Aircraft comprising at least one engine attachment system with reduced vertical volume

Abstract

The invention relates to an aircraft comprising at least one engine attachment system (60) connecting a main structure (58) of a pylon with a motor (56), having: a right interface (66) connected to a right lateral face (64.1) of the main structure (58); a left interface (68) connected to a left lateral face (64.2) of the main structure (58); first and second links (70, 78) connecting the right and left interfaces (66, 68) to the motor (56) by means of engine connection pins (72, 80) and interface connection pins (74, 76, 82); a right emergency connection pin (84) cooperating with the right interface (66) and the motor (56); and a left emergency connection pin (86) cooperating with the left interface (68) and the motor (56). This arrangement makes it possible to obtain a relatively compact engine attachment system (60) in the vertical direction.

Description

Technical Field

[0001] The present application relates to an aircraft comprising at least one engine attachment system with reduced vertical volume. Background Art

[0002] According to Figure 1 and Figure 2 In the embodiment shown in FIG. 1 , the aircraft 10 includes a plurality of propulsion assemblies 12 positioned below each wing 14 of the aircraft. Each propulsion assembly 12 includes a motor 16, a nacelle ( Figure 2 ), and a pylon 18 connecting the motor 16 to the wing 14. The pylon 18 includes a main structure 20 connected to the motor 16 by an engine attachment system 22 and to the wing 14 by a wing attachment system 24.

[0003] For the present invention, the longitudinal direction X is substantially parallel to the rotation axis A16 of the motor 16. The vertical midplane PMV is a vertical plane passing through the rotation axis A16. The transverse plane is a plane perpendicular to the rotation axis A16. The horizontal transverse direction Y is a horizontal direction perpendicular to the rotation axis A16. The vertical direction is denoted Z in the various figures. The term front / rear refers to the flow direction of an airflow flowing from front to rear in the longitudinal direction X.

[0004] The engine attachment system 22 includes a forward engine attachment system 26 , a rearward engine attachment system 28 , and a pair of thrust rods 30 for reacting thrust.

[0005] according to Figure 3 , for the rear engine attachment system 28 , the primary structure 20 includes a base plate 32 positioned generally in a horizontal plane.

[0006] Furthermore, the rear engine attachment system 28 comprises a transverse beam 34 having a bearing surface F34 pressed against the base plate 32 , the transverse beam 34 being connected to the main structure 20 by means of a connecting element 36 .

[0007] The rear engine attachment system 28 includes: a first L-shaped link 38 having a first end 38.1, a second end 38.2 and a middle area 38.3, o a first engine connecting pin 40, which connects the first end 38.1 of the first link 38 to the motor 16, o a first beam connecting pin 42, which connects the second end 38.2 of the first link 38 with the transverse beam 34, o a second beam connecting pin 44 connecting the middle region 38 . 3 of the first link 38 with the transverse beam 34 ; a second link 46 having a first end 46.1 and a second end 46.2, o A second engine connecting pin 48, which connects the first end 46.1 of the second link 46 to the motor 16, o A third beam connecting pin 50, which connects the second end 46.2 of the second link 46 with the transverse beam 34; An emergency connection pin 52 which directly connects the transverse beam 34 to the motor 16 in the event of a failure, this emergency connection pin being positioned at the vertical median plane PMV.

[0008] The connecting pins 40 , 42 , 44 , 48 , 50 , 52 are substantially parallel to one another and to the longitudinal direction X.

[0009] according to Figure 3 In the embodiment shown in FIG. 1 , the transverse beam 34 must be positioned below the main structure 20 of the pylon 18. This arrangement results in a considerable volume in the vertical direction and this tends to limit the diameter of the motor 16 and more specifically of its fan casing 16.1. Summary of the invention

[0010] The purpose of the present invention is to remedy all or some of the deficiencies of the prior art.

