Aircraft comprising at least one engine mounting system with wing attachments positioned approximately in a median longitudinal plane

Abstract

Aircraft comprising at least one engine attachment system having wing attachments positioned approximately in a median longitudinal plane. The invention relates to an aircraft comprising at least one engine attachment system that connects a propulsion unit and a wing and that includes a primary structure (50), engine attachments connecting the primary structure (50) and the propulsion unit, and at least first, second, and third wing attachments (54, 56, 58) connecting the primary structure (50) and the wing structure (46); the first and second wing attachments (54, 56) being offset vertically from each other, the third wing attachment (58) being offset in the longitudinal direction (X) rearward relative to the first and second wing attachments (54, 56). This solution optimizes the transmission of forces between the primary structure (50) and the wing structure (46). Figure 6

Description

Title of the invention: Aircraft comprising at least one engine attachment system having wing attachments positioned approximately in a median longitudinal plane

[0001] The present application relates to an aircraft comprising at least one engine attachment system connecting a propulsion assembly to the wing of the aircraft and having wing attachments positioned approximately in a median longitudinal plane.

[0002] According to an embodiment visible in [Fig.l], an aircraft 10 comprises a fuselage 12, at least one wing 14 connected to the fuselage 12 as well as propulsion assemblies 16 arranged on either side of the fuselage 12 and connected to the wing 14 by an engine attachment system.

[0003] According to an embodiment visible in [Fig.2], each propulsion assembly 16 comprises an engine 20, a propeller 22 having an axis of rotation A22, a gearbox 24 connecting the engine 20 and the propeller 22, the attachment system 18 connecting the engine 20 and the gearbox 24 to the wing 14. Whatever the embodiment, the propulsion assembly 16 has a thrust axis. In the case of a propeller engine, the thrust axis coincides with the axis of rotation A22 of the propeller.

[0004] For the remainder of the description, a longitudinal direction X is parallel to the thrust axis. A median longitudinal plane Py is a vertical plane containing the thrust axis. A transverse plane Px is perpendicular to the longitudinal direction X. A horizontal transverse direction Y is perpendicular to the longitudinal direction X and oriented horizontally. A vertical direction Z is perpendicular to the longitudinal direction X and oriented vertically. The concepts “front” and “rear” refer to the direction of airflow relative to the aircraft in flight, the air flowing from front to rear.

[0005] According to an embodiment visible in [Fig. 3], the engine attachment system 18 comprises a front hoop 26 connected by several interfaces to a front zone of the engine 20 as well as a rear hoop 28 connected by several interfaces to a rear zone of the engine 20. Each front or rear hoop 26, 28 comprises a transverse and horizontal part 26.1, 28.1 as well as first and second uprights 26.2, 26.3, 28.2, 28.3 which are substantially vertical, offset in the horizontal transverse direction Y.

[0006] The front and rear arches 26, 28 are connected to each other by oblique connecting rods 30 so as to form a lattice structure.

[0007] The engine attachment system 18 comprises wing attachments connecting the rear arch 28 to the wing 14 at anchor points 32.1 to 32.5. Thus, the part transverse 28.1 of the rear arch 28 is connected to the wing 14 at an anchoring point 32.1 located at the median longitudinal plane Py. The first upright 28.2 of the rear arch 28 is connected to the wing 14 at two anchoring points 32.2, 32.3 located in a first vertical longitudinal plane spaced from the median longitudinal plane Py. The second upright 28.3 of the rear arch 28 is connected to the wing 14 at two anchoring points 32.4, 32.5 located in a second vertical longitudinal plane, the first and second vertical longitudinal planes being symmetrical with respect to the median longitudinal plane Py. The first and second uprights 28.2, 28.3 being positioned on either side of the engine 20, the first and second vertical longitudinal planes are spaced significantly apart in the transverse and horizontal direction Y so that the fairing which covers the engine attachment system 18 is relatively wide at the level of the wing 14, which is detrimental in terms of aerodynamic performance.

