Aircraft comprising at least one engine mounting system that has a reduced vertical footprint

Abstract

Aircraft comprising at least one engine mounting system with a reduced vertical footprint. The invention relates to an aircraft comprising at least one engine mounting system (60) connecting a primary structure (58) of a mast and an engine (56), comprising: a right interface (66) connected to the right lateral face (64.1) of the primary structure (58), a left interface (68) connected to the left lateral face (64.2) of the primary structure (58), first and second shackles (70, 78) connecting said right and left interfaces (66, 68) to the engine (56) by means of engine connection shafts (72, 80) and interface connection shafts (74, 76, 82), a right emergency connection shaft (84) cooperating with the right interface (66) and the engine (56), a left emergency connection shaft (86) cooperating with the left interface (68) and the motorization (56).This arrangement allows for a relatively compact motor mounting system (60) in the vertical direction. Figure 5.

Description

Title of the invention: Aircraft comprising at least one engine attachment system which has a reduced vertical size

[0001] The present application relates to an aircraft comprising at least one engine attachment system which has a reduced vertical size.

[0002] According to an embodiment visible in Figures 1 and 2, an aircraft 10 comprises several propulsion units 12 positioned under each of the wings 14 of the aircraft. Each propulsion unit 12 comprises a motorization 16, a nacelle (not shown in [Fig.2]) positioned around the motorization 16 as well as a mast 18 connecting the motorization 16 and the wing 14. The mast 18 comprises a primary structure 20 which is connected to the motorization 16 by an engine attachment system 22 and to the wing 14 by a wing attachment system 24.

[0003] For the present invention, a longitudinal direction X is substantially parallel to the axis of rotation A16 of the motorization 16. A vertical median plane PMV is a vertical plane passing through the axis of rotation A16. A transverse plane is a plane perpendicular to the axis of rotation A16. A horizontal transverse direction Y is a direction horizontal and perpendicular to the axis of rotation A16. A vertical direction is noted Z in the various figures. The terms front / rear refer to the direction of flow of the air flows which flow in the longitudinal direction X, from front to rear.

[0004] The engine attachment system 22 comprises a front engine attachment system 26, a rear engine attachment system 28 and a pair of thrust rods 30 ensuring the absorption of thrust forces.

[0005] According to an embodiment visible in [Fig.3], for the rear engine attachment system 28, the primary structure 20 comprises a sole 32 positioned approximately in a horizontal plane.

[0006] In addition, the rear engine attachment system 28 comprises a transverse beam 34 which has a bearing face F34 pressed against the sole 32, the transverse beam 34 being connected to the primary structure 20 by connecting elements 36.

[0007] The rear engine attachment system 28 comprises: a. a first L-shaped shackle 38 which has a first end 38.1, a second 38.2 and an intermediate zone 38.3, i. a first motor connecting axis 40 connecting the first end 38.1 of the first shackle 38 and the motorization 16, ii. a first beam connecting axis 42 connecting the second end 38.2 of the first shackle 38 and the transverse beam 34, iii. a second beam connecting axis 44 connecting the intermediate zone 38.3 of the first shackle 38 and the transverse beam 34; b. a second shackle 46 which has first and second ends 46.1, 46.2, i. a second motor connecting shaft 48 connecting the first end 46.1 of the second shackle 46 and the motorization 16, ii. a third beam connecting axis 50 connecting the second end 46.2 of the second shackle 46 and the transverse beam 34; c. an emergency connecting axis 52, directly connecting the transverse beam 34 and the motorization 16 in the event of a failure, positioned at the level of the vertical median plane PMV.

[0008] The connecting axes 40, 42, 44, 48, 50, 52 are substantially parallel to each other and to the longitudinal direction X.

[0009] According to the embodiment visible in [Fig. 3], the transverse beam 34 is necessarily positioned under the primary structure 20 of the mast 18. This arrangement leads to a significant bulk in the vertical direction, which tends to limit the diameter of the motorization 16 and more particularly of its fan casing 16.1.

