining conduit clearance.
Patent Information
- Application Number
- FR2023000840
- Authority / Receiving Office
- FR · FR
- Patent Type
- Utility models
- Current Assignee / Owner
- Filing Date
- 2023-01-30
- Publication Date
- 2024-12-20
- Estimated Expiration
- 2033-01-30
AI Technical Summary
Existing aircraft reactor mast assemblies obstruct the passage for pneumatic systems supplying hot air from turbojets to the cabin, necessitating a redesign that allows for unobstructed integration of these systems.
The assembly of the reactor mast to the aircraft wing involves a unique fixing system using upper and lower connecting rods that extend parallel to the wing's panels, anchored via a sole fixed to the front spar, allowing the connecting rods to be positioned outside the conduit path, thus avoiding obstruction.
This design ensures unobstructed passage for conduits supplying hot air from the turbojet to the cabin, facilitating efficient integration of pneumatic systems without compromising structural integrity.
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Abstract
Description
Title of the invention: ASSEMBLY OF AN AIRCRAFT WING WITH A ENGINE PISTON
[0001] The present invention relates to an assembly of a wing of an aircraft with a reactor mast.
[0002] Usually, for an aircraft, a propulsion assembly comprises a turbojet engine which is fixed under a wing of the aircraft by means of a reactor mast.
[0003] Patent application EP3939891 describes an assembly of a wing of an aircraft with a reactor mast under which a turbojet engine is fixed. According to this patent application, and with reference to [Fig.l], the reactor mast 1 comprises a primary structure in the form of an elongated box comprising a first 2-plane side panel, a second 3-plane side panel, an upper 4-plane panel forming the upper face of the box, a lower 6-plane panel forming the lower face of the box, and a rear rib (not visible) of trapezoidal shape which closes the box at the rear. Each of the side panels 2, 3 comprises an upper extension 2a, 3a and a rear extension 2b.Each extension of a side panel 2,3 extends in the plane of said 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 backwards, beyond the rear rib in the case of the rear extension 2b.
[0004] The assembly of this reactor mast 1 to the wing 5 is carried out by means of:
[0005] - of a first and a second pair of upper connecting rods 7,8 and where each of the upper connecting rods is a two-point connecting rod. The connecting rods of the first pair of upper connecting rods 7, extending parallel to the first side panel 2, sandwich said first side panel 2 and connect the upper extension 2a of the panel to a front spar 9 of the wing 5. The connecting rods of the second pair of upper connecting rods 8, extending parallel to said second side panel 3, sandwich the second side panel 3 and connect the upper extension 3a of said second side panel 3 to the front spar 9 of the wing 5;
[0006] - of a first and a second pair of lower connecting rods 10 (only one pair of lower balls is visible in [Fig.l]), and where each of the lower rods is a two-point rod. The rods of the first pair of lower rods 10, extending parallel to said first side panel 2, sandwich the first side panel 2 and connect the rear extension 2b of said side panel 2 to the front spar 9 of the wing 5. The rods of the second pair of lower rods, extending parallel to the second side panel 3, sandwich said second side panel 3 and connect the rear extension of said side panel 3 to the spar before 9 of wing 5,
[0007] - of a rear connecting rod 11 which connects the rear rib of the engine mast 1 to the wing 5, in rear of the front spar 9 of the wing 5.
[0008] To supply the aircraft cabin with hot air from the turbojet engine (not shown), it is customary to pass air from the engine pylon 1 to the aircraft via a duct (not shown) connected to an air system of the turbojet engine. The duct passes through the primary structure of the engine pylon 1, opening into an opening O made in the upper panel 4, running along the upper panel 4 until it reaches the leading edge of the wing forming the front end of the wing, and then traveling towards the fuselage of the aircraft, running along the front spar 9 of the wing and passing through the space defined between the leading edge of the wing and the front spar 9 of the wing. With the solution described in patent application EP393989, the upper connecting rods 7,8 extend into the space defined between the leading edge and the front spar 9 of the wing and obstruct the passage for the duct.