[0008] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0009] For this purpose, the invention relates to an aircraft comprising at least one wing, at least one propulsion assembly and at least one engine attachment system connecting the propulsion assembly and the wing, the latter having a wing structure; said engine attachment system comprising a primary structure, engine attachments connecting the primary structure and the propulsion assembly and at least first, second and third wing attachments connecting the primary structure and the wing structure, the primary structure having a median longitudinal plane and extending in a longitudinal direction from front to rear.

[0010] According to the invention, the first and second wing attachments are offset in height relative to each other, the third wing attachment being offset in the longitudinal direction towards the rear relative to the first and second wing attachments.

[0011] This arrangement makes it possible to arrange the first, second and third wing attachments in a vertical longitudinal plane, which makes it possible to optimize the transmission of forces between the primary structure and the wing structure, the forces being introduced into the wing structure without offset or with a small offset relative to a vertical longitudinal plane.

[0012] According to another characteristic, the first, second and third wing attachments are configured to form a set of isostatic connections between the wing structure and the primary structure.

[0013] According to another characteristic, the wing structure comprises a front spar and a second spar offset in the longitudinal direction towards the rear relative to the first spar, the first and second wing attachments being connected to the spar. front, the third wing attachment being connected to the second spar.

[0014] According to another characteristic, the first, second and third wing attachments each have a connection comprising at least one pivot axis and / or a swivel point positioned in the median longitudinal plane or in a vertical longitudinal plane slightly spaced from the median longitudinal plane.

[0015] According to another characteristic, the third wing attachment comprises a third pivot axis parallel to the longitudinal direction and contained in the median longitudinal plane.

[0016] According to another characteristic, the first wing attachment comprises a first pivot axis parallel to a vertical direction. In addition, the second wing attachment comprises a second pivot axis parallel to the longitudinal direction.

[0017] According to another characteristic, the first wing attachment comprises a first pivot axis parallel to a vertical direction. In addition, the second wing attachment comprises a second pivot axis aligned with the first pivot axis.

[0018] According to another characteristic, the first wing attachment comprises a first pivot axis parallel to the longitudinal direction. In addition, the second wing attachment comprises a second pivot axis parallel to a vertical direction.

[0019] According to another characteristic, each of the first, second and third wing attachments comprises a tab or a plate secured to a first element among the wing structure and the primary structure, a yoke secured to a second element, different from the first element, among the wing structure and the primary structure as well as a cylindrical rod, secured to the tab or the plate and to the yoke, forming the first, second or third pivot axis.

[0020] According to another characteristic, the first wing attachment comprises at least one pivot axis parallel to the vertical direction. In addition, the second wing attachment comprises a ball joint.

[0021] According to another characteristic, the first wing attachment comprises at least one first lug secured to the wing structure, at least one second lug secured to the primary structure, at least one connecting rod which extends between first and second ends, a first cylindrical rod secured to the first lug and to the first end of the connecting rod and forming a first pivot axis parallel to the vertical direction as well as a second cylindrical rod secured to the second lug and to the second end of the connecting rod and forming a second pivot axis parallel to the vertical direction.

[0022] According to another characteristic, the first wing attachment comprises a tab secured to a first element among the wing structure and the primary structure, a yoke secured to a second element, different from the first element, among the wing structure and the primary structure as well as a cylindrical rod secured to the lug and the yoke and forming a pivot axis parallel to the vertical direction, the lug comprising an oblong hole for housing the cylindrical rod which has a large dimension oriented in the longitudinal direction in order to allow the lug to move in the longitudinal direction relative to the yoke.

[0023] According to another characteristic, the second wing attachment comprises a second pivot axis parallel to a horizontal transverse direction perpendicular to the longitudinal direction.

[0024] According to another characteristic, the second wing attachment comprises a lug secured to a first element among the wing structure and the primary structure, a yoke secured to a second element, different from the first element, among the wing structure and the primary structure as well as a cylindrical rod secured to the lug and the yoke and forming the second pivot axis, the ball joint being interposed between the lug and the cylindrical rod.