[0010] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0011] To this end, the invention relates to an aircraft comprising at least one engine, at least one primary structure of a mast and at least one engine attachment system connecting the primary structure and the engine, said primary structure comprising a lower face as well as right and left lateral faces positioned on either side of a vertical median plane, the engine attachment system comprising: a. at least one first L-shaped shackle, positioned in a transverse plane, which has first and second ends as well as an intermediate zone, b. a first motor connection axis connecting the first end of the first shackle and the motorization, c. at least one second shackle, positioned in a transverse plane, which has first and second ends, d. a second motor connecting shaft connecting the first end of the second shackle and the motorization.

[0012] According to the invention, the engine attachment system comprises: a. a right interface connected to the right lateral face of the primary structure, b. a left interface connected to the left lateral face of the primary structure, c. a first interface connecting pin connecting the second end of the first shackle and at least one first interface among the right and left interfaces, d. a second interface connecting axis connecting the intermediate zone of the first shackle and the first interface, e. a third interface connecting axis connecting the second end of the second shackle and at least one second interface, different from the first interface, among the first and second interfaces, f. a right emergency connecting shaft cooperating with the right interface and the motorization, g. a left emergency connecting axle cooperating with the left interface and the motorization.

[0013] According to this arrangement, the right and left interfaces not being positioned under the primary structure but on its lateral faces, the motor attachment system is relatively compact in the vertical direction, which makes it possible to install motors with larger diameters.

[0014] According to another characteristic, the first, second and third interface connection axes are located at the level of a lower plane passing through the lower face of the primary structure or offset upwards relative to this lower plane.

[0015] According to another characteristic, the first interface among the right and left interfaces comprises, for each of the first and second interface connection axes, at least one through-orifice housing the first or second interface connection axis and dimensioned so that the first or second interface connection axis is immobile in translation, in a transverse plane, relative to the first interface. In parallel, the second interface among the right and left interfaces comprises at least one through-orifice housing the third interface connection axis and dimensioned so that the third interface connection axis is immobile in translation, in a transverse plane, relative to the second interface.

[0016] According to another characteristic, each right or left interface comprises front and rear wings positioned in transverse planes, parallel to each other and slightly spaced apart, as well as a right or left base connecting the front and rear wings, said right or left base being connected to the primary structure by at least one connecting element.

[0017] According to another characteristic, the engine attachment system comprises at least one reinforcing bracket having a first wall pressed against one of the front and rear wings of the right and left interfaces as well as a second wall pressed against the right or left lateral face of the primary structure and connected to the primary structure by at least one connecting element; the first wall comprising, for each of the first, second and third interface connection axes passing through it, a through orifice sized so that the first, second or third interface connection axis is immobile in translation, in a transverse plane, relative to the first wall.

[0018] According to another characteristic, for each right and left interface, the engine attachment system comprises a front reinforcement bracket, positioned at the front of the right or left interface, comprising a first wall pressed against the front wing of the right or left interface and a second wall pressed against the right or left lateral face of the primary structure as well as a rear reinforcement bracket, positioned at the rear of the right or left interface, comprising a first wall pressed against the rear wing of the right or left interface and a second wall pressed against the right or left lateral face of the primary structure.

[0019] According to another characteristic, each front and rear wing of each right and left interface comprises a side oriented towards the motorization as well as an extension positioned at the level of said side and offset towards the motorization relative to the rest of said side, said extension having a through orifice which houses the right or left emergency connecting axis.

[0020] According to another characteristic, the motorization comprises, for each right or left emergency connecting shaft, a transverse flange positioned at least partially between the front and rear wings of the corresponding right or left interface, said transverse flange comprising a through orifice which houses the right or left emergency connecting shaft.

[0021] According to another characteristic, the motorization comprises, for the first motor connection axis, a first yoke which has two wings between which the first shackle is positioned as well as, for the second motor connection axis, a second yoke which has two wings between which the second shackle is positioned.

[0022] According to another characteristic, the engine attachment system comprises, for each right or left emergency connection shaft, a clearance between the right or left emergency connection shaft and one element among the motorization and the right or left interface.

[0023] According to another characteristic, the motorization comprises, for each of the first and second motor connection axes, at least one through orifice, which houses the first or second motor connection axis, dimensioned so that each of the first and second motor connection axes is immobile in translation, in a transverse plane, relative to the motorization.

