Propulsion system including a rear-mounted shock-absorbing engine mount; aircraft comprising at least one such propulsion system

Abstract

Propulsion assembly including a rear damping engine mount, aircraft comprising at least one such propulsion assembly. The invention relates to a propulsion assembly (30) comprising: an engine mount system (46), connecting a primary mast structure (42) and an engine (32), which includes several mounts (48, 50, 52) each having at least one engine anchor point (P48, P50, P52) on the engine (32), all the engine anchor points (P48, P50, P52) being approximately positioned in the same transverse plane (PT), a rear damping engine mount (66) connecting the primary structure (42) and the rear part (40.3) of the engine core (40), said rear damping engine mount (66) forming a force path which includes at least one elastically deformable element. This configuration optimizes the transfer of forces between the motor (32) and the primary structure (42). Figure 3

Description

Title of the invention: Propulsion assembly comprising a shock-absorbing rear engine mount, aircraft comprising at least one such propulsion assembly

[0001] The present application relates to a propulsion system comprising a rear damping engine mount and to an aircraft comprising at least one such propulsion system.

[0002] According to a configuration visible in figures 1 and 2, an aircraft 10 comprises several propulsion assemblies 12 which are positioned under the wing 14 of the aircraft 10.

[0003] A propulsion assembly 12 includes a motor 16, a nacelle (not shown in [Fig.2]) positioned around the motor 16 and a mast 18 connecting the motor 16 to the rest of the aircraft 10, in particular to the wing 14.

[0004] For the remainder of this description, a longitudinal direction X is parallel to the axis of rotation of the motor A16. A transverse plane is a plane perpendicular to the axis of rotation of the motor A16. A vertical median plane is a vertical plane passing through the axis A16 of the motor. A horizontal transverse direction Y is a direction perpendicular to the axis of rotation of the motor A16 and horizontal. A vertical transverse direction Z is a direction perpendicular to the axis of rotation of the motor A16 and vertical. A vertical median plane is a vertical plane containing the axis of rotation of the motor A16. The terms front and rear refer to the direction of airflow in the motor 16, which flows from front to rear.

[0005] The engine 16 includes a fan 20 which has a fan housing 20.1 and a reactor core 22 which has a front part 22.1 positioned inside the fan 20, a central part 22.2 and a rear part 22.3.

[0006] The mast 18 comprises a primary structure 24, in the form of a box, which is connected to the sail 14 by a sail attachment system 26 (represented in a simplified manner on [Fig.2] as it is outside the scope of the invention) and to the motor 16 by a motor attachment system 28. This primary structure 24 comprises a front end 24.1, a middle part 24.2 and a rear end 24.3.

[0007] According to an embodiment visible in [Fig. 2], the engine attachment system 28 comprises a first attachment 28.1 connecting the front end 24.1 of the primary structure 24 and the fan casing 20.1, a second attachment 28.2 connecting the front end 24.1 of the primary structure 24 and the front part 22.1 of the reactor core 22, and a third attachment 28.3 comprising two connecting rods, positioned symmetrically with respect to the vertical median plane of the motorization 16, connecting the median part 24.2 of the primary structure 24 and the front part 22.1 of the reactor core 22. According to this embodiment, the first, second and third attachments 28.1, 28.2, 28.3 are connected to the reactor core 22 at points positioned approximately in the same transverse plane PI.

[0008] In some cases, this solution does not allow optimal transfer of forces between the motor 16 and the primary structure 24 of the mast 18.

[0009] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0010] To this end, the invention relates to a propulsion system comprising: a. an engine comprising a fan and a reactor core having a front section, a central section and a rear section, b. a primary mast structure comprising a front end, a middle section and a rear end, c. a motor attachment system, linking the primary structure and the motorization, which includes several attachments each having at least one motor anchor point on the motorization, all motor anchor points being approximately positioned in the same transverse plane.

[0011] According to the invention, the propulsion assembly includes a rear damping engine attachment which has a first end connected to the primary structure and a second end connected to the rear part of the reactor core, said rear damping engine attachment forming a force path which includes at least one elastically deformable element.

[0012] This rear shock-absorbing engine mount makes it possible to filter out large forces while ensuring the absorption of smaller forces, such as the weight of the rear part of the reactor core.

[0013] According to another feature, the first and second ends are positioned along a substantially vertical line.