[0011] To this end, the invention relates to an aircraft comprising at least one motor, at least one main structure of a pylon, and at least one engine attachment system connecting the main structure to the motor, the main structure having a lower face and a right lateral face and a left lateral face positioned on either side of a vertical median plane, the engine attachment system having: at least one first L-shaped link positioned in the transverse plane, the first L-shaped link having a first end and a second end and a middle area, - a first engine connecting pin connecting the first end of the first link to the motor, at least one second link positioned in the transverse plane, the at least one second link having a first end and a second end, - A second engine connecting pin connecting the first end of the second link to the motor.

[0012] According to the present invention, the engine attachment system comprises: - a right side interface, which is connected to the right side lateral surface of the main structure, - a left side interface, which is connected to the left side lateral surface of the main structure, - a first interface connecting pin, the first interface connecting pin connecting the second end of the first link and the first interface among the right interface and the left interface, - a second interface connecting pin, which connects the middle area of ​​the first link with the first interface, a third interface connecting pin, the third interface connecting pin connecting the second end of the second link to a second interface different from the first interface among the right interface and the left interface, - a right emergency connection pin, which cooperates with the right interface and the motor, - A left emergency connection pin cooperating with the left interface and the motor.

[0013] According to this arrangement, since the right and left interfaces are not positioned below the main structure but on the lateral surfaces thereof, the engine attachment system is relatively compact in the vertical direction, and this makes it possible to mount a motor of a larger diameter.

[0014] According to another feature, the first, second and third interface connection pins are located at or offset upwardly relative to a lower plane passing through a lower face of the primary structure.

[0015] According to another feature, for each of the first interface connecting pin and the second interface connecting pin, the first interface among the right interface and the left interface includes at least one through hole, the at least one through hole accommodates the first interface connecting pin or the second interface connecting pin, and the size of the at least one through hole is designed so that the first interface connecting pin or the second interface connecting pin is not translationally movable relative to the first interface in a transverse plane. At the same time, the second interface among the right interface and the left interface includes at least one through hole, the at least one through hole accommodates the third interface connecting pin, and the size of the at least one through hole is designed so that the third interface connecting pin is not translationally movable relative to the second interface in a transverse plane.

[0016] According to another feature, each right-side interface or left-side interface comprises a forearm and a rear arm, and a right-side base or a left-side base, wherein the forearm and the rear arm are positioned in a transverse plane, parallel to each other and slightly spaced apart, the right-side base or the left-side base connecting the forearm and the rear arm, and the right-side base or the left-side base is connected to the main structure by at least one connecting element.

[0017] According to another feature, the engine attachment system includes at least one reinforcement bracket, which has a first wall and a second wall, the first wall pressing against one of the front arm and the rear arm of the right interface and the left interface, the second wall pressing against the right lateral surface or the left lateral surface of the main structure and connected to the main structure by at least one connecting element; for each of the first interface connecting pin, the second interface connecting pin, and the third interface connecting pin passing through the first wall, the first wall has a through hole, the size of the through hole is designed so that the first interface connecting pin, the second interface connecting pin or the third interface connecting pin is non-translationally movable relative to the first wall in a transverse plane.

[0018] According to another feature, for each right-side interface and left-side interface, the engine attachment system includes a front reinforcement bracket and a rear reinforcement bracket, the front reinforcement bracket is positioned at the front of the right-side interface or the left-side interface, the front reinforcement bracket has a first wall and a second wall, the first wall presses against the front arm of the right-side interface or the left-side interface, and the second wall presses against the right-side lateral surface or the left-side lateral surface of the main structure; the rear reinforcement bracket is positioned at the rear of the right-side interface or the left-side interface, the rear reinforcement bracket has a first wall and a second wall, the first wall presses against the rear arm of the right-side interface or the left-side interface, and the second wall presses against the right-side lateral surface or the left-side lateral surface of the main structure.

[0019] According to another feature, each front arm and rear arm of each right-side interface and left-side interface includes a side oriented toward the motor, and an extension positioned on the side and offset toward the motor relative to the rest of the side, the extension having a through hole for accommodating a right-side emergency connection pin or a left-side emergency connection pin.

[0020] According to another feature, for each right-side emergency connecting pin or left-side emergency connecting pin, the motor includes a lateral flange, which is at least partially positioned between the front arm and the rear arm of the corresponding right-side interface or left-side interface, and the lateral flange has a through hole for accommodating the right-side emergency connecting pin or the left-side emergency connecting pin.

