AIRCRAFT ASSEMBLY COMPRISING MEANS FOR ATTACHING A WING TO AN ENGINE POST

Abstract

AIRCRAFT ASSEMBLY COMPRISING MEANS FOR ATTACHING A WING TO AN ENGINE POLE The invention relates to an aircraft assembly (1) comprising an upper fitting (104c) attached to a structure (104a) of the aircraft wing, a lower fitting (104d) attached to an underside panel of the wing, an engine pylon (106) with two side panels mounted hinged on the lower fitting (104d), a starboard connecting rod (252a) and a port connecting rod (252b) mounted hinged between the side panel (208a-b) which is on the same side and the upper fitting (104c), and a stud having a proximal end integral with a rear rib of the engine pylon (106) and a distal end mounted in a window of the lower fitting (104d) through an annular linear connection. With such an assembly, the occurrence of out-of-plane forces is limited. Fig. 2

Description

Title of the invention: Aircraft assembly comprising means for attaching a wing to an engine mast technical field

[0001] The present invention relates to an aircraft assembly comprising means for attaching a wing to a jet pylon, as well as an aircraft comprising a wing and such an assembly. PREVIOUS STATE OF THE ART

[0002] Typically, for an aircraft, a propulsion system comprises a turbojet engine which is fixed under a wing of the aircraft by means of a jet pylon. The jet 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 is fixed under the engine mast by means of engine attachments which conventionally include, 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 on one side to the turbojet, and on the other side to a shoe integral with the primary structure of the mast, to absorb the thrust forces generated by the turbojet.

[0004] A fastening system connects the engine pylon to the wing. This fastening system reacts to and absorbs bending moments and shear forces at the interface between the engine pylon and the wing. An example of such an arrangement is described in US-A-2016 / 0221682.

[0005] Although such fastening systems are satisfactory, it is desirable to find different arrangements in particular to limit the appearance of out-of-plane forces in the reactor mast and to enlarge the force transfer surface to the wing structure. Description of the invention

[0006] An object of the present invention is to provide an aircraft assembly comprising means for fixing a wing to a jet pylon where the fixing means limit the appearance of out-of-plane forces in the jet pylon and enlarge the surface area for transferring forces to the wing structure.

[0007] To this end, an assembly is proposed for an aircraft comprising a wing with a structure and an intrados panel, said assembly having a longitudinal direction and a vertical median plane and comprising:

[0008] - an upper fitting intended to be fixed to the wing structure,

[0009] - a lower fitting intended to be fixed to the intrados panel,

[0010] - a reactor mast having a primary structure forming a box and comprising a starboard side panel, a port side panel and a rear rib that closes the box at the rear, where each side panel is hinged to the lower fitting,

[0011] - a starboard connecting rod and a port connecting rod where a first end of each connecting rod is mounted hinged on the side panel which is on the same side and where a second end of each connecting rod is mounted hinged on the upper fitting, and

[0012] - a stud with an axis parallel to the longitudinal direction and having an end proximal end integral with the rear rib and a distal end mounted in a window of the lower fitting through an annular linear connection.

[0013] With such an assembly, the appearance of out-of-plane forces is limited.

[0014] Advantageously, the block is movable in translation relative to the lower fitting parallel to a vertical direction.

[0015] Advantageously, the assembly comprises a ring which has a spherical outer surface and which is fitted onto the distal end of the stud, a nut which has a spherical inner surface in which the ring is housed, where on either side of the nut, the outer surface of the nut has a rib parallel to the vertical direction, where, on the edges of the window, the lower fitting has, for each rib, a recess extending parallel to the vertical direction in which said rib is guided in translation.

[0016] Advantageously, the block consists of two half-cylinders joined along a plane where the proximal end of each half-cylinder is fixed to the rear rib.

[0017] Advantageously, the two second ends of the connecting rods are mounted articulated around the same articulation shaft.

[0018] Advantageously, said articulation shaft consists of a peripheral shaft which is cylindrical and hollow and an inner shaft which is fitted into the peripheral shaft.

[0019] According to a particular embodiment, the lower fitting consists of a port piece and a starboard piece fixed to each other along the vertical median plane, and where each piece is fixed to the side panel which is on the same side and to the intrados panel.

[0020] According to a particular embodiment, the lower fitting consists of a lower port piece, a lower starboard piece, an upper port piece, and an upper starboard piece, where the starboard pieces are fixed to each other, where the port pieces are fixed to each other, where the starboard and port pieces are fixed to each other along the vertical median plane, where each lower piece is attached to the side panel which is on the same side and where each upper piece is attached to the intrados panel.

