Arrangement for an aircraft with a wing and a reactor mast for coupling a propulsion system to the wing

Description

[0001] The present invention relates to an assembly for an aircraft which comprises a wing and a powerplant for coupling a propulsion system to the wing, as well as to an aircraft comprising a propulsion system and such an assembly for coupling the propulsion system to the wing. STATE OF THE PRIOR ART

[0002] Typically, for an aircraft, a propulsion system includes, for example, a turbojet engine that is attached to a wing of the aircraft using a jet engine pylon. The jet engine pylon generally consists of a primary structure formed by a box consisting of an upper spar, a lower spar, and two side panels connecting the two spars, and internal ribs distributed along the box.

[0003] The turbojet engine is fixed under the engine pylon to the engine attachment means which conventionally comprise, at the front, a front engine attachment, at the rear, a rear engine attachment, and between the front and rear engine attachments, a thrust force recovery assembly comprising recovery rods fixed between the turbojet engine and the primary structure of the pylon, to absorb the thrust forces generated by the turbojet engine.

[0004] The engine pylon is further attached to the wing structure by means of fittings through which the forces from the turbojet are transferred to the wing structure. Although current installations are satisfactory, it is necessary to provide a layout where the transfer of forces is improved, particularly in the case where the engine is installed vertically very close to the wing.

[0005] Document US10358226 proposes a known assembly for mounting a propulsion system on an aircraft. STATEMENT OF THE INVENTION

[0006] An object of the present invention is to provide an assembly for an aircraft comprising a wing and a reactor mast for coupling a propulsion system to the wing and which comprises means for attachment to the wing which ensure an improved transfer of forces to the wing structure while allowing the engine to be installed vertically very close to the wing.

[0007] For this purpose, 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, an upper surface panel and a lower surface panel fixed respectively to the upper part of the front spar and to the lower part of the front spar, where the upper surface panel is crossed vertically by a fourth bore and a fifth bore, a reactor mast comprising a primary structure, a pallet secured to the primary structure and extending to the rear and to the upper part of the primary structure, and two starboard and port fixing lugs secured to the primary structure and extending to the rear and on the sides of the primary structure, where the pallet is crossed vertically by a first bore, a second bore and a third bore, where each fixing lug is crossed horizontally by a sixth bore, two first shackles arranged vertically on either side of the pallet and the upper surface panel,wherein a first bore of each first shackle is coaxially aligned with the first bore of the pallet with a pin threaded into the bores thus aligned, wherein a second bore of each first shackle is coaxially aligned with the fourth bore of the upper panel with a pin threaded into the bores thus aligned, two second shackles arranged vertically on either side of the pallet and the upper panel, wherein a first bore of each second shackle is coaxially aligned with the second bore of the pallet with a pin threaded into the bores thus aligned, wherein a second bore of each second shackle is coaxially aligned with the third bore of the pallet with a pin threaded into the bores thus aligned, wherein a third bore of each second shackle is coaxially aligned with the fifth bore of the upper panel with a pin threaded into the bores thus aligned,and a starboard fitting and a port fitting fixed under the intrados panel and having respectively a starboard female yoke in which the starboard fixing lug is inserted and a port female yoke in which the port fixing lug is inserted, where each female yoke is crossed by a seventh bore whose axis is coaxial with the axis of the sixth bore of the fixing lug which is inserted therein, and where an axis is threaded into the associated bores thus aligned.

[0008] With such a reactor mast, the engine forces which are transported by the primary structure of the mast are transmitted directly to the extrados and intrados panels.

[0009] Advantageously, the extrados panel comprises a plate secured to the extrados panel and the two bores of the extrados panel are made in said plate.

[0010] The invention also proposes an aircraft comprising a propulsion system and an assembly according to one of the preceding variants where the propulsion system is fixed to the engine pylon. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] The above-mentioned and other features of the invention will become more clearly apparent from 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 an exploded and perspective view of an assembly according to a first embodiment of the invention, and Fig. 3 is an exploded and perspective view of an assembly according to a second embodiment of the invention. DETAILED PRESENTATION OF EMBODIMENT METHODS

[0012] There Fig. 1 shows an aircraft 10 which comprises a propulsion system 102 for example of the turbojet or turboprop type. The propulsion system 102 is linked to a wing 104 of the aircraft 10 via a reactor mast 106. The wing 104 and the reactor mast 106 form an assembly 100 according to the invention and the propulsion system 102 is fixed to the reactor mast 106 by any suitable fixing means known to those skilled in the art such as those disclosed in document US-A-2016 / 0221682.