[0009] There is a need to find an assembly of a jet engine mast to an aircraft wing which does not have the aforementioned drawback for the integration of the pneumatic system making it possible to supply the cabin with hot air coming from the turbojet engine.
[0010] The invention meets this need in whole or in part and relates to an assembly of a wing of an aircraft with a jet engine pylon, the wing having a structure comprising a front spar located at the front of the wing, said structure being covered with an extrados panel forming an upper outer skin of the wing, a lower surface panel forming a lower outer skin of the wing, said extrados and lower surface panels being connected to each other by the front spar, the jet engine pylon having the shape of an elongated box extending lengthwise along a longitudinal axis and comprising a rear rib at the rear of said pylon, said rib forming a rear face of the box, a flat upper panel forming an upper face of the box, a longitudinal median plane separating the jet engine pylon into two parts,the engine pylon comprising a first lateral plane panel on a first side of the longitudinal median plane and forming a first side of the box and a second lateral plane panel on the other side of the longitudinal median plane and forming a second side of the box, the assembly comprising: - a first and a second pair of upper connecting rods arranged on either side of the longitudinal median plane, each of the first and second pairs and upper connecting rods connects the upper panel of the engine pylon to the front spar of the wing, extends parallel to the plane of the upper panel, the attachment of each upper connecting rod to the front spar is carried out by means of a sole plate fixed to the front spar and having an upper face in contact with the lower surface panel, the lower surface panel being sandwiched between the sole plate and the front spar, the sole plate comprising a , plate of thickness identical to that of the upper panel of the engine pylon and extending in the extension of said upper panel, a space being defined between the lower surface panel of the wing and the plate of the sole, each of the first pair and the second pair of upper connecting rods sandwiches, on the one hand, the upper panel of the pylon, and on the other hand, the plate, the connecting rods of the first pair and of the second pair of upper connecting rods all being of the same thickness less than the smallest dimension of the space between the lower surface panel of the wing and the plate of the sole; - a first and a second pair of lower connecting rods, where the lower connecting rods are two-point connecting rods, and where on one side of the engine pylon the first pair of lower connecting rods connects the first side panel to the front spar of the wing through a first fitting secured to the sole, and on the other side of the engine pylon, the second pair of lower connecting rods connects the second side panel to the front spar of the wing through a second fitting secured to the sole; - at least one rear connecting rod which connects the rear rib to the wing structure.
[0011] The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the attached drawings, among which:
[0012] [Fig. 1], already discussed, is a perspective and side view of an assembly of a reactor mast to an aircraft wing according to the prior art;
[0013] [Fig.2], is a side view of an aircraft comprising a mast assembly single-wing aircraft reactor according to the invention;
[0014] [Fig.3] is a side perspective view of an assembly of a reactor mast to an aircraft wing according to an embodiment of the invention;
[0015] [Fig.4] is a perspective view of the rear of the assembly of a reactor mast with an aircraft wing of [Fig.3].
[0016] With reference to Figures 2 to 4, an aircraft 100 with a fuselage 100a comprises a propulsion system 101 with a turbojet engine 102 fixed under a wing 103 of the aircraft through a reactor mast 104 suspended under the wing 103 and fixed to the latter by means of a fixing system 105 (shown only in Figures 3 and 4) of the reactor mast 104.
[0017] In the following description, and by convention, the horizontal axis is called X, the transverse axis is called Y, and the vertical axis is called Z, these three axes X, Y and Z being orthogonal to each other.
[0018] The terms relating to a position are taken with respect to the direction of advance F of the aircraft when the turbojet 102 produces thrust. The direction of advance F is parallel to the horizontal axis X when the aircraft is moving along the ground.
[0019] The wing 103 comprises a structure 103a comprising a plurality of structural elements, in particular a front spar 103b and ribs 106 (only one shown schematically in [Fig. 3]). The front spar 103b is generally in a plane parallel to the YZ plane and the ribs 106 are generally in planes parallel to the XZ plane. The structure of the wing 103b is covered with an extrados panel 107 which forms the upper outer skin of the wing 103, and a intrados panel 108 which forms the lower outer skin of the wing 103 facing the ground. The upper and lower surface panels 107, 108 are connected to the wing structure 103b and join at the leading edge of the wing A located at the front of the wing 103. In particular, the front spar 103b joins the lower surface panel 108 and the upper surface panel 107 of the wing.