[0021] The invention also proposes an aircraft comprising a wing with a structure and an underside panel, a turbojet and an assembly according to one of the preceding variants, where the upper fitting is fixed to the wing structure, where the lower fitting is fixed to the underside panel and where the turbojet is fixed under the engine mast. Brief description of the drawings

[0022] 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:

[0023] [Fig-1] is a side view of an aircraft according to the invention,

[0024] [Fig.2] is a perspective and side view of an assembly according to the invention,

[0025] [Fig.3] is a perspective and side view of the assembly according to the invention,

[0026] [Fig.4] is a perspective view of a detail of the assembly according to the invention,

[0027] [Fig.5] shows the detail of [Fig.4] seen in cross-section by plane V,

[0028] [Fig.6] is an exploded view of certain elements of the detail in [Fig.4], and

[0029] [Fig.7] is a perspective and front view of a part of the assembly according to the invention.

[0030] DETAILED STATEMENT OF IMPROVEMENTS

[0031] Figure 1 shows an aircraft 10 comprising a propulsion system 100 with a turbojet engine 102 connected to a wing 104 of the aircraft 10 by means of a jet engine pylon 106. The jet engine pylon 106 and the fastening means described below, which secure the jet engine pylon 106 to the wing 104, form an assembly according to the invention. The turbojet engine 102 is fixed below the jet engine pylon 106.

[0032] In the following description, terms relating to a position are taken with reference to an aircraft in normal flight position, i.e. as shown in [Fig.1], and the positions "forward" and "rear" are taken with respect to the front and rear of the turbojet and with respect to the forward direction F of the aircraft 10 when the turbojet 102 is operating.

[0033] In the following description, and by convention, X is called the longitudinal direction of the assembly which is parallel to the longitudinal axis of the turbojet, 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.

[0034] The turbojet 102 has a shape of revolution around its longitudinal axis.

[0035] As shown in [Fig. 2] and [Fig. 3], the wing 104 has a rigid structure 104a, which here takes the form of spars extending along the transverse Y direction. The wing 104 also has an intrados panel (104b, [Fig. 7]) that at least partially covers the lower part of the structure 104a. Conventionally, the wing 104 also has an extrados panel that at least partially covers the upper part of the structure 104a.

[0036] Assembly 1 also includes an upper fitting 104c which is fixed to the wing structure 104a 104 and a lower fitting 104d which is fixed to the lower wing panel 104b and more particularly under the lower wing panel 104b. These fixings are secured by any suitable means such as bolts, spot welds,

[0037] In particular, the fixings of the lower fitting 104d to the intrados panel 104b ensure a transfer of forces in X, Y and Z.

[0038] The upper fitting 104c takes the form of a wedge fixed to a spar of the structure 104a of the wing 104 and more particularly to the front spar.

[0039] The lower fitting 104d takes the form of a beam which extends along the longitudinal direction X and as shown in [Fig.7], it has an upper face 218 arched to best fit the shape of the intrados panel 104b.

[0040] The upper fitting 104c is above the lower fitting 104d.

[0041] The reactor pylon 106 includes a rigid structure 202 forming a box girder, also called the primary structure. The primary structure 202 is formed by an upper spar 204, a lower spar 206, and a starboard side panel 208a and a port side panel 208b connecting the two spars 204 and 206. The primary structure 202 may also include internal ribs distributed within the primary structure 202 and connected to the spars 204 and 206 and to the side panels 208a-b. The primary structure 202 also includes a rear rib 268 that closes the box girder at the rear and is generally perpendicular to the longitudinal direction X.

[0042] The primary structure 202 is globally symmetric with respect to a median plane XZ of the set 1 which extends vertically.

[0043] The primary structure 202 supports the turbojet 102 via engine attachments which may be of conventional design such as those disclosed in document US-A-2016 / 0221682.

[0044] The cascade attachment of the turbojet 102 to the engine mast 106 and then to the structure 104a of the wing 104 ensures the transfer of forces from the turbojet 102 to the wing 104.

[0045] The attachment of the reactor mast 106 to the wing 104 is ensured, among other things, by the fact that each side panel 208a-b is mounted articulated on the lower fitting 104d. Each of the two articulations here takes the form of a rotation around the same first articulation axis 50 which is perpendicular to the vertical median plane XZ and therefore parallel to the transverse direction Y.

[0046] These joints ensure the transfer of forces in Z and X.

[0047] Each articulation of a side panel 208a-b to the lower fitting 104d is made here by a lower shaft (not shown) which passes through a bore of said side panel 208a-b and a bore of the lower fitting 104d. There are thus two lower shafts arranged on either side of the vertical median plane XZ and these two articulations are redundant with each other, that is to say that if one of them has failures, the force path passes through the other.