[0025] According to another characteristic, each leg or plate comprises two walls pressed against each other.

[0026] According to another characteristic, each yoke comprises two parallel wings each comprising two walls pressed against each other.

[0027] Other characteristics and advantages will emerge from the description of the invention which follows, a description given by way of example only, with reference to the appended drawings, among which:

[0028] [Fig-1] is a perspective view of an aircraft,

[0029] [Fig.2] is a schematic side view of a propulsion assembly and a engine attachment system without fairings illustrating an embodiment of the prior art,

[0030] [Fig.3] is a perspective view of an engine attachment system illustrating a mode of implementation of the prior art,

[0031] [Fig.4] is a perspective view of a wing, a propulsion assembly and a engine attachment system illustrating an embodiment of the invention,

[0032] [Fig.5] is a perspective view of the wing attachments of an attachment system engine illustrating a first embodiment of the invention,

[0033] [Fig.6] is a schematic side view of the wing attachments visible in [Fig.5],

[0034] [Fig.7] is a schematic top view of the wing attachments of a system engine attachment illustrating a second embodiment of the invention,

[0035] [Fig.8] is a schematic side view of the wing attachments visible in [Fig.7],

[0036] [Fig.9] is a schematic top view of the wing attachments of a system engine attachment illustrating a third embodiment of the invention,

[0037] [Fig. 10] is a schematic side view of the wing attachments visible in [Fig.9],

[0038] [Fig. 11] is a section along line XI-XI of [Fig. 10] of a wing attachment illustrating an embodiment of the invention,

[0039] [Fig. 12] is a schematic top view of the wing attachments of an engine attachment system illustrating a fourth embodiment of the invention, and

[0040] [Fig. 13] is a schematic side view of the wing attachments visible in [Fig. 12]

[0041] According to one embodiment, an aircraft comprises at least one wing 40 as well as at least one propulsion assembly 42 connected to the wing 40 by at least one engine attachment system 44.

[0042] According to one embodiment, the wing 40 comprises a wing structure 46 as well as an aerodynamic wall 48 supported by the wing structure 46, the latter comprising at least first and second spars 46.1, 46.2 spaced apart in the longitudinal direction X as well as ribs connecting the first and second spars 46.1, 46.2.

[0043] According to one embodiment, the propulsion assembly 42 comprises at least one engine 42.1, a propeller 42.2 and a gearbox 42.3 connecting the engine 42.1 and the propeller 42.2. The propeller 42.2 defines a thrust axis substantially coincident with its axis of rotation.

[0044] According to one configuration, the engine 42.1 is a turbomachine powered by fuel (hydrogen, kerosene or others). According to another configuration, the propulsion assembly 42 comprises several electric motors as well as a set of fuel cells for supplying electrical energy to the electric motors. Of course, the invention is not limited to these configurations. Thus, the propulsion assembly 42 could comprise a double-flow turbojet.

[0045] The propulsion assembly 42 also comprises a fairing 42.4 for enveloping the engine(s) and its (their) equipment. This fairing 42.4 can take different forms depending on the type of engine.

[0046] The engine attachment system 44 comprises a primary structure 50, engine attachments 52 connecting the primary structure 50 and the propulsion assembly 42, wing attachments 54, 56, 58 connecting the primary structure 50 and the wing 40 as well as at least one fairing enveloping in particular the primary structure 50.

[0047] According to one configuration, the primary structure 50 comprises a front hoop 60 connected by several engine attachments 52 to a front zone of the propulsion assembly 42 as well as a rear hoop 62 connected by several engine attachments 52 to a rear zone of the propulsion assembly 42. In addition, the primary structure 50 comprises several reinforcements 64 connecting the front and rear hoops 60, 62 so as to form a lattice structure.

[0048] Of course, the invention is not limited to this embodiment for the primary structure 50. According to another configuration, the primary structure 50 could have a box structure.