[0024] 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:

[0025] [Fig.l] is a side view of an aircraft,

[0026] [Fig.2] is a side view of a motorization,

[0027] [Fig.3] is a front view of an engine attachment system which illustrates a mode of implementation of the prior art,

[0028] [Fig.4] is a perspective view of an engine attachment system which illustrates a embodiment of the invention,

[0029] [Fig.5] is a front view of the engine attachment system visible in [Fig.4],

[0030] [Fig.6] is a side view of the engine attachment system visible in [Fig.4],

[0031] [Fig.7] is a front view of the engine attachment system visible in [Fig.4] illustrating a failure at one of the shackles,

[0032] [Fig.8] represents side views of the engine attachment system visible on the [Fig.4] illustrating different failures.

[0033] An aircraft comprises at least one engine 56, at least one primary structure 58 of a mast as well as at least one engine attachment system 60 connecting the engine 56 and the primary structure 58. According to one arrangement, this engine attachment system 60, called rear, is spaced from the fan casing of the engine 56.

[0034] The motorization 56 has a vertical median plane PMV and a substantially cylindrical casing at the right of the motor attachment system 60.

[0035] According to an embodiment visible in Figures 4 to 8, the primary structure 58 comprises a lower face 62 substantially perpendicular to the vertical median plane PMV as well as right and left lateral faces 64.1, 64.2 positioned on either side of the vertical median plane PMV and above the lower face 62. According to one configuration, each right or left lateral face 64.1, 64.2 forms, in a transverse plane, an angle of between 0 and 20° with the vertical median plane PMV, the right and left lateral faces 64.1, 64.2 being flared upwards.

[0036] The engine attachment system 60 comprises: a. a right interface 66 connected to the right lateral face 64.1 of the primary structure 58, b. a left interface 68 connected to the left lateral face 64.2 of the primary structure 58, c. at least one first L-shaped shackle 70, positioned in a transverse plane, which has a first end 70.1, a second end 70.2 and an intermediate zone 70.3 located at the level of the bent zone of the first L-shaped shackle 70, i. a first motor connecting shaft 72 connecting the first end 70.1 of the first shackle 70 and the motorization 56, ii. a first interface connecting axis 74 connecting the second end 70.2 of the first shackle 70 and a first interface among the in- right and left interfaces 66, 68, iü. a second interface connecting axis 76 connecting the intermediate zone 70.3 of the first shackle 70 and the first interface; d. at least one second shackle 78, positioned in a transverse plane, which has first and second ends 78.1, 78.2, i. a second motor connecting shaft 80 connecting the first end 78.1 of the second shackle 78 and the motorization 56, ii. a third interface connecting axis 82 connecting the second end 78.2 of the second shackle 78 and a second interface among the right and left interfaces 66, 68; e. a right emergency connecting shaft 84 cooperating with the right interface 66 and the motorization 56, f. a left emergency connecting shaft 86 cooperating with the left interface 68 and the motorization 56.

[0037] The engine connection, interface connection and emergency connection axes are parallel to each other and to the longitudinal direction X.

[0038] According to this arrangement, the right and left interfaces 66, 68 are two distinct and separate elements. These right and left interfaces 66, 68 not being positioned under the primary structure 58 but on its lateral faces, the motor attachment system 60 is relatively compact in the vertical direction, which makes it possible to install motors 56 of larger diameters.

[0039] According to one configuration, the interface connection axes 74, 76, 82 are located at a lower plane passing through the lower face 62 of the primary structure 58 or offset upwards relative to this lower plane. This arrangement makes it possible to further reduce the vertical size.

[0040] According to one embodiment, the first interface connection axis 74 connected to the second end 70.2 of the first L-shaped shackle 70 is positioned between the primary structure 58 and the second interface connection axis 76 connected to the intermediate zone 70.3 of the first shackle 70.

[0041] According to one arrangement, each first L-shaped shackle 70 is connected to the right interface 66 and each second shackle 78 is connected to the left interface 68. Alternatively, each first L-shaped shackle 70 could be connected to the left interface 68 and each second shackle 78 could be connected to the right interface 66.

[0042] Each first or second shackle 70, 78 comprises, for each motor connection shaft 72, 80 and each interface connection shaft 74, 76, 82, a through-hole, which houses the motor connection shaft 72, 80 or the interface connection shaft 74, 76, 82, dimensioned so that each motor or interface connection shaft 72, 74, 76, 80, 82 is immobile in translation, in a transverse plane, relative to the first or second shackle 70, 78.