[0021] According to another feature, the motor comprises a first fork head for a first engine connecting pin, having two arms between which a first link is positioned, and a second fork head for a second engine connecting pin, having two arms between which a second link is positioned.

[0022] According to another feature, for each right emergency connection pin or left emergency connection pin, the engine attachment system includes a gap between the right emergency connection pin or left emergency connection pin and an element between the motor and the right interface or the left interface.

[0023] According to another feature, for each of the first engine connecting pin and the second engine connecting pin, the motor includes at least one through hole for accommodating the first engine connecting pin or the second engine connecting pin, and the size of the at least one through hole is designed so that each of the first engine connecting pin and the second engine connecting pin is non-translationally movable relative to the motor in a transverse plane. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Further features and advantages will become apparent from the following description of the invention, which is given by way of example only with reference to the accompanying drawings, in which: - Figure 1 This is a side view of the aircraft. - Figure 2 is the side view of the motor. - Figure 3 is a front view of an engine attachment system showing an embodiment of the prior art, - Figure 4 is a perspective view of an engine attachment system illustrating an embodiment of the present invention, - Figure 5 is Figure 4 Front view of the engine attachment system visible in the - Figure 6 yes Figure 4 A side view of the engine attachment system is visible in the - Figure 7 yes Figure 4 Front view of the engine attachment system visible in Figure 1, showing a failure in one of the links. - Figure 8 Depicted Figure 4 A side view of the engine attachment system visible in Figure 1, showing a variety of different failures. DETAILED DESCRIPTION

[0025] The aircraft comprises at least one motor 56, at least one main structure 58 of the pylon, and at least one engine attachment system 60 connecting the motor 56 to the main structure 58. According to one arrangement, the engine attachment system 60 (called the rear engine attachment system) is moved away from the fan case of the motor 56.

[0026] The motor 56 has a vertical mid-plane PMV and a substantially cylindrical housing in line with the engine attachment system 60 .

[0027] according to Figures 4 to 8In the embodiment visible in FIG. 5 , the main structure 58 comprises a lower face 62 substantially perpendicular to the vertical median plane PMV, and a right lateral face 64.1 and a left lateral face 64.2 positioned on either side of the vertical median plane PMV and above the lower face 62. According to one configuration, each right lateral face 64.1 or left lateral face 64.2 forms an angle with the vertical median plane PMV in a transverse plane between 0 and 20°, the right lateral face 64.1 and the left lateral face 64.2 flaring upwards.

[0028] The engine attachment system 60 includes: a right interface 66 connected to the right lateral face 64 . 1 of the main structure 58 , a left-hand interface 68 connected to the left-hand lateral face 64 . 2 of the main structure 58 , at least one first L-shaped link 70 positioned in a transverse plane, the at least one first L-shaped link having a first end 70.1, a second end 70.2 and a middle area 70.3 located at the bending area of ​​the first L-shaped link 70, o a first engine connecting pin 72, which connects the first end 70.1 of the first link 70 with the motor 56, o A first interface connecting pin 74, which connects the second end 70.2 of the first link 70 with the first interface among the right interface 66 and the left interface 68, o A second interface connecting pin 76, which connects the middle area 70.3 of the first link 70 with the first interface; at least one second link 78 positioned in the transverse plane, the at least one second link having a first end 78.1 and a second end 78.2, o A second engine connecting pin 80, which connects the first end 78.1 of the second link 78 to the motor 56, A third interface connecting pin 82, which connects the second end 78.2 of the second link 78 with the second interface of the right interface 66 and the left interface 68; a right emergency connection pin 84 which cooperates with the right interface 66 and the motor 56 , A left emergency connection pin 86 which cooperates with the left interface 68 and the motor 56 .

[0029] The engine connection pin, the interface connection pin and the emergency connection pin are parallel to each other and to the longitudinal direction X.

[0030] According to this arrangement, the right side interface 66 and the left side interface 68 are two different and separate elements. Since the right side interface 66 and the left side interface 68 are not located below the main structure 58 but on its lateral surface, the engine attachment system 60 is relatively compact in the vertical direction, and this makes it possible to install a larger diameter motor 56.