[0049] The primary structure 50 and the engine attachments 52 are not described further because they are known to those skilled in the art and depend on the propulsion assembly 42.

[0050] Whatever the embodiment, the primary structure 50 comprises at least first and second interfaces 66, 68, each of which is connected to the wing 40 by wing attachments 54, 56, 58.

[0051] According to embodiments visible in Figures 7 to 13, the primary structure 50 comprises only first and second interfaces 66, 68, such as the front and rear hoops 60, 62 for example, connected by three wing attachments 54, 56, 58.

[0052] According to another embodiment visible in Figures 5 and 6, the primary structure 50 comprises first, second and third interfaces 66, 68, 70, such as at least one connecting rod 72 and the front and rear arches 60, 62, connected respectively by first, second and third wing attachments 54, 56, 58.

[0053] Of course, the primary structure 50 could comprise more than three interfaces 66, 68, 70 and more than three wing attachments 54, 56, 58.

[0054] At a minimum, the primary structure 50 comprises at least first and second interfaces 66, 68 and the engine attachment system 44 comprises at least three wing attachments 54, 56, 58 connecting said at least two interfaces 66, 68 and the wing structure 46. The primary structure 50 has a median longitudinal plane Py which corresponds to a vertical plane (when the aircraft is on the ground) containing the thrust axis of the propulsion assembly 42 and extends in a longitudinal direction X from front to rear.

[0055] Each wing attachment 54, 56, 58 comprises at least one pivot axis A54, A56, A58 or a swivel point.

[0056] According to a particular feature, the pivot axis A54, A56, A58 or the swivel point of each wing attachment 54, 56, 58 is positioned in the median longitudinal plane Py of the engine attachment system 44 or slightly spaced from the latter. By slightly spaced, it is meant that the pivot axis A54, A56, A58 or the swivel point is positioned in a vertical longitudinal plane parallel to the median longitudinal plane Py and spaced from the latter by a distance of less than 10 cm.

[0057] According to one arrangement, the first and second wing attachments 54, 56 are connected to a first spar 46.1 of the wing structure 46 and the third wing attachment 58 is connected to a second spar 46.2 of the wing structure 46 offset in the longitudinal direction towards the rear relative to the first spar 46.1. According to this arrangement, the first and second wing attachments 54, 56 are offset in height (in the vertical direction Z) relative to each other, the third wing attachment 58 being offset in the longitudinal direction towards the rear relative to the first and second wing attachments 54, 56. According to this arrangement, the first, second and third wing attachments 54, 56, 58 can be arranged in a vertical longitudinal plane.

[0058] According to one configuration, the first spar 46.1 corresponds to the front spar of the wing structure 46, the one positioned furthest to the front. The second spar 46.2 corresponds to the rear spar of the wing structure 46, the one positioned furthest to the rear. However, the second spar 46.2 could correspond to an intermediate spar located between the front and rear spars.

[0059] According to the different embodiments, the third pivot axis A58 of the third wing attachment 58 is parallel to the longitudinal direction X and contained in the median longitudinal plane Py. This third wing attachment 58 is located under the second spar 46.2 of the wing structure 46. According to one embodiment, the third wing attachment 58 comprises a tab 58.1 substantially parallel to a transverse plane Px and secured to a first element among the wing structure 46 and the primary structure 50, a yoke 58.2, having two wings positioned in transverse planes Px and secured to a second element (different from the first element) among the wing structure 46 and the primary structure 50 as well as a cylindrical rod 58.3 secured to the tab 58.1 and the yoke 58.2 and forming the third pivot axis A58.