[0043] The first interface among the right and left interfaces 66, 68 comprises, for each of the first and second interface connection axes 74, 76, at least one through-orifice, which houses the first or second interface connection axis 74, 76, and dimensioned so that the first or second interface connection axis 74, 76 is immobile in translation, in a transverse plane, relative to the first interface. In addition, the second interface among the right and left interfaces 66, 68 comprises at least one through-orifice, which houses the third interface connection axis 82, and dimensioned so that the third interface connection axis 82 is immobile in translation, in a transverse plane, relative to the second interface.Thus, in normal operation, each interface connection axis 74, 76, 82 is configured to ensure transmission of forces, at least in a transverse plane, between the right and left interfaces 66, 68 as well as the first and second shackles 70, 78.

[0044] The motorization 56 comprises, for each motor connection shaft 72, 80, at least one through-orifice, which houses the motor connection shaft 72, 80, dimensioned so that each motor connection shaft 72, 80 is immobile in translation, in a transverse plane, relative to the motorization 56. Thus, in normal operation, each motor connection shaft 72, 80 is configured to ensure transmission of forces, at least in a transverse plane, between the motorization 56 and the corresponding first or second shackle 70, 78.

[0045] The right interface 66 comprises at least one right wing 66.1 positioned in a transverse plane and crossed by at least one of the first, second and third interface connection axes 74, 76, 82. The left interface 68 comprises at least one left wing 68.1 positioned in a transverse plane and crossed by at least one of the first, second and third interface connection axes 74, 76, 82.

[0046] According to one configuration, the right interface 66 comprises front and rear right wings 66.1, 66.2 positioned in transverse planes, parallel to each other and slightly spaced apart, as well as a right base 66.3 connecting the front and rear right wings 66.1, 66.2, said right base 66.3 having a contact face F66.3 pressed against the right lateral face 64.1 of the primary structure 58 and being connected to the primary structure 58 by at least one connecting element 66.4, generally several connecting elements 66.4 distributed in the vertical direction.

[0047] The left interface 68 comprises front and rear left wings 68.1, 68.2 positioned in transverse planes, parallel to each other and slightly spaced apart, as well as a left base 68.3 connecting the front and rear left wings 68.1, 68.2, said left base 68.3 having a contact face F68.3 pressed against the left lateral face 64.2 of the primary structure 58 and being connected to the primary structure 58 by at least a connecting element 68.4, generally several connecting elements 68.4 distributed in the vertical direction.

[0048] In addition, the engine attachment system 60 comprises a single first shackle 70, inserted between the front and rear wings 66.1, 66.2, 68.1, 68.2 of the right or left interface 66, 68, as well as a single second shackle 78 inserted between the front and rear wings 66.1, 66.2, 68.1, 68.2 of the right or left interface 66, 68.

[0049] Finally, the motorization 56 comprises, for the first motor connection axis 72, a first yoke 56.1 which has two wings between which the first shackle 70 is positioned as well as, for the second motor connection axis 80, a second yoke 56.2 which has two wings between which the second shackle 78 is positioned.

[0050] According to another configuration, each right and left interface 66, 68 comprises a single right or left wing 66.1, 68.1. In addition, the engine attachment system 60 comprises two first shackles 70 positioned on either side of a first wing among the right and left wings as well as two second shackles 78 positioned on either side of a second wing, different from the first wing, among the right and left wings.

[0051] Whatever the configuration, each right or left interface 66, 68 has a contact face 66.3, 68.3, pressed against the right or left lateral face 64.1, 64.2, which does not extend against the lower face 62 and therefore beyond the right or left lateral face 64.1, 64.2.

[0052] According to one embodiment, each right or left wing 66.1, 66.2, 68.1, 68.2 has a substantially triangular outline comprising a first side C1, pressed against the primary structure 58, which extends from the lower face 62 of the primary structure 58, a second side C2 positioned approximately in the extension of the lower face 62 of the primary structure 58 and approximately in a horizontal plane, as well as a third side C3, the second and third sides C2, C3 being connected by a rounded apex at the level of which is positioned the second interface connection axis 76 connected to the intermediate zone 70.3 of the first shackle 70 or the third interface connection axis 82 connected to the second end 78.2 of the second shackle 78. The front and rear wings 66.1, 66.2, 68.1, 68.2 of each right or left interface 66, 68 have the same outline. Whatever the embodiment, each right or left wing 66.1, 66.2, 68.1, 68.2 includes a side facing the motorization 56. .