[0031] According to one configuration, the interface connection pins 74, 76, 82 are located at or offset upward relative to a lower plane passing through the lower face 62 of the main structure 58. This arrangement makes it possible to further reduce the vertical volume.

[0032] According to one embodiment, a first interface connection pin 74 connected to the second end 70 . 2 of the first L-shaped link 70 is positioned between the primary structure 58 and a second interface connection pin 76 connected to the middle region 70 . 3 of the first link 70 .

[0033] According to one arrangement, each first L-shaped link 70 is connected to the right interface 66 and each second link 78 is connected to the left interface 68. In a variation, each first L-shaped link 70 may be connected to the left interface 68 and each second link 78 may be connected to the right interface 66.

[0034] For each engine connecting pin 72, 80 and each interface connecting pin 74, 76, 82, each first link 70 or second link 78 includes a through hole that accommodates the engine connecting pin 72, 80 or the interface connecting pin 74, 76, 82, and the size of the through hole is designed so that each engine connecting pin 72, 80 or the interface connecting pin 74, 76, 82 is non-translationally movable in a transverse plane relative to the first link 70 or the second link 78.

[0035] For each of the first interface connection pin 74 and the second interface connection pin 76, the first interface among the right interface 66 and the left interface 68 includes at least one through hole, the at least one through hole accommodates the first interface connection pin 74 or the second interface connection pin 76, and the size of the at least one through hole is designed so that the first interface connection pin 74 or the second interface connection pin 76 is not translationally movable relative to the first interface in the transverse plane. In addition, the second interface among the right interface 66 and the left interface 68 includes at least one through hole, the at least one through hole accommodates the third interface connection pin 82, and the size of the at least one through hole is designed so that the third interface connection pin 82 is not translationally movable relative to the second interface in the transverse plane. Therefore, in normal operation, each interface connection pin 74, 76, 82 is configured to transmit force between the right interface 66 and the left interface 68 and the first link 70 and the second link 78 at least in the transverse plane.

[0036] For each motor connecting pin 72, 80, the motor 56 includes at least one through hole for the motor connecting pin 72, 80, the at least one through hole being sized such that each motor connecting pin 72, 80 is not translationally movable in a transverse plane relative to the motor 56. Thus, in normal operation, each motor connecting pin 72, 80 is configured to transmit forces between the motor 56 and the corresponding first link 70 or second link 78 at least in a transverse plane.

[0037] The right side interface 66 includes at least one right side arm 66.1, which is positioned in a transverse plane and is passed through at least one of the first interface connecting pin 74, the second interface connecting pin 76, and the third interface connecting pin 82. The left side interface 68 includes at least one left side arm 68.1, which is positioned in a transverse plane and is passed through at least one of the first interface connecting pin 74, the second interface connecting pin 76, and the third interface connecting pin 82.

[0038] According to one configuration, the right side interface 66 includes a right side forearm 66.1 and a right side rear arm 66.2, and a right side base 66.3, wherein the right side forearm and the right side rear arm are positioned in a transverse plane, parallel to each other and slightly spaced apart, and the right side base connects the right side forearm 66.1 and the right side rear arm 66.2, and the right side base 66.3 has a contact surface F66.3, which is pressed against the right side lateral surface 64.1 of the main structure 58 and is connected to the main structure 58 by at least one connecting element 66.4, and the at least one connecting element is typically a plurality of connecting elements 66.4 distributed in the vertical direction.

[0039] The left side interface 68 includes a left side forearm 68.1 and a left side rear arm 68.2, and a left side base 68.3, wherein the left side forearm and the left side rear arm are positioned in a transverse plane, parallel to each other and slightly spaced apart, the left side base connects the left side forearm 68.1 and the left side rear arm 68.2, and the left side base 68.3 has a contact surface F68.3, which is pressed against the left side lateral surface 64.2 of the main structure 58 and is connected to the main structure 58 by at least one connecting element 68.4, and the at least one connecting element is typically a plurality of connecting elements 68.4 distributed in the vertical direction.