[0020] The reactor mast 104 comprises conventionally extending 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. horizontal) and which divides the reactor mast 104 into two left and right parts.
[0021] The reactor mast 104 is in the form of an elongated box 110 comprising an internal structure covered with walls, including a first lateral panel 111 located on a first side of the longitudinal median plane V, a second lateral panel 112 located on a second side of the longitudinal median plane V, a flat upper panel 113 which forms the upper face of the box 110, and a flat lower panel 114 which forms the lower face of the box 110 and which faces the ground. In a plane XZ, the upper panel 113 is, in the example shown here, oriented at an angle of between 0 and 20° relative to the longitudinal axis L. Here, the upper panel 113 is wider than the lower panel 114, the width being defined as the dimension measured along the Y axis.
[0022] A rear rib 115 (visible in transparency in [Fig.4]), located at the rear end of the box 110, and which extends perpendicular to the longitudinal median plane V, closes the box 110 to form the rear face of the latter. It will be noted that in the embodiment shown in [Fig.4], the rear rib 115 is formed of two identical parts welded to each other, but it could just as easily be formed from a single piece.
[0023] Each of the side panels 111, 112 comprises a rear extension, 111a, 112a which extends in the plane of said side panel 111, 112 and extends the latter longitudinally towards the rear, beyond the rear rib 115. Each rear extension 111a, 112a of a side panel comprises a through bore whose bore axis is orthogonal to the plane of said side panel 111, 112.
[0024] The engine pylon 104 supports the turbojet 102 by means of engine attachments (not shown) fixed to the lower panel 114 and which may be conventional design as disclosed in document US-A-2016 / 0221682.
[0025] As described above, the assembly of the engine pylon 104 to the wing 103 is carried out by means of a system 105 for attaching the engine pylon to the wing which comprises a first and a second pair of upper connecting rods 120, 130 which connect the engine pylon 104 to the front spar 103b of the wing, a first and a second pair of lower connecting rods 140, 150, which connect the side panels 111, 112 of the engine pylon 104 to the front spar 103b of the wing 103 and at least one rear connecting rod 160 which connects, behind the front spar 103b of the wing, the rear rib 115 of the engine pylon 104 to the structure of the wing 103a, for example to a rib 106.
[0026] According to the invention, and unlike the invention described in patent application EP3939891, each connecting rod 121, 122, 131, 132 of the first and second pair of upper connecting rods 120, 130 connects the upper panel 113 of the engine pylon 104 to the front spar 103b of the wing by extending parallel to the plane of the upper panel 113, and the connection of each of the upper connecting rods to the front spar 103b of the wing is carried out by means of a sole 170 (visible in [Fig.4]) positioned under the lower surface panel 108 of the wing 103.
[0027] The upper panel 113 of the engine pylon 104 comprises a flat extension 113a which extends the upper panel longitudinally towards the rear, beyond the rear rib 115 of the box, i.e. beyond the rear face of the box 110.
[0028] The extension 113a comprises three through bores, with a central bore arranged in the middle of two end bores, and whose bore axes are perpendicular to the plane of the upper panel 113. The bore axis of the central bore is included in the longitudinal median plane V. The two end bores are distributed on either side of the central bore, symmetrically with respect to the longitudinal median plane V. The three bores are all three equipped with a spherical bearing.
[0029] The sole 170 is attached to the front spar 103b of the wing, under the latter, with the lower surface panel of the wing 108 sandwiched between the sole 170 and the front spar 103b of the wing. It will be noted that a reinforcing fitting 180 is attached to the front of the front spar 103b of the wing and makes it possible to locally reinforce the latter at the level of the area of attachment of the sole 170 to the front spar 103b. The sole 170 is attached to the front spar 103b of the wing, by means of any known attachment device, such as for example by means of screws screwed into the front spar 103b, and passing through the lower surface panel 108 of the wing. The sole 170 is made of metallic or composite material.