[0053] According to one embodiment, the engine attachment system 60 comprises at least one reinforcing bracket 88 having a first wall 88.1 pressed against one of the right or left, front or rear wings 66.1, 66.2, 68.1, 68.2 as well as a second wall 88.2 pressed against the right or left lateral face 64.1, 64.2 and connected to the primary structure 58 by at least one connecting element 88.3, ​​generally several connecting elements 88.3 distributed in the vertical direction. Each first wall 88.1 comprises, for each interface connecting axis 74, 76, 82 which passes through it, a through-orifice, which houses the interface connecting axis 74, 76, 82, dimensioned so that the interface connecting axis 74, 76, 82 is immobile in translation, in a transverse plane, relative to the first wall 88.1. Thus, in normal operation, each of the first, second and third interface connecting axes 74, 76, 82 is configured to ensure transmission of forces, at least in a transverse plane, between the first wall 88.1 of the reinforcing bracket 88 and the first or second shackle 70, 78 crossed by the first, second or third interface connecting axis 74, 76, 82.

[0054] According to one configuration, the engine attachment system 60 comprises, for each front and rear wing 66.1, 66.2, 68.1, 68.2 of each right and left interface 66, 68, a reinforcing bracket 88, 88'. Thus, for each right and left interface 66, 68, the engine attachment system 60 comprises a front reinforcement bracket 88, positioned at the front of the right or left interface 66, 68, comprising a first wall 88.1 pressed against the front wing 66.1, 68.1 of the right or left interface 66, 68 and a second wall 88.2 pressed against the right or left lateral face 64.1, 64.2 of the primary structure 58, at the front of the right or left interface 66, 88, as well as a rear reinforcement bracket 88', positioned at the rear of the right or left interface 66, 68, comprising a first wall 88.1 pressed against the rear wing 66.2, 68.2 ... and a rear against the right or left side face 64.1, 64.2 of the primary structure 58, at the rear of the right or left interface 66, 68. .

[0055] According to one embodiment, each wing 66.1, 66.2, 68.1, 68.2 of each right and left interface 66, 68 comprises an extension 90 positioned at its second side C2 oriented towards the motorization 56 and offset towards the motorization 56 relative to the rest of the second side C2, said extension 90 having a through orifice 92 provided to house the right or left emergency connecting shaft 84, 86.

[0056] According to a first configuration, when the right or left interface 66, 68 comprises a single right or left wing 66.1, 68.1, the motorization 56 comprises, for each right or left emergency connecting shaft 84, 86, a yoke which has two wings between which the extension 90 is positioned at least partially, each of the wings each comprising a through-orifice provided to house the right or left emergency connecting shaft 84, 86.

[0057] According to a second configuration, when the right or left interface 66, 68 comprises front and rear wings 66.1, 66.2, 68.1, 68.2, the motorization 56 comprises, for each right or left emergency connecting axis 84, 86, a transverse flange 94 positioned at least partially between the front and rear wings 66.1, 66.2, 68.1, 68.2 of the corresponding right or left interface 66, 68, said transverse flange 94 comprising a through hole provided to house the right or left emergency connecting shaft 84, 86.

[0058] Regardless of the configuration, the right or left emergency connecting shaft 84, 86 provides a direct connection between each right or left interface 66, 68 and the motorization 56 in the event of a failure. The motor attachment system 60 comprises, for each right or left emergency connecting shaft 84, 86, a clearance between the right or left emergency connecting shaft 84, 86 and one element among the motorization 56 and the right or left interface 66, 68. This clearance is calibrated to allow a clearance in a transverse plane between the motorization 56 and the right or left interface 66, 68 in operation.

[0059] According to a first arrangement, the right or left emergency connecting shaft 84, 86 is secured to the right or left interface 66, 68 and a clearance is provided between the right or left emergency connecting shaft 84, 86 and the motorization 56.