[0014] According to another feature, the rear damping engine attachment comprises at least one body, at least one connecting shaft linking the body and an element between the reactor core and the primary structure, positioned in a longitudinal and vertical plane, as well as at least one elastomer ring interposed between the body and the connecting shaft.

[0015] According to one embodiment, the body is a three-point shackle comprising at least one plate having three through holes. In addition, the shock-absorbing rear engine mount comprises first, second and third connecting pins housed respectively in the first, second and third through holes of the plate and each positioned in a vertical longitudinal plane; the first connecting axis linking the plate and the primary structure, the second and third connecting axes linking the plate and the reactor core.

[0016] According to another feature, the rear damping motor mount includes at least one elastomer ring interposed between each of the first, second and third connecting axes and the body.

[0017] According to another embodiment, the body comprises a base and first and second arms that form a flared V towards the reactor core and respectively comprise first and second through-holes. In addition, the rear shock-absorbing engine mount comprises a link connecting the body and the primary structure, as well as first and second connecting axes respectively housed in the first and second through-holes of the body and positioned in a longitudinal and vertical plane, the first and second connecting axes linking the body and the reactor core.

[0018] According to another configuration, the first and second branches are configured to obtain a damping effect through a design optimized in stiffness.

[0019] According to another feature, the rear damping motor mount includes at least one elastomer ring interposed between at least one of the first and second connecting axes and the body.

[0020] According to another feature, the body comprises a contact face pressed against the primary structure and a cylindrical spigot-type pin projecting from the contact face. In addition, the rear shock-absorbing motor mount comprises a housing, provided in the primary structure, configured to fit snugly against the cylindrical spigot-type pin and a retaining system configured to hold the body pressed against the primary structure; the cylindrical spigot-type pin of the body and the housing in the primary structure essentially ensuring the absorption of shear forces positioned in an approximately horizontal plane, the retaining system essentially ensuring the absorption of tensile forces oriented approximately vertically.

[0021] According to another feature, the rear damping engine attachment includes a "waiting fail-safe" type safety link connecting the body and the reactor core, configured not to generate a force path when the first and second link axes are in a state of operation and to generate an additional force path only in the event of failure of at least one of the first and second link axes.

[0022] According to another feature, the rear damping motor mount includes at least one elastomer ring interposed between each of the first and second connecting axes and the body.

[0023] According to another feature, each ring is made of a material having a stiffness depending on the desired damping effect.

[0024] The invention also relates to an aircraft comprising at least one propulsion assembly according to one of the preceding characteristics.

[0025] Other features and advantages will become apparent from the following description of the invention, given by way of example only, with reference to the accompanying drawings, among which:

[0026] [Fig-1] is a perspective view of an aircraft,

[0027] [Fig.2] is a side view of an aircraft propulsion assembly (without nacelle) illustrating a method of realizing earlier art,

[0028] [Fig.3] is a side view of an aircraft propulsion assembly (without nacelle) illustrating one embodiment of the invention,

[0029] [Fig.4] is a perspective view of an aircraft propulsion assembly (without gondola) illustrating one embodiment of the invention,

[0030] [Fig.5] is a side view of a primary structure and a motor attachment system illustrating one embodiment of the invention,

[0031] [Fig.6] is a top view of a primary structure and an attachment system engine illustrating one embodiment of the invention,

[0032] [Fig.7] is a perspective view of part of an engine attachment system illustrating one embodiment of the invention,

[0033] [Fig.8] is a front view of a rear shock-absorbing engine mount illustrating a method of embodiment of the invention,

[0034] [Fig.9] is a front view of a rear shock-absorbing engine mount illustrating a another embodiment of the invention.

[0035] According to an embodiment shown in Figures 3 and 4, a propulsion unit 30 comprises a motor 32, a nacelle (not shown) positioned around the motor 32, and a mast 34 configured to connect the propulsion unit 30, and more particularly the motor 32, to a wing 36 of an aircraft. The aircraft comprises at least one such propulsion unit 30.

[0036] The propulsion system 32 includes a fan 38 and a reactor core 40.

[0037] The fan 38 includes a fan casing 38.1. The reactor core 40 comprises, from front to rear, a forward section 40.1 positioned inside the fan 38, a central section 40.2, and a rear section 40.3 incorporating, in particular, high- and low-pressure turbines and providing a downstream connection to a nozzle (not shown). In one configuration, the central section 40.2 has a smaller cross-section than the forward and rear sections 40.1 and 40.3.