[0013] In the following description, terms relating to a position are taken with reference to an aircraft in a normal flight position, that is to say as it is represented on the Fig. 1 and the "forward" and "rear" positions are taken relative to the front and rear of the propulsion system 102 and relative to the direction of advance F of the aircraft 10 when the propulsion system 102 is operating.

[0014] In the following description, and by convention, we call X the longitudinal direction of the propulsion system which is horizontal when the aircraft is on the ground, we call Y the transverse direction which is horizontal when the aircraft is on the ground, and Z 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.

[0015] 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 double-flow turbojet type with a nacelle.

[0016] There Fig. 2 shows the assembly 100a according to a first embodiment of the invention and the Fig. 3 shows the assembly 100b according to a second embodiment of the invention. The elements common to both embodiments bear the same references.

[0017] The reactor mast 106 comprises a rigid structure forming a box and also called primary structure 202. The primary structure 202 is formed of an upper spar 204, a lower spar 206 and two side panels 208 (only the port panel is shown in the figures 1 And 2 ) starboard and port connecting the two stringers 204 and 206.

[0018] The wing structure 104 includes a forward spar 210, an upper surface panel 214 and a lower surface panel 216 which are both attached to the forward spar 210 and extend generally in horizontal planes XY.

[0019] Of course, to ensure the rigidity of the wing, its structure includes other elements such as ribs which are distributed between the extrados panel 214 and the intrados panel 216.

[0020] The front spar 210 here takes the form of a profile in the shape of an inverted Z step on the Fig. 2, with an upper wing 210a and a lower wing 210b which are generally horizontal and a central portion 210c generally perpendicular to the median plane and extending vertically in the YZ plane. The extrados panel 214 is fixed above the upper wing 210a of the spar 210 and the intrados panel 216 is fixed below the lower wing 210b of the spar 210. The fixing of the front spar 210 to the panels 214 and 216 is carried out by any suitable means such as for example welds, bolts, etc. The extrados panel 214 is thus fixed in the upper part of the front spar 210 and the intrados panel 216 is fixed in the lower part of the front spar 210.

[0021] The central part 210c is at the level of the leading edge of the wing 104.

[0022] The attachment of the engine pylon 106 to the wing 104 differs slightly between the first embodiment and the second embodiment.

[0023] The engine pylon 106 comprises at the rear, a vane 280 which is integral with the primary structure 202 and which extends at the rear of the primary structure 202 in the extension of the upper spar 204. The vane 280 thus extends generally horizontally parallel to the XY plane. The vane 280 is crossed by three bores 280a-c and the axis of each bore 280a-c of the vane 280 is generally vertical. There is thus a first bore 280a, here starboard, a second bore 280b, here port, and a third bore 280c, here central. The third bore 280c is generally in the median plane and the first bore 280a and the second bore 280b are on either side of the median plane. The pallet 280 thus extends in the upper part of the primary structure 202 towards the front spar 210 of the wing 104 and opposite the extrados panel 214.

[0024] In the first embodiment of the invention, the extrados panel 214 is crossed by two bores 282a-b and the axis of each bore 282a-b of the extrados panel 214 is parallel to the axes of the bores 280a-c of the pallet 280 and is therefore generally vertical. There is a fourth bore 282a, here starboard, and a fifth bore 282b, here port.

[0025] In the second embodiment of the invention, the upper surface panel 214 comprises a plate 302 which is integral with the upper surface panel 214, which extends forward and which is crossed by the two bores 282a-b of the upper surface panel 214. The plate 302 thus extends forward from the front end of the upper surface panel 214 in the area of ​​the leading edge of the wing 104.

[0026] The bores 282a-b of the extrados panel 214 are on either side of the median plane and are aligned respectively with the first bore 280a and the second bore 280b parallel to the longitudinal direction X.