[0060] According to a second arrangement, the right or left emergency connecting shaft 84, 86 is secured to the motorization 56 and a clearance is provided between the right or left emergency connecting shaft 84, 86 and the right or left interface 66, 68. Thus, according to the second configuration, the right or left emergency connecting shaft 84, 86 is secured to the transverse flange 94 of the motorization 56 and a clearance is provided between the right or left emergency connecting shaft 84, 86 and each front and rear wing 66.1, 66.2, 68.1, 68.2 of the corresponding right or left interface 66, 68.

[0061] As illustrated in Figures 5 and 6, in normal operation, the first and second motor connection axes 72, 80 as well as the first, second and third interface connection axes 74, 76, 82 are configured to ensure transmission of forces between the motorization 56 and the right and left interfaces 66, 68 and possibly the reinforcing brackets 88, 88'. In addition, the connecting elements 66.4, 68.4 and 88.3 connecting the right and left interfaces 66, 68 and the reinforcing brackets 88, 88' to the primary structure 58 are configured to ensure transmission of forces between, on the one hand, the right and left interfaces 66, 68 and the reinforcing brackets 88, 88' and, on the other hand, the primary structure 58.

[0062] As illustrated in [Fig.7], in the event of damage to a shackle 70, 78, the right or left emergency connecting shaft 84, 86, connected to the right or left interface 66, 68 to which the damaged shackle 70, 78 is connected, is configured to ensure, in addition to the undamaged shackle, the transmission of forces between the motorization 56 and the right and left interfaces 66, 68 and compensate for this failure.

[0063] As illustrated in part (A) of [Fig.8], in the event of failure of the right or left interface 66, 68, the front and rear reinforcement brackets 88, 88', positioned on either side of the damaged right or left interface 66, 68, are configured to compensate for this failure and ensure at least partial transmission of the forces between the motorization 56 and the primary structure 58.

[0064] As illustrated in part (B) of [Fig.8], in the event of failure of the front reinforcement bracket 88, the right or left interface 66, 68 and the rear reinforcement bracket 88', positioned against the same right or left lateral face 64.1, 64.2 of the primary structure 58 as the damaged front reinforcement bracket 88, are configured to compensate for this failure and ensure at least partial transmission of the forces between the motorization 56 and the primary structure 58.

[0065] As illustrated in part (C) of [Fig.8], in the event of failure of the rear reinforcement bracket 88', the right or left interface 66, 68 and the front reinforcement bracket 88, positioned against the same right or left lateral face 64.1, 64.2 of the primary structure 58 as the damaged rear reinforcement bracket 88', are configured to compensate for this failure and ensure at least partial transmission of the forces between the motorization 56 and the primary structure 58.

Claims

Claims

1. Aircraft comprising at least one engine (56), at least one primary structure (58) of a mast and at least one engine attachment system (60) connecting the primary structure (58) and the engine (56), said primary structure (58) comprising a lower face (62) as well as right and left lateral faces (64.1, 64.2) positioned on either side of a vertical median plane (VMP), the engine attachment system comprising: a. at least one first L-shaped shackle (70), positioned in a transverse plane, which has first and second ends (70.1, 70.2) as well as an intermediate zone (70.3), b. a first motor connection axis (72) connecting the first end (70.1) of the first shackle (70) and the motorization (56), c. at least one second shackle (78), positioned in a transverse plane, which has first and second ends (78.1,78.2), d. a second motor connecting shaft (80) connecting the first end (78.1) of the second shackle (78) and the motorization (56), characterized in that the engine attachment system comprises: a. a right interface (66) connected to the right lateral face (64.1) of the primary structure (58), b. a left interface (68) connected to the left lateral face (64.2) of the primary structure (58), c. a first interface connecting pin (74) connecting the second end (70.2) of the first shackle (70) and at least one first interface among the right and left interfaces (66, 68), d. a second interface connecting axis (76) connecting the intermediate zone (70.3) of the first shackle (70) and the first interface, e. a third interface connecting axis (82) connecting the second end (78.2) of the second shackle (78) and at least one second interface, different from the first interface, among the first and second interfaces (66, 68), f. a right emergency connecting shaft (84) cooperating with the right interface (66) and the motorization (56), g. a left emergency connecting shaft (86) cooperating with the left interface (68) and the motorization (56).

2. Aircraft according to the preceding claim, characterized in that the first, second and third interface connection axes (74, 76, 82) are located at the level of a lower plane passing through the lower face (62) of the primary structure (58) or offset upwards relative to this lower plane.