[0040] In addition, the engine attachment system 60 includes a single first link 70 and a single second link 78, wherein the first link is placed between the front arms 66.1, 68.1 and the rear arms 66.2, 68.2 of the right interface 66 or the left interface 68, and the second link is placed between the front arms 66.1, 68.1 and the rear arms 66.2, 68.2 of the right interface 66 or the left interface 68.

[0041] Finally, the motor 56 comprises a first fork head 56.1 for the first engine connecting pin 72, having two arms between which the first link 70 is positioned, and a second fork head 56.2 for the second engine connecting pin 80, the first fork head having two arms between which the second link 78 is positioned.

[0042] According to another configuration, each right interface 66 and left interface 68 includes a single right arm 66.1 or left arm 68.1. In addition, the engine attachment system 60 includes two first links 70 positioned on both sides of a first arm among the right arm and the left arm, and two second links 78 positioned on both sides of a second arm different from the first arm among the right arm and the left arm.

[0043] Regardless of the configuration, each right or left interface 66, 68 has a contact surface 66.3, 68.3 pressed against the right or left lateral surface 64.1, 64.2, which does not extend against the lower surface 62 and therefore does not extend beyond the right or left lateral surface 64.1, 64.2.

[0044] According to one embodiment, each right arm 66.1, 66.2 or left arm 68.1, 68.2 has a substantially triangular profile with a first side C1, a second side C2 and a third side C3, the first side being pressed against the main structure 58, extending from the lower face 62 of the main structure 58, the second side being positioned approximately in the continuation of the lower face 62 of the main structure 58 and being approximately in a horizontal plane, the second side C2 and the third side C3 being connected by a rounded vertex, the second interface connection pin 76 connected to the middle region 70.3 of the first link 70 or the third interface connection pin 82 connected to the second end 78.2 of the second link 78 being positioned at the rounded vertex. The front arm 66.1, 68.1 and the rear arm 66.2, 68.2 of each right interface 66 or left interface 68 have the same profile. Regardless of the embodiment, each right arm 66.1, 66.2 or left arm 68.1, 68.2 includes a side oriented toward the motor 56.

[0045] According to one embodiment, the engine attachment system 60 comprises at least one reinforcing bracket 88, the at least one reinforcing bracket having a first wall 88.1, which is pressed against one of the right front arm 66.1, the right rear arm 66.2, the left front arm 68.1 or the left rear arm 68.2, and a second wall 88.2, which is pressed against the right lateral face 64.1 or the left lateral face 64.2 and is connected to the main structure 58 by at least one connecting element 88.3, ​​which is usually a plurality of connecting elements 88.3 distributed in the vertical direction. For each interface connection pin 74, 76, 82 passing through each first wall, each first wall 88.1 comprises a through hole for accommodating the interface connection pin 74, 76, 82, the size of which is designed so that the interface connection pin 74, 76, 82 is non-translationally movable in the transverse plane relative to the first wall 88.1. Therefore, in normal operation, each of the first interface connecting pin 74, the second interface connecting pin 76 and the third interface connecting pin 82 is configured to transmit force between the first wall 88.1 of the reinforcing bracket 88 and the first link 70 or the second link 78, at least in a transverse plane, the first link or the second link being passed through by the first interface connecting pin 74, the second interface connecting pin 76 or the third interface connecting pin 82.

[0046] According to one configuration, the engine attachment system 60 includes a reinforcement bracket 88 , 88 ′ for each front arm 66 . 1 , 68 . 1 and rear arm 66 . 2 , 68 . 2 of each right and left interface 66 , 68 . Therefore, for each right-side interface 66 and left-side interface 68, the engine attachment system 60 includes a front reinforcement bracket 88 and a rear reinforcement bracket 88', the front reinforcement bracket being positioned at the front of the right-side interface 66 or the left-side interface 68, the front reinforcement bracket having a first wall 88.1 and a second wall 88.2, the first wall pressing against the front arms 66.1, 68.1 of the right-side interface 66 or the left-side interface 68, the second wall pressing against the right-side lateral surface 64.1 or the left-side lateral surface 64.2 of the main structure 58 at the front of the right-side interface or the left-side interface 66, 88, the rear reinforcement bracket being positioned at the rear of the right-side interface 66 or the left-side interface 68, the rear reinforcement bracket having a first wall 88.1 and a second wall 88.2, the first wall pressing against the rear arms 66.2, 68.2 of the right-side interface 66 or the left-side interface 68, the second wall pressing against the right-side lateral surface 64.1 or the left-side lateral surface 64.2 of the main structure 58 at the rear of the right-side interface 66 or the left-side interface 68.