[0030] The sole 170 comprises an upper face 171 bearing against the lower surface panel 108 of the wing, and a lower face 174 which faces the ground. Each of the upper and lower faces 171, 174 of the sole is flat and extends parallel to the surface. on the plan of the upper panel 113 of the reactor mast.
[0031] Due to the angle between the intrados panel 108 and the ground, the sole has a general shape of a triangular prism and
[0032] The sole 170 comprises) at the front and facing the engine pylon 104, a front face 172 orthogonal to its upper face 171. A plate 173 extends out of the front face 172, towards the front, and in the extension and continuity of the upper panel 113 of the engine pylon. The plate 173 has a thickness equal to that of the upper panel 113 of the engine pylon. A space is defined between the lower surface panel of the wing 108 and the plate 173 and the smallest dimension, measured between the lower surface panel of the wing 108 and the plate 173, is greater than the thickness of an upper connecting rod 121, 122, 132, 132; it being defined that the four upper connecting rods all have the same thickness.
[0033] The plate 173 of the sole 170 comprises two through bores, distributed on either side of the longitudinal median plane V. The bore axes of the two bores of the plate 173 of the sole are parallel to the plane of the upper panel 113 of the engine mast 104 and the two bores are both equipped with a spherical bearing.
[0034] The connecting rods 121, 122 of the first upper pair of connecting rods 120 are three-point connecting rods, triangular in shape. Each three-point connecting rod 121, 122 comprises three through bores, where each through bore is disposed at a vertex of the connecting rod 121, 122. The axes of the three through bores of each of the three-point connecting rods 121, 122 are parallel to each other.
[0035] The connecting rods 121, 122 of the first pair of upper connecting rods 120 are positioned on a first side of the longitudinal median plane V and sandwich on the one hand the extension 113 of the upper panel 113, and on the other hand the plate 173.
[0036] Each connecting rod 121, 122 of the first pair of upper connecting rods 120 is articulated, on the one hand, at two points with the upper panel 113 at both an end bore and the central bore, and on the other hand, at one point with the plate 173 of the extension 170, at a bore of said extension.
[0037] For each articulation of the pair of upper connecting rods 120 to the upper panel 113 of the engine pylon, an articulation axis oriented perpendicular to the plane of the upper panel 113 and parallel to the longitudinal median plane V is fitted, depending on the position of the articulation point, in the ball joint bearing of the central bore or of the end bore of the extension 113a of the upper panel 113 and, on either side of this ball joint bearing, in a sleeve (not shown) mounted in the through bore of a three-point connecting rod 121, 122.
[0038] For each joint, an immobilization system is used to axially immobilize the end sleeves and the bearing. For example, the immobilization system is of the screw-nut type. In this case, on one side of the yoke, a screw is inserted into the joint axis and a first locking washer is inserted on the screw and interposed between the head of the screw and an end sleeve, and on the other side of the yoke, a second lock washer is fitted onto the shank of the screw and interposed between the other end sleeve and a threaded end of the screw. A clamping nut is tightened to the torque on the threaded end of the screw to keep the washers pressed against the end sleeves. The end sleeves and the bearing are thus axially immobilized due to the compaction between the clamping nut in contact with the second lock washer and the head of the screw in contact with the first lock washer.
[0039] The first pair of upper connecting rods 120 is fixed to the base plate 170 by a clevis-type connection with a hinge pin oriented perpendicular to the plane of the upper panel 113 of the engine pylon 104. The hinge pin is fitted into the ball joint bearing of the bore of the plate 173 of the base plate and, on either side of this ball joint bearing, into a sleeve (not shown) mounted in the through bore of a three-point connecting rod 121, 122. An immobilization system, for example as described above, is used to axially immobilize the end sleeves and the bearing.
[0040] The connecting rods 131, 132 of the second pair of upper connecting rods 130 are two-point connecting rods, of straight shape. Each two-point connecting rod 131, 132 comprises two through bores distributed over the two ends of the connecting rod.
[0041] The connecting rods 131, 132 of the second pair of upper connecting rods 130 are positioned on a second side of the longitudinal median plane V and sandwich on the one hand the extension 113a of the upper panel 113 of the engine mast 104, and on the other hand the plate 173 of the sole 170.