3. Aircraft according to one of the preceding claims, characterized in that the first interface among the right and left interfaces (66, 68) comprises, for each of the first and second interface connection axes (74, 76), at least one through-orifice, which houses the first or second interface connection axis (74, 76), dimensioned so that the first or second interface connection axis (74, 76) is immobile in translation, in a transverse plane, relative to the first interface and in that the second interface among the right and left interfaces (66, 68) comprises at least one through-orifice, which houses the third interface connection axis (82), dimensioned so that the third interface connection axis (82) is immobile in translation, in a transverse plane, relative to the second interface.

4. Aircraft according to one of the preceding claims, characterized in that each right or left interface (66, 68) comprises front and rear wings (66.1, 66.2, 68.1, 68.2) positioned in transverse planes, parallel to each other and closely spaced, as well as a right or left base (66.3, 68.3) connecting the front and rear wings (66.1, 66.2, 68.1, 68.2), said right or left base (66.3, 68.3) being connected to the primary structure (58) by at least one connecting element (66.4, 68.4).

5. Aircraft according to the preceding claim, characterized in that the engine attachment system (60) comprises at least one reinforcing bracket (88) having a first wall (88.1) pressed against one of the front and rear wings (66.1, 66.2, 68.1, 68.2) of the right and left interfaces (66, 68) as well as a second wall (88.2) pressed against the right or left lateral face (64.1, 64.2) of the primary structure (58) and connected to the primary structure (58) by at least one connecting element (88.3); the first wall (88.1) comprising, for each of the first, second and third interface connecting axes (74, 76, 82) which passes through it, a through orifice sized so that the first, second or third interface connecting axis (74, 76, 82) is immobile in translation, in a transverse plane, relative to the first wall (88.1).

6. Aircraft according to the preceding claim, characterized in that, for each right and left interface (66, 68), the engine attachment system (60) comprises a front reinforcing bracket (88), positioned at the front of the right or left interface (66, 68), comprising a first wall (88.1) pressed against the front wing (66.1, 68.1) of the right or left interface (66, 68) and a second wall (88.2) pressed against the right or left lateral face (64.1, 64.2) of the primary structure (58) as well as a rear reinforcing bracket (88'), positioned at the rear of the right or left interface (66, 68), comprising a first wall (88.1) pressed against the rear wing (66.2, 68.2) of the right or left interface (66, 68) and a second wall (88.2) pressed against the right or left lateral face (64.1, 64.2) of the primary structure (58).

7. Aircraft according to one of claims 4 to 6, characterized in that each front and rear wing (66.1, 66.2, 68.1, 68.2) of each right and left interface (66, 68) comprises a side oriented towards the motorization (56) as well as an extension (90) positioned at said side and offset towards the motorization (56) relative to the rest of said side, said extension (90) having a through orifice (92) which houses the right or left emergency connecting axis (84, 86).

8. Aircraft according to one of claims 4 to 7, characterized in that the motorization (56) comprises, for each right or left emergency connecting shaft (84, 86), a transverse flange (94) positioned at least partially between the front and rear wings (66.1, 66.2, 68.1, 68.2) of the corresponding right or left interface (66, 68), said transverse flange (94) comprising a through-orifice which houses the right or left emergency connecting shaft (84, 86).

9. Aircraft according to one of claims 4 to 8, characterized in that the motorization (56) comprises, for the first engine connection axis (72), a first yoke (56.1) which has two wings between which the first shackle (70) is positioned as well as, for the second engine connection axis (80), a second yoke (56.2) which has two wings between which the second shackle (78) is positioned.

10. Aircraft according to one of the preceding claims, characterized in that the engine attachment system (60) comprises, for each right or left emergency connecting shaft (84, 86), a clearance between the right or left emergency connecting shaft (84, 86) as well as an element from among the engine (56) and the right or left interface (66, 68).

11. Aircraft according to one of the preceding claims, characterized in that the motorization (56) comprises, for each of the first and second engine connection shafts (72, 80), at least one through-orifice, which houses the first or second engine connection shaft (72, 80), dimensioned so that each of the first and second engine connection shafts (72, 80) is immobile in translation, in a transverse plane, relative to the motorization (56).

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