[0038] The mast 34 comprises a primary structure 42, in the form of a box, which is connected to the sail 36 by a sail attachment system 44 (represented in a simplified on [Fig.3] because outside the scope of the invention) and to the motorization 32 by a motor attachment system 46. This primary structure 42 comprises a front end 42.1, a middle part 42.2 and a rear end 42.3.

[0039] According to an embodiment visible in Figures 3 to 6, the engine attachment system 46 comprises a first attachment 48 connecting the front end 42.1 of the primary structure 42 and the fan casing 38.1, a second attachment 50 connecting the front end 42.1 of the primary structure 42 and the front part 40.1 of the reactor core 40, and a third attachment 52 connecting the middle part 42.2 of the primary structure 42 and the front part 40.1 of the reactor core 40. According to this embodiment, the first, second, and third attachments 48, 50, 52 are connected to the engine 32 at engine anchor points P48, P50, P52 positioned approximately in the same transverse plane PT.

[0040] As illustrated in [Fig.4], according to one embodiment, the first attachment 48 is configured to ensure the transfer of forces along the longitudinal direction X and the transverse and horizontal direction Y. According to a configuration visible in Figures 5 and 6, the first attachment 48 comprises a first vertical pivot axis A48, a cylindrical pin 48.1 of the spigot type, integral with the blower housing 38.1, vertical which has an axis coinciding with the first pivot axis A48 as well as a plate 48.2 integral with the front end 42.1 of the primary structure 42, substantially horizontal, which has an orifice 48.3 configured to house in a fitted manner the cylindrical pin 48.1 of the spigot type.

[0041] The second attachment 50 is configured to ensure a transfer of forces along the horizontal and vertical transverse directions Y and Z. According to a configuration visible in [Fig.7], the second attachment 50 comprises at least one three-point shackle 54, a first connecting axis A56.1 linking the three-point shackle 54 and the front end 42.1 of the primary structure 42 as well as the second and third connecting axes A56.2, A56.3 linking the three-point shackle 54 and the front part 40.1 of the reactor core 40.

[0042] The first, second and third connecting axes A56.1, A56.2, A56.3 are parallel to each other and positioned in substantially vertical planes.

[0043] The three-point shackle 54 comprises two plates 54.1, 54.2 that are substantially parallel to each other and slightly spaced apart. Each plate 54.1, 54.2 is approximately triangular and has three through holes for housing the connecting pins A56.1 to A56.3, positioned at the vertices of each plate 54.1, 54.2. In addition, the second attachment 50 comprises a first tab 58 integral with the front end 42.1 of the primary structure 42, positioned between the two plates 54.1, 54.2 of the three-point shackle 54, which has a hole for housing the first connecting pin A56.1 as well as at least a second tab 58' attached to the front part 40.1 of the reactor core 40, positioned between the two plates 54.1, 54.2 of the three-point shackle 54, which has two openings to accommodate the second and third connecting axes A56.2, A56.3.

[0044] The first, second and third connecting axes A56.1 to A56.3 can be spherically articulated.

[0045] According to an arrangement, each of the first, second and third connecting axes A56.1 to A56.3 forms an angle of approximately 15 to 45° with a transverse plane. In parallel, each plate 54.1, 54.2 of the three-point shackle 54 is positioned in a plane perpendicular to the first, second and third connecting axes A56.1 to A56.3.

[0046] The third attachment 52 is configured to ensure the transfer of forces along at least one longitudinal direction X. It comprises two connecting rods 60, positioned symmetrically with respect to the vertical median plane.

[0047] Each connecting rod 60 has a first end 60.1 connected to the midsection 42.2 of the primary structure 42 by a first connecting axis A60.1 and a second end 60.2 connected to the forward section 40.1 of the reactor core 40 by a second connecting axis A60.2. In one arrangement, each second connecting axis A60.2 is positioned in a substantially horizontal plane. In addition, each first connecting axis A60.1 is positioned in a substantially longitudinal and vertical plane. Thus, the first and second connecting axes A60.1 and A60.2 are oriented in two substantially perpendicular directions. However, the angular orientation of the connecting axes A60.1 and A60.2 could be oriented in two substantially parallel or intermediate directions without affecting the scope of the invention. According to one embodiment, these connecting axes A60.1 and A60.2 could also be hinged.