[0060] According to a first embodiment visible in Figures 5 and 6, the first pivot axis A54 of the first wing attachment 54 is parallel to the vertical direction Z. This first wing attachment 54 is connected to a front face F46.1 of the first spar 46.1. According to one embodiment, the first wing attachment 54 comprises a tab 54.1, positioned in a horizontal plane Pz and secured to a first element among the wing structure 46 and the primary structure 50, a yoke 54.2 having wings positioned in horizontal planes Pz and secured to a second element (different from the first element) among the wing structure 46 and the primary structure 50 as well as a cylindrical rod 54.3 secured to the tab 54.1 and the yoke 54.2 and forming the first pivot axis A54.

[0061] According to this first embodiment, the second pivot axis A56 of the second wing attachment 56 is parallel to the longitudinal direction X. This second wing attachment 56 is located under the first spar 46.1 of the wing structure 46. According to one embodiment, the second wing attachment 56 comprises a tab 56.1 positioned in a transverse plane Px and secured to a first element among the wing structure 46 and the primary structure 50, a yoke 56.2 having wings positioned in transverse planes Px and secured to a second element (different from the first element) among the wing structure 46 and the primary structure 50 as well as a cylindrical rod 56.3 secured to the lug 56.1 and the yoke 56.2 and forming the second pivot axis A56.

[0062] According to this first embodiment, the first wing attachment 54 ensures the absorption of forces in the longitudinal direction X and of torques in the longitudinal direction X, the second wing attachment 56 ensures the absorption of forces in the horizontal and vertical transverse directions Y, Z and the third wing attachment 58 ensures the absorption of torques in the horizontal and vertical transverse directions Y, Z.

[0063] According to a second embodiment visible in Figures 7 and 8, the first pivot axis A54 of the first wing attachment 54 is parallel to the vertical direction Z. This first wing attachment 54 is connected to a front face F46.1 of the first spar 46.1. According to one embodiment, the first wing attachment 54 comprises a tab 54.1 positioned in a horizontal plane Pz and secured to a first element among the wing structure 46 and the primary structure 50, a yoke 54.2 having wings positioned in horizontal planes Pz and secured to a second element (different from the first element) among the wing structure 46 and the primary structure 50 as well as a cylindrical rod 54.3 secured to the tab 54.1 and the yoke 54.2 and forming the first pivot axis A54.

[0064] In addition, the second pivot axis A56 of the second wing attachment 56 is parallel to the vertical direction Z and aligned with the first pivot axis A54. This second wing attachment 56 is connected to a front face F46.1 of the first spar 46.1. According to one embodiment, the second wing attachment 56 comprises a lug 56.1 positioned in a horizontal plane Pz and secured to a first element among the wing structure 46 and the primary structure 50, a yoke 56.2 having wings positioned in horizontal planes Pz and secured to a second element (different from the first element) among the wing structure 46 and the primary structure 50 as well as a cylindrical rod 56.3 secured to the lug 56.1 and the yoke 56.2 and forming the second pivot axis A56.

[0065] According to this second embodiment, the first wing attachment 54 ensures the absorption of forces in the longitudinal direction X and of torques in the longitudinal direction X, the second wing attachment 56 ensures the absorption of forces in the horizontal transverse direction Y and of torques in the horizontal transverse direction Y and the third wing attachment 58 ensures the absorption of forces in the vertical direction Z and of torques in the vertical direction Z.

[0066] According to a third embodiment visible in Figures 9 to 11, the first wing attachment 54 comprises two pivot axes A54, A54' parallel to each other and to the vertical direction Z, slightly spaced from the median longitudinal plane Py. According to one embodiment, the first wing attachment 54 comprises at least one first leg 54.1 positioned in a horizontal plane Pz and secured to the wing structure 46, at least one second leg 54.2 positioned in a horizontal plane Pz and secured to the primary structure 50, at least one connecting rod 74 (also called a shackle) which extends between first and second ends 74.1, 74.2, a first cylindrical rod 74.3 secured to the first leg 54.1 and the first end 74.1 of the connecting rod 74 and forming the first pivot axis A54 as well as a second cylindrical rod 74.4 secured to the second leg 54.2 and the second end 74.2 of the connecting rod 74 and forming the second pivot axis A54'. According to one arrangement, the first wing attachment 54 comprises two connecting rods 74 positioned on either side of the first and second legs 54.1, 54.2. According to another arrangement, the first wing attachment 54 comprises two first legs 54.1 parallel to each other and slightly spaced apart forming a first yoke, two second legs 54.2 parallel to each other and slightly spaced apart forming a second yoke as well as a connecting rod 74 positioned between the legs 54.1, 54.2 of the first and second yokes.