[0042] Each connecting rod 131, 132 of the second pair of upper connecting rods 130 is articulated, on the one hand, at a point with the upper panel 113 at the level of an end bore, and on the other hand, at a point with the plate 173 of the sole, at the level of a bore of the extension.
[0043] The second pair of upper connecting rods 130 is fixed to the upper panel 113 by a clevis-type connection with a hinge pin oriented perpendicular to the plane of the upper panel 113 and parallel to the longitudinal median plane V. The hinge pin is fitted into the ball joint bearing of the end bore of the upper panel 113 and, on either side of this ball joint bearing, into a sleeve (not shown) mounted in the through bore of a two-point connecting rod 131, 132. An immobilization system, for example as described above, is used to axially immobilize the end sleeves and the bearing.
[0044] The attachment of the second pair of upper connecting rods 130 to the sole 170 is ensured by a clevis-type connection with a hinge axis oriented perpendicular to the plane of the upper panel 113 and parallel to the longitudinal median plane V. The axis articulation is fitted into the ball joint bearing of the bore of the plate 173 of the extension 170 and, on either side of this ball joint bearing, into a sleeve (not shown) mounted in the through bore of a two-point connecting rod 131, 132. An immobilization system, for example as described above, is used to axially immobilize the end sleeves and the bearing.
[0045] The attachment of the upper connecting rods 121, 122, 131, 132 thus extends parallel to the plane of the upper panel 113. Furthermore, the upper connecting rods 121, 122, 131, 132, attached to the front spar 103b of the wing by means of the sole 170, extend under the lower surface panel of the wing 108. The upper connecting rods 121, 122, 131, 132 therefore do not extend into the space defined between the leading edge and the front spar 103b of the wing and do not obstruct the passage for a duct connected to an air system of the turbojet engine (not shown) which passes through the primary structure of the engine pylon 104 and opens onto an opening O made in the upper panel 113, running along the upper panel 113 to joining the leading edge of wing A and then traveling towards the fuselage 100a of the aircraft, along the front spar 103b of the wing and passing through the space defined between the leading edge of wing A and the front spar 103b of the wing.
[0046] The connecting rods 141, 142, 151, 152 of the first and second pairs of lower connecting rods 140, 150 are two-point connecting rods, of straight shape. Each two-point connecting rod 141, 142, 151, 152 comprises two through bores distributed over the two ends of the connecting rod.
[0047] On a first side of the longitudinal median plane V, the first pair of lower connecting rods 140 connects the rear extension 111a of the first side panel 111 to the front spar 103b of the wing and the connection is made by means of a first additional support 143 connected to the sole 170. On the second side of the longitudinal median plane V, the second pair of lower connecting rods 150 connects the rear extension 112a of the second side panel 112 to the front spar 103b of the wing and the connection is made by means of a second additional support 153 connected to the sole.
[0048] The first additional support and the second additional support 143, 153 here take the form of a first, respectively, second simple fittings fixed by screwing or welded to the sole 170. More precisely, the fittings 143, 153 are fixed to the lower face 174 of the sole 170 which is the part of the sole 170, facing the ground.
[0049] Each of the fittings 143, 153 comprises a flat tab, extending downwards and of the same thickness as that of a side panel 111, 112 of the box. Each flat tab comprises a through bore.
[0050] On each side of the longitudinal median plane V, the flat tab of a fitting 143,153 extends in the extension and continuity of the side panel 111,112 of the box and the axis of the bore of the tab is perpendicular to the plane of the side panel 143,153.
[0051] The connecting rods 141, 142, 151, 152 of the first respectively second pair of lower connecting rods 140, 150 sandwich the rear extension 111a, 112a of the first, respectively second side panel 111, 112 of the box, and on the other hand the lug of the first, respectively second, fitting 143, 153.
[0052] Each connecting rod 141, 142, 151, 152 of the first, respectively, second pair of lower connecting rods 140, 150 is articulated, on the one hand, at a point with the first, respectively second side panel 111, 112, and on the other hand, at a point with first, respectively second, additional support 143, 153.