[0048] Each of the first and second ends 60.1, 60.2 of each connecting rod 60 includes a clevis.

[0049] The third attachment 52 comprises, for each connecting rod 60, a first lug 62 integral with the middle part 42.2 of the primary structure 42 and connected by the first connecting axis A60.1 to the clevis of the first end 60.1 of the connecting rod 60 and a second lug 64 integral with the front part 40.1 of the reactor core 40 and connected by the second connecting axis A60.2 to the clevis of the second end 60.2 of the connecting rod 60.

[0050] The first, second and third attachments 48, 50, 52 are not further described as they may be identical to those of the prior art.

[0051] Of course, the invention is not limited to this configuration for the engine mounting system. In any embodiment, the engine mounting system 46 comprises several mounts 48, 50, 52, each of which has at least one point motor anchoring points P48, P50, P52 on the motorization 32, all motor anchoring points P48, P50, P52 being positioned approximately in the same transverse plane PT; at least one of the attachments 48, 50, 52 comprising a rear anchoring point PA on the primary structure 42 located furthest back, at the level of the middle part 42.2 of the primary structure 42.

[0052] According to one feature of the invention, the propulsion assembly 30 comprises at least one rear damping engine attachment 66 which has at least one first end 66.1 connected to the primary structure 42 at an anchorage area offset rearward from the rear anchorage point PA of the engine attachment system 46, near the rear end 42.3 of the primary structure 42, and at least one second end 66.2 connected to the rear part 40.3 of the reactor core 40. The first and second ends 66.1, 66.2 are positioned in a substantially vertical plane.

[0053] As illustrated in [Fig. 4], this rear damping engine mount 66 is configured to provide load transfer in the horizontal and vertical transverse directions Y, Z. In one configuration, the rear damping engine mount 66 is configured to provide load transfer only in the horizontal and vertical transverse directions Y, Z. In another configuration, the rear damping engine mount 66 is configured to provide load transfer only in the horizontal transverse direction Y.

[0054] The rear shock-absorbing engine attachment 66 comprises at least one body 68 connected to at least one element among the reactor core 40 and the primary structure 42 by at least one pivot axis positioned in a longitudinal and vertical plane.

[0055] According to a first embodiment shown in [Fig. 8], the rear shock-absorbing engine mount 66 comprises a body 68 connected to the reactor core 40 by a first linkage 70 comprising at least one first linkage axis A70 positioned in a longitudinal and vertical plane, and to the primary structure 42 by a second linkage 72 comprising at least one second linkage axis A72 positioned in a longitudinal and vertical plane. The first and second linkage axes A70, A72 are substantially parallel to each other.

[0056] According to one configuration, the body 68 is a three-point shackle comprising at least one approximately triangular plate 74 having first, second, and third through holes 74.1, 74.2, 74.3 positioned at the three vertices of the triangular shape. According to one design, the three-point shackle comprises two identical plates 74 that are substantially parallel to each other and slightly spaced apart. The shock-absorbing rear motor mount 66 comprises first, second, and third connecting pins A70, A72, A72' housed respectively in the first, second, and third through holes 74.1, 74.2, 74.3, which have Each has a cylindrical body, at least one first lug 76, integral with the primary structure 42, which has an opening to accommodate the first connecting shaft A70, and at least one second lug 78, integral with the reactor core 40, which has two openings to accommodate the second and third connecting shafts A72, A72'. Thus, the first connecting shaft A70 connects the plate 74 and the first lug 76. The second and third connecting shafts A72, A72' connect the plate 74 and the second lug 78.

[0057] The first, second, third connecting axes A70, A72, A72' are substantially parallel to each other and each positioned in a longitudinal and vertical plane.

[0058] According to this first embodiment, the rear shock-absorbing engine mount 66 is configured to ensure the transfer of forces along the horizontal and vertical transverse directions Y, Z.

[0059] To obtain a damping effect, the rear damping motor mount 66 includes at least one elastomer ring 80 interposed between one of the first, second and third connecting axes A70, A72, A72' and the body 68. According to one arrangement, the rear damping motor mount 66 includes at least one elastomer ring 80 interposed between each of the first, second and third connecting axes A70, A72, A72' and the body 68.