[0067] As a variant, the first wing attachment 54 comprises a tab 54.1 positioned in a horizontal plane Pz and secured to a first element among the wing structure 46 and the primary structure 50, two tabs 54.2 positioned in horizontal planes Pz and slightly spaced apart forming a yoke 54.2 and secured to a second element (different from the first element) among the wing structure 46 and the primary structure 50 as well as a cylindrical rod 54.3 secured to the tab 54.1 and the yoke 54.2 and forming a pivot axis A54 parallel to the vertical direction Z. According to this variant, the tab 54.1 comprises an oblong hole for housing the cylindrical rod 54.3 having a large dimension oriented in the longitudinal direction X, greater than the diameter of the cylindrical rod 54.3, in order to allow the tab 54.1 to move in the longitudinal direction X by report to screed 54.2.

[0068] According to these two variants, the first wing attachment 54 comprises at least one pivot axis A54, A54' positioned in the median longitudinal plane Py or in a vertical longitudinal plane slightly spaced from the latter.

[0069] According to the third embodiment, the second pivot axis A56 of the second wing attachment 56 is parallel to the horizontal transverse direction Y. This second wing attachment 56 is connected to a front face F46.1 of the first spar 46.1. According to one embodiment, the second wing attachment 56 comprises a tab 56.1 positioned in a vertical longitudinal plane parallel to the median longitudinal plane Py and secured to a first element among the wing structure 46 and the primary structure 50, a yoke 56.2 having wings positioned in vertical longitudinal planes parallel to the median longitudinal plane Py and secured to a second element (different from the first element) among the wing structure 46 and the primary structure 50 as well as a cylindrical rod 56.3 secured to the lug 56.1 and the yoke 56.2 and forming the second pivot axis A56. According to this third embodiment, as illustrated in [Fig. 11], the second wing attachment 56 comprises a ball joint 76 interposed between the lug 56.1 and the cylindrical rod 56.3.

[0070] According to this third embodiment, the first wing attachment 54 ensures the absorption of torques in the lateral direction Y, the second wing attachment 56 ensures the absorption of forces in the three directions X, Y, Z and the third wing attachment 58 ensures the absorption of torques in the horizontal and vertical transverse directions Y, Z.

[0071] According to a fourth embodiment visible in Figures 12 and 13, the first pivot axis A54 of the first wing attachment 54 is parallel to the longitudinal direction X. This first wing attachment 54 is connected to a front face F46.1 of the first spar 46.1 and to a horizontal face of the primary structure 50. According to one embodiment, the first wing attachment 54 comprises a plate 54.1 positioned in a transverse plane Px and secured to a first element among the wing structure 46 and the primary structure 50, a yoke 54.2 having wings positioned in transverse planes Px and secured to a second element (different from the first element) among the wing structure 46 and the primary structure 50 as well as a cylindrical rod 54.3 secured to the plate 54.1 and the yoke 54.2 and forming the first pivot axis A54. According to one arrangement, the yoke 54.2 is integral with the primary structure 50. In addition, the plate 54.1 is connected to the front face F46.1 of the first side member 46.1 by two lugs 78 positioned on either side of the yoke 54.2.

[0072] In addition, the second pivot axis A56 of the second wing attachment 56 is parallel to the vertical direction Z. This second wing attachment 56 is connected to a front face F46.1 of the first spar 46.1. According to one embodiment, the second wing attachment 56 comprises a lug 56.1 positioned in a horizontal plane Pz and secured to a first element among the wing structure 46 and the primary structure 50, a yoke 56.2 having wings positioned in horizontal planes Pz and secured to a second element (different from the first element) among the wing structure 46 and the primary structure 50 as well as a cylindrical rod 56.3 secured to the lug 56.1 and the yoke 56.2 and forming the second pivot axis A56.