[0053] The fixing of each of the two pairs of lower connecting rods 140, 150 with a side panel 111, 112 is carried out in a similar manner on each side of the longitudinal median plane V and is ensured by a clevis-type connection with a hinge pin oriented perpendicular to the plane of the side panel 111, 112. The vertical hinge pin is fitted into the ball joint bearing of the through bore arranged at the rear extension 111a, 112a of the side panel and, on either side of this ball joint bearing, into a sleeve (not shown) mounted in the through bore of a connecting rod 141, 142, 151, 152.
[0054] An immobilization system, for example as described above, is used to axially immobilize the end sleeves and the bearing.
[0055] The fixing of each of the two pairs of lower connecting rods 140, 150 with a fitting 143, 153 is carried out in a similar manner on each side of the longitudinal median plane V and is ensured by a clevis-type connection with a vertical articulation axis oriented vertically, that is to say perpendicular to the longitudinal axis X and parallel to the longitudinal median plane V. The vertical articulation axis is fitted into the ball joint bearing of the fitting 143, 153 and, on either side of this ball joint bearing, into a sleeve (not shown) mounted in the through bore of a connecting rod 141, 142, 151, 152.
[0056] An immobilization system, for example as described above, is used to axially immobilize the end sleeves and the bearing.
[0057] Each lower connecting rod 141, 142, 151, 152 thus extends parallel to the side panel 111, 112 to which it is connected and is thus oriented almost vertically, that is to say that the line connecting the two centers of the same lower connecting rod is almost vertical. Nevertheless, the lower connecting rods 141, 142, 151, 152 could be oriented with an inclination of between 0° and 30° relative to the vertical axis Z.
[0058] In the embodiment illustrated in the figures, the connection between the rear rib 115 and the wing 103 is provided by a pair of rear connecting rods 161, 162. The rear connecting rods 161, 162 are two-point connecting rods, of straight shape. Each rear connecting rod 161, 162 comprises two through bores distributed on the two ends of the connecting rod.
[0059] The pair of rear connecting rods 160 connects the rear rib 115 of the box to the structure of the wing 103a and each rear connecting rod 161, 162 is oriented in X / Z. The rear rib 115 comprises a lug oriented towards the outside of the box and towards the rear and which extends parallel to the longitudinal median plane V. The lug comprises a through bore whose bore axis is orthogonal to the longitudinal median plane V.
[0060] The connection between each rear connecting rod 161, 162 and the structure of the wing 103a passes through a fitting 180 secured (screwed or welded) to the structure of the wing 103a, for example secured to a rib 106, and fixed to the lower surface panel 108. The fitting 180 has a downwardly oriented tab which extends parallel to the longitudinal median plane V. The tab comprises a through bore whose bore axis is orthogonal to the longitudinal median plane V. The thickness of the tab of the fitting 180 fixed to the lower surface panel of the wing 108 is identical to the thickness of the tab of the fitting fixed to the rear rib of the box.
[0061] The rear connecting rods 161, 162 sandwich, on the one hand, the lug of the rear rib 115 of the box and, on the other hand, the lug of the fitting 180 fixed to the structure of the wing 103a.
[0062] Each rear connecting rod 161, 162 is articulated, at one point with the lug of the rear rib 115 of the box and at another point, with the lug of the fitting 180 fixed to the intrados panel 108 of the wing.
[0063] The fixing of the pair of rear connecting rods 160 with each of the lugs is carried out in a similar manner and is ensured by a clevis-type connection with a hinge pin oriented perpendicular to the longitudinal median plane V. The vertical hinge pin is fitted into the ball joint bearing of the through bore of the lug and, on either side of this ball joint bearing, into a sleeve (not shown) mounted in the central through bore of a rear connecting rod 161, 162.
[0064] An immobilization system, for example as described above, is used to axially immobilize the end sleeves and the bearing.