[0060] Each ring 80 has a stiffness depending on the desired damping effect. To give an order of magnitude, a ring 80 has a thickness (distance separating the inner wall in contact with a connecting shaft and the outer wall in contact with the body 68) of between 10 and 40 mm.

[0061] According to a second embodiment shown in [Fig. 9], the rear shock-absorbing engine mount 66 comprises a body 68' connected to the primary structure 42 by a first link 82 and to the reactor core 40 by a second link 84 comprising at least first and second connecting axes A84, A84' each approximately positioned in a longitudinal and vertical plane. The first and second connecting axes A84, A84' are substantially parallel to each other.

[0062] According to one configuration, the body 68' comprises a base 86.1 having a contact face F86.1 held against the primary structure 42, a cylindrical spigot-type pin 86.2 projecting from the contact face F86.1, and first and second arms 86.3, 86.4 forming a flared V towards the reactor core 40 and comprising first and second through holes 86.5, 86.6 respectively for housing the first and second connecting shafts A84, A84'. In addition, the rear shock-absorbing engine mount 66 comprises a housing 88, provided in the primary structure 42, configured to fit snugly the cylindrical spigot-type pin 86.2 and at least one tab 90, integral with the reactor core 40, which has first and second holes 90.1 and 90.2 are used to house the first and second A84 and A84' connecting axes, respectively. These axes connect the 68' body and the 40 reactor core.

[0063] According to one embodiment, the first and second arms 86.3, 86.4 are configured to achieve a damping effect through a design optimized for stiffness along the three directions X, Y, and Z. In addition, or alternatively, the rear damping motor mount 66 includes at least one elastomer ring interposed between one of the first and second connecting axes A84, A84' and the body 68'. According to one arrangement, the rear damping motor mount 66 includes at least one elastomer ring 80 interposed between each of the first and second connecting axes A84, A84' and the body 68'.

[0064] According to this configuration, the cylindrical spigot-type tenon 86.2 of the body 68' and the housing 88 of the primary structure 42 essentially ensure the transfer of shear forces (positioned in an approximately horizontal plane) between the body 68' and the primary structure 42. In addition, the rear shock-absorbing engine mount 66 includes a retaining system 86.7 (such as bolts inserted into sleeves, for example) configured to hold the base 86.1 of the body 68' against the primary structure 42 and essentially ensure the transfer of tensile forces oriented approximately vertically. This arrangement makes it possible to separate the transfer of shear forces positioned in a horizontal plane from that of tensile forces, oriented vertically.

[0065] Alternatively, the first link 82 comprises only vertical connecting elements (such as bolts) which indifferently take up shear and tensile forces.

[0066] According to one arrangement, the rear shock-absorbing engine attachment 66 includes a waiting fail-safe link 92 of the English type, connecting the body 68' and the reactor core 40, configured not to generate a load path when the first and second link axes A84, A84' are in working order and to generate an additional load path only in the event of failure of at least one of the first and second link axes A84, A84'.

[0067] According to this second embodiment, the rear damping engine mount 66 is configured to ensure the transfer of forces along the longitudinal, horizontal transverse and vertical directions X, Y, Z and by combination of the torsional moment Mx.

[0068] Regardless of the embodiment, the propulsion assembly comprises a shock-absorbing engine mount 66 having a first end 66.1 connected to the primary structure 42 at an anchorage area offset rearward relative to the rear anchorage point PA of the engine mount system 46, and a second end 66.2 connected to the rear portion 40.3 of the reactor core. This engine mount rear damping 66 forms a force path which includes at least one elastically deformable element to absorb by deformation part of the forces passing between the rear part 40.3 of the reactor core 40 and the primary structure 42. This elastically deformable element may be a ring, a sleeve or any other intercalated element.

[0069] This damping rear engine mount 66 generates a filtering force path that drains only the inertial forces originating solely from the rear section 40.3 of the reactor core 40, in which high- and low-pressure turbines are located. Thus, the damping rear engine mount 66 filters out significant forces while absorbing less significant forces, such as the weight of the rear section 40.3 of the reactor core 40.