[0048] The attachment of the reactor pylon 106 to the wing 104 is also ensured by a starboard connecting rod 252a and a port connecting rod 252b, which are also arranged on either side of the vertical median plane XZ. One end of each connecting rod 252a-b is hinged to the side panel 208a-b on the same side, and the other end of each connecting rod 252a-b is hinged to the upper fitting 104c. Each hinge of the first two ends takes the form of a rotation about the same second hinge axis 52, which is perpendicular to the vertical median plane XZ and therefore parallel to the transverse direction Y. Each hinge of the second two ends takes the form of a rotation about the same third hinge axis 54, which is perpendicular to the vertical median plane XZ and therefore parallel to the transverse direction Y.

[0049] These joints ensure the transfer of forces in Z and X.

[0050] Each articulation of a first end to the side panel 208a-b is made here by an upper shaft (not shown) which passes through a bore of said first end and a bore of said side panel 208a-b. There are thus two upper shafts arranged on either side of the vertical median plane XZ and these two articulations are redundant with each other, that is to say that if one of them has failures, the force path passes through the other.

[0051] Here, each first end constitutes a female clevis into which a male clevis of the side panel 208a-b considered is fitted.

[0052] Each articulation of a second end to the upper fitting 104c is achieved here by an articulation shaft 210 which passes through a bore of said second end and a bore of the upper fitting 104c. In the embodiment of the invention presented here, there is a single articulation shaft 210 for both second ends of the connecting rods 252a-b.

[0053] For reasons of redundancy, the articulation shaft 210 may consist of a peripheral shaft which is cylindrical and hollow and an inner shaft which is fitted into the peripheral shaft. Thus, in the event of failure of the peripheral shaft, the inner shaft can take over.

[0054] The attachment of the reactor mast 106 to the wing 104 is also ensured by a stud 502 (Figs. 4 and 5) in the form of a straight cylinder whose axis is parallel to the longitudinal direction X. The stud 502 has a proximal end fixed to the rear rib 268 and a distal end mounted in a window 601 of the lower fitting 104d through an annular linear connection 504, i.e. that the stud 502 is mounted in the window 601 through a ball joint and the stud 502 is also movable in translation relative to the lower fitting 104d parallel to the longitudinal direction X.

[0055] Plot 502 projects rearward from rear rib 268.

[0056] Such an arrangement limits the appearance of out-of-plane forces in the engine pylon and widens the force transfer surface to the wing structure.

[0057] According to a particular arrangement, the block 502 is also movable in translation relative to the lower fitting 104d parallel to a vertical direction Z. This arrangement ensures the transfer of forces in Y but avoids recovering forces in Z, which limits unnecessary hyperstaticity and the appearance of moments.

[0058] Figs. 4 to 6 show an embodiment of the connection between the stud 502 and the lower fitting 104d.

[0059] The assembly 1 comprises a ring 602 which is drilled with a central bore 602a which is fitted onto the distal end of the stud 502 and where the stud 502 is movable in translation in said central bore 602a parallel to the longitudinal direction X. Furthermore, the ring 602 has an outer surface 602b which is spherical.

[0060] Assembly 1 also includes a nut 604 with a spherical inner surface in which the ring 602 is housed. The ring 602 is thus free to rotate within the nut 604.

[0061] Here, assembly 1 also has a locking plate 608 which is fixed to the nut 604, for example by screw, and which blocks the rotation of the nut 604 relative to the lower fitting 104d.

[0062] The ring 602, the nut 604 and the locking plate 608 are housed in the window 601 of the lower fitting 104d, the shape of which is adapted.

[0063] To ensure the translation of the stud 502 parallel to a vertical direction Z, the nut 604 has on its outer surface two ribs 606 which are on either side of the nut 604 with respect to the vertical median plane XZ. Each rib 606 is parallel to the vertical direction Z and here takes the form of a portion of a cylinder.

[0064] On the edges of the window 601, the lower fitting 104d has for each rib 606, a recess 603 which extends parallel to the vertical direction Z and in which said rib 606 is guided in translation.

[0065] For reasons of redundancy, the block 502 is here made up of two half-cylinders 502a-b which are on either side of a plane XY perpendicular to the vertical direction Z. The two half-cylinders 502a-b are thus joined along said plane XY and the proximal end of each half-cylinder 502a-b is fixed to the rear rib 268, here by means of a shoe 506a-b fixed for example by screw elements to the rear rib 268. Thus in the event of breakage of one or the other of the half-cylinders 502a-b, the other takes over.

[0066] To keep the two half-cylinders 502a-b joined, the distal end of the stud 502 is covered with a sleeve 508.

[0067] According to a particular embodiment, shown more especially in [Fig. 7], the lower fitting 104d consists of a lower port piece 112b, a lower starboard piece 112a, an upper port piece 114b, and an upper starboard piece 114a. The lower pieces 112a-b are symmetrical to each other with respect to the vertical median plane XZ and are joined to each other along this vertical median plane XZ. Similarly, the upper pieces 114a-b are symmetrical to each other with respect to the vertical median plane XZ and are joined to each other along this median plane XZ.