[0047] According to one embodiment, each arm 66.1, 66.2, 68.1, 68.2 of each right-side interface 66 and left-side interface 68 includes an extension 90 positioned at its second side C2, which is oriented toward the motor 56 and offset toward the motor 56 relative to the rest of the second side C2, and the extension 90 has a through hole 92, which is designed to accommodate the right-side emergency connection pin 84 or the left-side emergency connection pin 86.

[0048] According to the first configuration, when the right-side interface 66 or the left-side interface 68 includes a single right-side arm 66.1 or a left-side arm 68.1, for each right-side emergency connection pin 84 or a left-side emergency connection pin 86, the motor 56 includes a fork-shaped head having two arms, and the extension 90 is at least partially positioned between the two arms, each of these arms having a through hole designed to accommodate the right-side emergency connection pin 84 or the left-side emergency connection pin 86.

[0049] According to the second configuration, when the right-side interface 66 or the left-side interface 68 includes a front arm 66.1, 68.1 and a rear arm 66.2, 68.2, for each right-side emergency connecting pin 84 or left-side emergency connecting pin 86, the motor 56 includes a lateral flange 94, which is at least partially positioned between the front arm 66.1, 68.1 and the rear arm 66.2, 68.2 of the corresponding right-side interface 66 or left-side interface 68, and the lateral flange 94 has a through hole designed to accommodate the right-side emergency connecting pin 84 or the left-side emergency connecting pin 86.

[0050] Regardless of the configuration, the right side emergency connection pin 84 or the left side emergency connection pin 86 provides a direct connection between each right side interface 66 or the left side interface 68 and the motor 56 in the event of a failure. For each right side emergency connection pin 84 or the left side emergency connection pin 86, the engine attachment system 60 includes a gap between the right side emergency connection pin 84 or the left side emergency connection pin 86 and one of the motor 56 and the right side interface 66 or the left side interface 68. The gap is calibrated to allow displacement between the motor 56 and the right side interface 66 or the left side interface 68 in the transverse plane during operation.

[0051] According to the first arrangement, the right emergency connection pin 84 or the left emergency connection pin 86 is integral with the right interface 66 or the left interface 68 , and a gap is provided between the right emergency connection pin 84 or the left emergency connection pin 86 and the motor 56 .

[0052] According to the second arrangement, the right emergency connection pin 84 or the left emergency connection pin 86 is integral with the motor 56, and a gap is provided between the right emergency connection pin 84 or the left emergency connection pin 86 and the right interface 66 or the left interface 68. Therefore, according to the second configuration, the right emergency connection pin 84 or the left emergency connection pin 86 is integral with the lateral flange 94 of the motor 56, and a gap is provided between the right emergency connection pin 84 or the left emergency connection pin 86 and each front arm 66.1, 68.1 and rear arm 66.2, 68.2 of the corresponding right interface 66 or the left interface 68.

[0053] like Figure 5 and Figure 6 As shown in FIG. 1 , in normal operation, the first engine connecting pin 72 and the second engine connecting pin 80 and the first interface connecting pin 74, the second interface connecting pin 76 and the third interface connecting pin 82 are configured to transmit forces between the motor 56 and the right and left interfaces 66, 68 and the optional 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 main structure 58 are configured to transmit forces between the right and left interfaces 66, 68 and the reinforcing brackets 88, 88' on the one hand and the main structure 58 on the other hand.

[0054] like Figure 7 As shown in the figure, in the event that the links 70, 78 are damaged, the right emergency connecting pin 84 or the left emergency connecting pin 86 connected to the right interface 66 or the left interface 68 connected to the damaged links 70, 78 is configured to ensure the transmission of force between the motor 56 and the right interface 66 and the left interface 68 in addition to the undamaged links, and compensate for the fault.