[0073] According to this fourth embodiment, the first wing attachment 54 ensures the absorption of forces in the vertical direction Z and of torques in the longitudinal direction X, the second wing attachment 56 ensures the absorption of forces in the longitudinal direction X and the horizontal transverse direction Y and the third wing attachment 58 ensures the absorption of torques in the horizontal transverse directions rhizotal and vertical Y, Z.

[0074] Of course, the invention is not limited to these four embodiments. Other embodiments are conceivable for the first, second and third wing attachments.

[0075] Whatever the embodiment, the first, second and third wing attachments 54, 56, 58 are arranged in a vertical longitudinal plane, which makes it possible to optimize the transmission of forces between the primary structure 50 and the wing structure 46, the forces being introduced into the wing structure 46 without offset or with a small offset relative to a vertical longitudinal plane.

[0076] The first, second and third wing attachments 54, 56, 58 are configured to ensure a transfer of forces and torques in the median longitudinal plane Py or in a vertical longitudinal plane slightly spaced from the latter. According to one configuration, the first, second and third wing attachments 54, 56, 58 each have a connection having at least one pivot axis and / or a swivel point positioned in the median longitudinal plane Py of the engine attachment system 44 or in a vertical longitudinal plane slightly spaced from the latter. This solution makes it possible to introduce into the wing structure 46 the forces without offset or with a slight offset relative to a vertical longitudinal plane.

[0077] The first, second and third wing attachments 54, 56, 58 are configured to form a set of isostatic connections between the wing structure 46 and the primary structure 50.

[0078] The different embodiments involve few parts to be assembled, which makes it possible to reduce the on-board mass, simplify assembly and obtain rapid assembly.

[0079] According to one configuration, to enhance safety, each tab or plate 54.1, 56.1, 58.1 comprises two walls pressed against each other. In addition, each yoke 54.2, 56.2, 58.2 comprises two wings parallel to each other, each comprising two walls pressed against each other.

Claims

Claims

1. Aircraft comprising at least one wing (40), at least one propulsion assembly (42) and at least one engine attachment system (44) connecting the propulsion assembly (42) and the wing (40), said wing (40) having a wing structure (46), said engine attachment system (44) comprising a primary structure (50), engine attachments (52) connecting the primary structure (50) and the propulsion assembly (42) and at least first, second and third wing attachments (54, 56, 58) connecting the primary structure (50) and the wing structure (46), the primary structure (50) having a median longitudinal plane (Py) and extending in a longitudinal direction (X) from front to rear;characterized in that the first and second wing attachments (54, 56) are offset in height relative to each other, the third wing attachment (58) being offset in the longitudinal direction (X) towards the rear relative to the first and second wing attachments (54, 56).;

2. Aircraft according to claim 1, characterized in that the first, second and third wing attachments (54, 56, 58) are configured to form a set of isostatic connections between the wing structure (46) and the primary structure (50).

3. Aircraft according to claim 1 or 2, characterized in that the wing structure (46) comprises a front spar (46.1) and a second spar (46.2) offset in the longitudinal direction (X) towards the rear relative to the first spar (46.1) and in that the first and second wing attachments (54, 56) are connected to the front spar (46.1), the third wing attachment (58) being connected to the second spar (46.2).

4. Aircraft according to one of the preceding claims, characterized in that the first, second and third wing attachments (54, 56, 58) each have a connection comprising at least one pivot axis and / or a swivel point positioned in the median longitudinal plane (Py) or in a vertical longitudinal plane slightly spaced from the median longitudinal plane (Py).

5. Aircraft according to the preceding claim, characterized in that the third wing attachment (58) comprises a third pivot axis (A58) parallel to the longitudinal direction (X) and contained in the median longitudinal plane (Py).