[0065] With such a fixing system 105 of the engine pylon 104 to the wing 103, the reaction of the bending moment around the vertical axis Z, called 'Mz' is ensured by the loading combination of the two pairs of upper connecting rods 120, 130, the reaction of the torsional moment around the horizontal axis X, called 'Mx' is ensured by the loading combination of the two pairs of lower connecting rods 140, 150 and the first pair of upper connecting rods 120 and finally, the reaction of the bending moment around the transverse axis Y, called 'My' is ensured by the combination of the upper connecting rods, 121, 122, 131, 132 of the rear connecting rods 161, 162 and the lower connecting rods 141, 142, 151, 152.
[0066] An advantage of the engine pylon attachment system 105 to the wing with this particular arrangement is that before the connecting rods are put in place on the structure primary, this is unique and can be commonly installed for a starboard wing or a port wing. It should be noted that the three-point upper connecting rods 121, 122, larger than the two-point upper connecting rods 131, 132, are arranged on the side of the engine pylon which is not on the side of the aircraft fuselage, because being larger, they could hinder the integration of the system coming from the fuselage and going towards the turbojet.
Claims
Claims
1. Assembly of a wing (103) of an aircraft with a powerplant (104), the wing (103) having a structure (103a) comprising a front spar (103b) located at the front of the wing, said structure (103a) being covered with an extrados panel (107) forming an upper outer skin of the wing (103), a lower surface panel (108) forming a lower outer skin of the wing (103), said extrados and lower surface panels (107, 108) being connected together by the front spar (103b), the powerplant (104) having the shape of an elongated box (110) extending in length along a longitudinal axis (L) and comprising a rear rib (115) at the rear of said spar, said rib (115) forming a face rear of the box (110), a flat upper panel (113) forming an upper face of the box (110), a longitudinal median plane (V) separating the reactor mast (104) into two parts,the reactor mast (104) comprising a first lateral plane panel (111) on a first side of the longitudinal median plane (V) and forming a first side of the box (110) and a second lateral plane panel (112) on the other side of the longitudinal median plane (V) and forming a second side of the box (110), the assembly being characterized in that it comprises:, - a first and a second pair of upper connecting rods (120, 130) arranged on either side of the longitudinal median plane (V), each of the first and second pairs and upper connecting rods (120, 130) connects the upper panel (113) of the engine pylon (104) to the front spar (103b) of the wing, extends parallel to the plane of the upper panel (113), the attachment of each upper connecting rod (121, 122, 131, 132) to the front spar (103b) is carried out by means of a sole (170) fixed to the front spar (103b) and having an upper face (171) in contact with the lower surface panel (108), the lower surface panel (108) being sandwiched between the sole (70) and the front spar (103b), the sole (170) comprising a plate (173) of thickness identical to that of the upper panel (113) of the reactor mast (104) and extending in the extension of said upper panel (113),a space being defined between the lower wing panel (108) and the plate (173) of the sole (170), each of the first pair and the second pair of upper connecting rods (120, 130), sandwiches, on the one hand the upper panel (103a) of the mast, and on the other hand the plate (173), the connecting rods of the first pair and of the second pair of upper connecting rods (120, 130) all being of the same thickness less than the smallest dimension of the space between the lower surface panel of the wing (108) and the plate (173) of the sole (170); - a first and a second pair of lower connecting rods (140, 150), where the lower connecting rods (141, 142, 151, 152) are two-point connecting rods, and where on one side of the engine pylon (104) the first pair of lower connecting rods (140) connects the first side panel (111) to the front spar (103b) of the wing through a first fitting (143) secured to the sole (170), and on the other side of the engine pylon (104), the second pair of lower connecting rods (150) connects the second side panel (112) to the front spar (103b) of the wing through a second fitting (153) secured to the sole (170); - at least one rear connecting rod (161, 162) connecting the rear rib (115) to the wing structure (103a).
2. Assembly according to claim 1, characterized in that the connecting rods (121, 122) of the first pair of upper connecting rods (120) are three-point connecting rods, connected at two points to the upper panel (113) of the mast and at one point to the plate (173) and in that the connecting rods (131, 132) of the second pair of upper connecting rods (130) are two-point connecting rods connected at one point to the upper panel (113) of the mast and at one point to the plate (173).