[0055] like Figure 8 As shown in part (A), in the event of a failure of the right interface 66 or the left interface 68, the front reinforcement bracket 88 and the rear reinforcement bracket 88' positioned on both sides of the damaged right interface 66 or the left interface 68 are configured to compensate for the failure and ensure at least partial transmission of force between the motor 56 and the main structure 58.

[0056] like Figure 8 As shown in part (B), in the event of failure of the front reinforcement bracket 88, the right interface 66 or the left interface 68 and the rear reinforcement bracket 88' positioned against the same right lateral surface 64.1 or left lateral surface 64.2 of the main structure 58 as the damaged front reinforcement bracket 88 are configured to compensate for the failure and ensure at least partial transmission of force between the motor 56 and the main structure 58.

[0057] like Figure 8As shown in part (C), in the event of failure of the rear reinforcement bracket 88', the right interface 66 or the left interface 68 and the front reinforcement bracket 88 positioned against the same right lateral surface 64.1 or left lateral surface 64.2 of the main structure 58 as the damaged rear reinforcement bracket 88' are configured to compensate for the failure and ensure at least partial transmission of force between the motor 56 and the main structure 58.

Claims

1. An aircraft, comprising at least one motor (56), at least one main structure (58) of a pylon, and at least one engine attachment system (60) connecting the main structure (58) and the motor (56), the main structure (58) having a lower surface (62), and a right lateral surface (64.1) and a left lateral surface (64.2) located on both sides of a vertical median plane (PMV), the engine attachment system having: at least one first L-shaped link (70), positioned in a transverse plane and having a first end (70.1) and a second end (70.2) and a middle area (70.3), - a first engine connecting pin (72) connecting the first end (70.1) of the first link (70) to the motor (56), - at least one second link (78), positioned in the transverse plane and having a first end (78.1) and a second end (78.2), - a second engine connecting pin (80) connecting the first end (78.1) of the second link (78) to the motor (56), The engine attachment system comprises: - a right side interface (66), which is connected to the right side lateral surface (64.1) of the main structure (58), - a left side interface (68), which is connected to the left side lateral surface (64.2) of the main structure (58), - a first interface connecting pin (74), the first interface connecting pin connecting the second end (70.2) of the first link (70) and the first interface among the right interface (66) and the left interface (68), - a second interface connecting pin (76), the second interface connecting pin connecting the middle area (70.3) of the first link (70) and the first interface, - a third interface connecting pin (82), the third interface connecting pin connecting the second end (78.2) of the second link (78) to a second interface different from the first interface among the right interface (66) and the left interface (68), - a right emergency connection pin (84) cooperating with the right interface (66) and the motor (56), - a left emergency connection pin (86) cooperating with the left interface (68) and the motor (56), The right side interface (66) includes: a forearm (66.1) and a rear arm (66.2), the forearm and the rear arm are positioned in a transverse plane, parallel to each other and slightly spaced apart; and a right side base (66.3) connecting the forearm and the rear arm, the right side base is connected to the main structure (58) via at least one connecting element (66.4); the left side interface (68) includes: a forearm (68.1) and a rear arm (68.1, 68.2), the forearm and the rear arm of the left side interface are positioned in a transverse plane, parallel to each other and slightly spaced apart; and a left side base (68.3) connecting the forearm and the rear arm of the left side interface, the left side base is connected to the main structure (58) via at least one connecting element (68.4).

2. The aircraft according to claim 1, wherein: The first interface connection pin (74), the second interface connection pin (76) and the third interface connection pin (82) are located at a lower plane passing through the lower surface (62) of the main structure (58) or are offset upward relative to the lower plane.