[0068] The port parts 112a and 114a are fixed to each other, and the starboard parts 112b and 114b are fixed to each other. Finally, the port parts 112a and 114a and the starboard parts 112b and 114b are fixed to each other along the vertical median plane XZ. All these fixings are achieved by suitable means such as screws.

[0069] In addition, each lower piece 112a-b is fixed to the side panel 208a-b which is on the same side and each upper piece 114a-b is fixed to the intrados panel 104b.

[0070] Thus, in the event of a break in one or the other of these parts, the forces continue to be transferred through the other parts.

[0071] In an embodiment not shown, the redundancy is reduced. The lower port part 112b and the upper port part 114b are a single piece and form a port part, and similarly, the lower starboard part 112a and the upper starboard part 114a are a single piece and form a starboard part. The lower fitting 104d then consists of the port part and the starboard part, which are symmetrical to each other with respect to the vertical median plane XZ and are joined to each other along this median plane XZ. The port and starboard parts are fixed to each other along the vertical median plane XZ, and each part is attached to the side panel 208a-b which is on the same side and to the intrados panel 104b.

Claims

Demands

1. Assembly (1) for an aircraft (10) comprising a wing (104) with a structure (104a) and an underside panel (104b), said assembly (1) having a longitudinal direction (X) and a vertical median plane (XZ) and comprising: - an upper fitting (104c) for being attached to the structure (104a) of the wing (104), - a lower fitting (104d) for being attached to the underside panel (104b), - a jet pylon (106) having a primary structure (202) forming a box and comprising a starboard side panel (208a), a port side panel (208b) and a rear rib (268) which closes the box at the rear, where each side panel (208a-b) is hinged to the lower fitting (104d),- a starboard connecting rod (252a) and a port connecting rod (252b) where a first end of each connecting rod (252a-b) is hinged to the side panel (208a-b) on the same side and where a second end of each connecting rod (252a-b) is hinged to the upper fitting (104c), and - a stud (502) with an axis parallel to the longitudinal direction (X) and having a proximal end integral with the rear rib (268) and a distal end mounted in a window (601) of the lower fitting (104d) through an annular linear connection (504).

2. Assembly (1) according to claim 1, characterized in that the stud (502) is movable in translation relative to the lower fitting (104d) parallel to a vertical direction (Z).

3. Assembly (1) according to claim 2, characterized in that it comprises a ring (602) having a spherical outer surface (602b) and fitted onto the distal end of the stud (502), a nut (604) having a spherical inner surface in which the ring (602) is housed, wherein on either side of the nut (604), the outer surface of the nut (604) has a rib (606) parallel to the vertical direction (Z), wherein, on the edges of the window (601), the lower fitting (104d) has, for each rib (606), a recess (603) extending parallel to the vertical direction (Z) in which said rib (606) is guided in translation.

4. Assembly (1) according to any one of claims 1 to 3, characterized in that the block (502) consists of two half-cylinders (502a-b) joined along a plane (XY) where the proximal end of each half-cylinder (502a-b) is fixed to the rear rib (268).

5. Assembly (1) according to any one of claims 1 to 4, characterized in that the two second ends of the connecting rods (252a-b) are mounted articulated around the same articulation shaft (210).

6. Assembly (1) according to claim 5, characterized in that said articulation shaft (210) consists of a peripheral shaft which is cylindrical and hollow and an inner shaft which is fitted into the peripheral shaft.

7. Assembly (1) according to any one of claims 1 to 6, characterized in that the lower fitting (104d) consists of a port piece and a starboard piece fixed to each other along the vertical median plane (XZ), and where each piece is fixed to the side panel (208a-b) which is on the same side and to the intrados panel (104b).

8. Assembly (1) according to any one of claims 1 to 6, characterized in that the lower fitting (104d) consists of a lower port piece (112b), a lower starboard piece (112a), an upper port piece (114b), and an upper starboard piece (114a), wherein the starboard pieces (112a, 114a) are fastened to each other, wherein the port pieces (112b, 114b) are fastened to each other, wherein the starboard pieces (112a, 114a) and the port pieces (112b, 114b) are fastened to each other along the vertical median plane (XZ), wherein each lower piece (112a-b) is fixed to the side panel (208a-b) that is on the same side, and wherein each upper piece (114a-b) is fixed to the intrados panel (104b).

9. Aircraft (10) comprising a wing with a structure (104a) and an underside panel (104b), a turbojet (102) and an assembly (1) according to any one of the preceding claims, wherein the upper fitting (104c) is fixed to the structure (104a) of the wing (104), wherein the lower fitting (104d) is fixed to the underside panel (104b) and wherein the turbojet (102) is fixed under the engine pylon (106).

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