[0027] The assembly 100a-b comprises a first set of shackles 252, here starboard, and a second set of shackles 254, here port, and each set of shackles 252, 254 consists of two identical shackles superimposed vertically. In the embodiment of the invention presented here, the shackles 252 of the first set have two attachment points and the shackles 254 of the second set have three attachment points, but in another embodiment not shown, the two-point shackles 252 and the three-point shackles 254 can be reversed from starboard to port and vice versa.

[0028] One of the shackle sets 252, 254, here the first shackle set 252, consists of two first shackles 252, each having two bores. The two first shackles 252 are arranged vertically on either side of the pallet 280 where a first bore of each first shackle 252 is coaxially aligned with the first bore 280a of the pallet 280. A pin is threaded through the first bore of each first shackle 252 and the first bore 280a of the pallet 280 to form a connection point in the form of a pivot connection about a generally vertical axis.

[0029] The first two shackles 252 are arranged vertically on either side of the upper surface panel 214 where a second bore of each first shackle 252 is coaxially aligned with the fourth bore 282a of the upper surface panel 214. A pin is threaded through the second bore of each first shackle 252 and the fourth bore 282a of the upper surface panel 214 to form a connection point in the form of a pivot connection about a generally vertical axis.

[0030] The other of the shackle sets 252, 254, here the second shackle set 254, consists of two second shackles 254 each having three bores. The two second shackles 254 are arranged vertically on either side of the pallet 280 where a first bore of each second shackle 254 is coaxially aligned with the second bore 280b of the pallet 280 and where a second bore of each second shackle 254 is coaxially aligned with the third bore 280c of the pallet 280. A pin is threaded through the first bore of each second shackle 254 and the second bore 280b of the pallet 280 to form a connection point in the form of a pivot connection about a generally vertical axis. A pin is threaded into the second bore of each second shackle 254 and the third bore 280c of the paddle 280 to form a connection point in the form of a pivot connection about a generally vertical axis.

[0031] The two second shackles 254 are arranged vertically on either side of the upper surface panel 214 where a third bore of each second shackle 254 is coaxially aligned with the fifth bore 282b of the upper surface panel 214. A pin is threaded through the third bore of each second shackle 254 and the fifth bore 282b of the upper surface panel 214 to form a connection point in the form of a pivot connection about a generally vertical axis.

[0032] The reactor mast 106 comprises, at the rear of the primary structure 202, two starboard 270a and port 270b fixing lugs which are integral with the primary structure 202 and which extend at the rear of the primary structure 202 in the extension respectively of the starboard side panel and the port side panel 208. The fixing lugs 270a-b thus extend on the starboard and port sides of the primary structure 202 towards the front spar 210.

[0033] Each fixing lug 270a-b thus extends generally in a vertical plane parallel to the XZ plane and they are on either side of the median plane. Each fixing lug 270a-b is crossed by a sixth bore 272a-b, respectively starboard and port and the axis of each sixth bore 272a-b is generally horizontal. There is thus a sixth starboard bore 272a and a sixth port bore 272b which are coaxial.

[0034] The assembly 100a-b also comprises two fittings 274a-b, namely a starboard fitting 274a and a port fitting 274b which are arranged on either side of the median plane and each is fixed under the intrados panel 216 by any suitable means such as welds, bolts, etc.

[0035] Each fitting 274a-b has a female yoke 276a-b, namely a starboard female yoke 276a into which the starboard fixing lug 270a is inserted and a port female yoke 276b into which the port fixing lug 270b is inserted.

[0036] Each female yoke 276a-b is crossed by a seventh bore 278a-b whose axis is coaxial with the axis of the sixth bore 272a-b of the fixing lug 270a-b which is inserted therein, that is to say generally horizontal.

[0037] The connection between a fitting 274a-b and the associated fixing lug 270a-b is ensured by the installation of an axis which is threaded into the associated bores, i.e. the female yoke 276a-b and the fixing lug 270a-b, and takes the form of a pivot connection around a generally horizontal axis.