Claims

Demands

1. Propulsion assembly (30) comprising: a. an engine (32) which includes a fan (38) and a reactor core (40) having a front portion (40.1), a central portion (40.2) and a rear portion (40.3), b. a primary mast structure (42) (34) which includes a front end (42.1), a mid-section (42.2) and a rear end (42.3), c. an engine attachment system (46), connecting the primary structure (42) and the engine (32), which includes several attachments (48, 50, 52) each having at least one engine attachment point (P48, P50, P52) on the engine (32), all the engine attachment points (P48, P50, P52) being approximately positioned in the same transverse plane (PT), d. characterized in that the propulsion assembly (30) includes a rear shock-absorbing motor mount (66) which has a first end (66.1) connected to the primary structure (42) and a second end (66.2) connected to the rear part (40.3) of the reactor core (40) and in that said rear damping engine attachment (66) forms a force path which includes at least one elastically deformable element.

2. Propulsion assembly according to the preceding claim, characterized in that the first and second ends (66.1, 66.2) are positioned along a substantially vertical line.

3. Propulsion assembly according to any one of the preceding claims, characterized in that the rear damping motor attachment (66) comprises at least one body (68, 68'), at least one connecting shaft linking the body (68, 68') and an element among the reactor core (40) and the primary structure (42), positioned in a longitudinal and vertical plane, as well as at least one elastomer ring (80) interposed between the body (68, 68') and the connecting shaft.

4. Propulsion assembly according to the preceding claim, characterized in that the body (68) is a three-point shackle comprising at least one plate (74) having three through holes (74.1, 74.2, 74.3) and in that the rear motor mount dampable (66) includes first, second and third connecting axes (A70, A72, A72') housed respectively in the first, second and third through holes (74.1, 74.2, 74.3) of the plate (74) and each positioned in a vertical longitudinal plane; the first connecting axis linking the plate (74) and the primary structure (42), the second and third connecting axes (A72, A72') linking the plate (74) and the reactor core (40).

5. Propulsion assembly according to the preceding claim, characterized in that the rear damping motor attachment (66) comprises at least one elastomer ring (80) interposed between each of the first, second and third connecting axes (A70, A72, A72') and the body (68).

6. Propulsion assembly according to claim 3, characterized in that the body (68') comprises a base (86.1) and first and second arms (86.3, 86.4) which form a flared V towards the reactor core (40) and comprise respectively first and second through ports (86.5, 86.6) and that the rear damping motor attachment (66) comprises a link (82) connecting the body (68') and the primary structure (42) and first and second link shafts (A84, A84') respectively housed in the first and second through ports (86.5, 86.6) of the body (68') and positioned each in a longitudinal and vertical plane, the first and second link shafts (A84, A84') connecting the body (68') and the reactor core (40).

7. Propulsion assembly according to the preceding claim, characterized in that the first and second arms (86.3, 86.4) are configured to obtain a damping effect through a design optimized in stiffness.

8. Propulsion assembly according to any one of claims 6 to 7, characterized in that the rear damping motor mount (66) comprises at least one elastomer ring interposed between at least one of the first and second connecting axes (A84, A84') and the body (68').

9. Propulsion assembly according to any one of claims 6 to 8, characterized in that the body (68') comprises a contact face (F86.1) pressed against the primary structure (42) and a cylindrical spigot-type tenon (86.2) projecting from the contact face (F86.1), and in that the rear shock-absorbing motor mount (66) includes a housing (88), provided at the level of the primary structure (42), configured to house in a fitted manner the cylindrical tenon (86.2) of the spigot type and a retaining system (86.7) configured to hold the body (68') pressed against the primary structure (42); the cylindrical tenon (86.2) of the spigot type of the body (68') and the housing (88) of the primary structure (42) essentially ensuring a transfer of shear forces positioned in an approximately horizontal plane, the retaining system (86.7) essentially ensuring a transfer of tensile forces oriented approximately vertically.

10. Propulsion assembly according to any one of claims 6 to 9, characterized in that the rear damping engine attachment (66) includes a waiting fail-safe link (92) of the "waiting fail-safe" type, connecting the body (68') and the reactor core (40), configured not to generate a force path when the first and second link axes (A84, A84') are in a functioning condition and to generate a force path in the event of failure of at least one of the first and second link axes (A84, A84').

11. Propulsion assembly according to any one of claims 6 to 10, characterized in that the rear damping motor mount (66) comprises at least one elastomer ring (80) interposed between each of the first and second connecting axes (A84, A84') and the body (68').

12. Propulsion assembly according to any one of claims 3 to 11, characterized in that each ring (80) is made of a material having a stiffness depending on the desired damping effect.

13. Aircraft comprising at least one propulsion assembly according to one of the preceding claims.

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