3. An aircraft according to any one of the preceding claims, wherein: For each of the first interface connecting pin (74) and the second interface connecting pin (76), the first interface among the right side interface (66) and the left side interface (68) includes at least one through hole, and the at least one through hole accommodates the corresponding first interface connecting pin (74) or the second interface connecting pin (76), and the size of the at least one through hole is designed so that the corresponding first interface connecting pin (74) or the second interface connecting pin (76) is non-translationally movable relative to the first interface in a transverse plane, and wherein the second interface among the right side interface (66) and the left side interface (68) includes at least one through hole, and the at least one through hole of the second interface accommodates the third interface connecting pin (82), and the size of the at least one through hole of the second interface is designed so that the third interface connecting pin (82) is non-translationally movable relative to the second interface in a transverse plane.

4. An aircraft according to any one of the preceding claims, wherein: The engine attachment system (60) includes at least one reinforcing bracket, the at least one reinforcing bracket having a first wall and a second wall, the first wall pressing against one of the front arm and the rear arm of the right interface (66) or the left interface (68), the second wall pressing against the right lateral surface (64.1) or the left lateral surface (64.2) of the main structure (58) and connected to the main structure (58) by at least one connecting element (88.3); for each of the first interface connecting pin (74), the second interface connecting pin (76) and the third interface connecting pin (82) passing through the first wall, the first wall has a through hole, the size of the through hole of the first wall is designed so that the corresponding first interface connecting pin (74), the second interface connecting pin (76) or the third interface connecting pin (82) is non-translationally movable relative to the first wall in a transverse plane.

5. The aircraft according to claim 4, wherein: For each of the right interface (66) and the left interface (68), the engine attachment system (60) includes a front reinforcement bracket (88) and a rear reinforcement bracket (88'), wherein the front reinforcement bracket is positioned at the front of the right interface (66) or the left interface (68), and the front reinforcement bracket has a first wall and a second wall, the first wall of the front reinforcement bracket presses against the front arm of the right interface (66) or the left interface (68), and the second wall of the front reinforcement bracket presses against the right lateral surface (64.1) or the left lateral surface (64.2) of the main structure (58); and the rear reinforcement bracket is positioned at the rear of the right interface (66) or the left interface (68), and the rear reinforcement bracket has a first wall and a second wall, the first wall of the rear reinforcement bracket presses against the rear arm of the right interface (66) or the left interface (68), and the second wall of the rear reinforcement bracket presses against the right lateral surface (64.1) or the left lateral surface (64.2) of the main structure (58).

6. An aircraft according to any one of the preceding claims, wherein: Each front arm and rear arm of each right interface (66) and left interface (68) includes a side oriented toward the motor (56), and an extension (90) positioned on the one side and offset toward the motor (56) relative to the rest of the one side, the extension (90) having a through hole (92) for accommodating a corresponding right emergency connection pin (84) or a left emergency connection pin (86).

7. An aircraft according to any one of the preceding claims, wherein: For each of the right emergency connection pin (84) and the left emergency connection pin (86), the motor (56) includes a lateral flange (94), which is at least partially positioned between the front arm and the rear arm of the corresponding right interface (66) or left interface (68), and the lateral flange (94) has a through hole to accommodate the corresponding right emergency connection pin (84) or left emergency connection pin (86).

8. An aircraft according to any one of the preceding claims, wherein: The motor (56) comprises a first fork head (56.1) for the first engine connecting pin (72) and a second fork head (56.2) for the second engine connecting pin (80), the first fork head having two arms between which the first link (70) is positioned, and the second fork head having two arms between which the second link (78) is positioned.

9. An aircraft according to any one of the preceding claims, wherein: For the right emergency connection pin (84), the engine attachment system (60) includes a gap between the right emergency connection pin (84) and an element between the motor (56) and the right interface (66), and for the left emergency connection pin (86), the engine attachment system (60) includes a gap between the left emergency connection pin (86) and an element between the motor (56) and the left interface (68).

10. An aircraft according to any one of the preceding claims, wherein: For each of the first engine connecting pin (72) and the second engine connecting pin (80), the motor (56) includes at least one through hole for accommodating the corresponding first engine connecting pin (72) or the second engine connecting pin (80), and the size of the at least one through hole of the motor is designed so that the corresponding first engine connecting pin (72) or the second engine connecting pin (80) is non-translationally movable relative to the motor (56) in a transverse plane.

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