6. Aircraft according to one of claims 4 to 5, characterized in that the first wing attachment (54) comprises a first pivot axis (A54) parallel to a vertical direction (Z) and in that the second wing attachment (56) comprises a second pivot axis (A56) parallel to the longitudinal direction (X).

7. Aircraft according to one of claims 4 to 5, characterized in that the first wing attachment (54) comprises a first pivot axis (A54) parallel to a vertical direction (Z) and in that the second wing attachment (56) comprises a second pivot axis (A56) aligned with the first pivot axis (A54).

8. Aircraft according to one of claims 4 to 5, characterized in that the first wing attachment (54) comprises a first pivot axis (A54) parallel to the longitudinal direction (X) and in that the second wing attachment (56) comprises a second pivot axis (A56) parallel to a vertical direction (Z).

9. Aircraft according to one of claims 6 to 8, characterized in that each of the first, second and third wing attachments (54, 56, 58) comprises a lug or a plate (54.1, 56.1, 58.1) secured to a first element among the wing structure (46) and the primary structure (50), a yoke (54.2) secured to a second element, different from the first element, among the wing structure (46) and the primary structure (50) as well as a cylindrical rod (54.3) secured to the lug or the plate (54.1) and to the yoke (54.2) and forming the first, second or third pivot axis (A54, A56, A58).

10. Aircraft according to one of claims 4 to 5, characterized in that the first wing attachment (54) comprises at least one pivot axis (A54, A54') parallel to the vertical direction (Z) and in that the second wing attachment (56) comprises a ball joint (76).

11. Aircraft according to the preceding claim, characterized in that the first wing attachment (54) comprises at least one first lug (54.1) secured to the wing structure (46), at least one second lug (54.2) secured to the primary structure (50), at least one link (74) which extends between first and second ends (74.1, 74.2), a first cylindrical rod (74.3) secured to the first lug (54.1) and to the first end (74.1) of the link (74) and forming a first pivot axis (A54) parallel to the vertical direction (Z) as well as a second cylindrical rod (74.4) secured to the second lug (54.2) and to the second end (74.2) of the link (74) and forming a second pivot axis (A54') parallel to the vertical direction (Z).

12. Aircraft according to claim 10, characterized in that the first wing attachment (54) comprises a lug (54.1) secured to a first element among the wing structure (46) and the primary structure (50), a yoke (54.2) secured to a second element, different from the first element, among the wing structure (46) and the primary structure (50) as well as a cylindrical rod (54.3) secured to the lug (54.1) and the yoke (54.2) and forming a pivot axis (A54) parallel to the vertical direction (Z), the lug (54.1) comprising an oblong hole for housing the cylindrical rod (54.3) which has a large dimension oriented in the longitudinal direction (X) in order to allow the lug (54.1) to move in the longitudinal direction (X) relative to the yoke (54.2).

13. Aircraft according to one of claims 10 to 12, characterized in that the second wing attachment (56) comprises a second pivot axis (A56) parallel to a horizontal transverse direction (Y) perpendicular to the longitudinal direction (X).

14. Aircraft according to one of claims 10 to 13, characterized in that the second wing attachment (56) comprises a lug (56.1) secured to a first element among the wing structure (46) and the primary structure (50), a yoke (56.2) secured to a second element, different from the first element, among the wing structure (46) and the primary structure (50) as well as a cylindrical rod (56.3) secured to the lug (56.1) and the yoke (56.2) and forming the second pivot axis (A56), the ball joint (76) being interposed between the lug (56.1) and the cylindrical rod (56.3).

15. Aircraft according to one of claims 9, 11 to 14, characterized in that each tab or plate (54.1, 56.1, 58.1) comprises two walls pressed against each other.

16. Aircraft according to one of claims 9, 12 to 14, characterized in that each yoke (54.2, 56.2, 58.2) comprises two parallel wings each comprising two walls pressed against each other.

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