[0038] The forces from the propulsion system 102 thus pass through the engine pylon 106 and then directly into the extrados 214 and intrados 216 panels. In addition, the rear part of the engine pylon 106 is thus opposite the front spar 210, the entire height of which is used in order to reduce the forces induced by the absorption of moments, in particular MY and MZ. The longitudinal forces (Tx) are distributed across: the two starboard shackles 252, the two port shackles 254 through the second bore 280b of the pallet 280 and the fifth bore 282b of the extrados panel 214, and the connections between the female clevises 276a-b and the fixing lugs 270a-b.

[0039] The transverse forces (Ty) are transmitted through the two port shackles 254.

[0040] The vertical forces (Tz) are transmitted through the connections between the female yokes 276a-b and the fixing lugs 270a-b.

[0041] The torsional moment Mx about the longitudinal direction X is compensated at the connections between the female yokes 276a-b and the fixing lugs 270a-b.

[0042] The bending moment My about the transverse direction Y and the bending moment Mz about the vertical direction Z are compensated at the level of the connections between the female clevises 276a-b and the fixing lugs 270a-b and at the level of the sets of shackles 252 and 254 arranged on either side of the vertical median plane, to starboard and port.

Claims

1. Assembly (100, 100a-b) for mounting a propulsion system (102) having a vertical median plane (XZ) on an aircraft (10), said assembly (100, 100a-b) comprising: - a wing (104) with a front spar (210), a suction-side panel (214) and a pressure-side panel (216), which are fastened at the upper portion of the front spar (210) and at the lower portion of the front spar (210), respectively, wherein a fourth bore (282a) and a fifth bore (282b) pass vertically through the suction-side panel (214), - an engine pylon (106) comprising a primary structure (202), a blade (280), which is secured to the primary structure (202) and extends to the rear and in the upper portion of the primary structure (202), and two starboard-side (270a) and port-side (270b) fastening lugs, which are secured to the primary structure (202) and extend to the rear and along the sides of the primary structure (202), wherein a first bore (280a), a second bore (280b) and a third bore (280c) pass vertically through the blade (280), wherein a sixth bore (272a-b) passes horizontally through each fastening lug (270a-b), and - a starboard-side fitting (274a) and a port-side fitting (274b), which have, respectively, a starboard-side female clevis (276a) in which the starboard-side fastening lug (270a) is inserted and a port-side female clevis (276b) in which the port-side fastening lug (270b) is inserted, wherein a seventh bore (278a-b) passes through each female clevis (276a-b), the axis of said seventh bore being coaxial with the axis of the sixth bore (272a-b) in the fastening lug (270a-b) inserted therein, and wherein a pin is inserted into the associated bores aligned in this way, said assembly (100, 100a-b) being characterized in that the starboard-side fitting (274a) and a port-side fitting (274b) are fastened beneath the pressure-side panel (216) and in that the assembly (100, 100a-b) comprises also: - two first shackles (252) arranged vertically on either side of the blade (280) and of the suction-side panel (214), wherein a first bore of each first shackle (252) is aligned so as to be coaxial with the first bore (280a) of the blade (280), with a pin being inserted into the bores aligned in this way, wherein a second bore of each first shackle (252) is aligned so as to be coaxial with the fourth bore (282a) of the suction-side panel (214), with a pin being inserted into the bores aligned in this way, and - two second shackles (254) arranged vertically on either side of the blade (280) and of the suction-side panel (214), wherein a first bore of each second shackle (254) is aligned so as to be coaxial with the second bore (280b) of the blade (280), with a pin being inserted into the bores aligned in this way, wherein a second bore of each second shackle (254) is aligned so as to be coaxial with the third bore (280c) of the blade (280), with a pin being inserted into the bores aligned in this way, wherein a third bore of each second shackle (254) is aligned so as to be coaxial with the fifth bore (282b) of the suction-side panel (214), with a pin being inserted into the bores aligned in this way.

2. Assembly (100b) according to Claim 1, characterized in that the suction-side panel (214) comprises a plate (302) that is secured to the suction-side panel (214) and in that the two bores (282a-b) of the suction-side panel (214) are formed in said plate (302).

3. Aircraft (10) comprising a propulsion system (102) and an assembly (100) according to either of Claims 1 and 2, wherein the propulsion system (102) is fastened to the engine pylon (106).