Abstract: A propulsion assembly having a pylon, a turbomachine comprising an engine and a fan that is enclosed by a fan casing, a nacelle surrounding the engine and the fan casing and having a load support disposed in the top part of the nacelle, a front engine attachment between the pylon and a front part of the engine, a rear engine attachment between the pylon and a rear part of the engine, a front fan attachment between the fan casing and the load support, and a rear pylon attachment between the pylon and the load support. Such a propulsion assembly allows a reduction in bulk since the load of the turbojet engine is distributed between the load support and the pylon, and the pylon is attached to the engine.

Abstract: A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.

Abstract: A propulsion assembly having a pylon, a turbomachine comprising an engine and a fan that is enclosed by a fan casing, a nacelle surrounding the engine and the fan casing and having a load support disposed in the top part of the nacelle, a front engine attachment between the pylon and a front part of the engine, a rear engine attachment between the pylon and a rear part of the engine, a front fan attachment between the fan casing and the load support, and a rear pylon attachment between the pylon and the load support. Such a propulsion assembly allows a reduction in bulk since the load of the turbojet engine is distributed between the load support and the pylon, and the pylon is attached to the engine.

Abstract: An aircraft engine assembly including an attachment mechanism of a turbojet onto a rigid structure of a mounting strut, including a first, second, and third forward engine attachment for taking up thrust loads brought onto the fan frame, and arranged such that the third attachment passes through a first diametrical plane of the turbojet, the first and second attachments being disposed on one side and another of the first plane. The first and second forward engine attachments are respectively brought to the fan frame at two points, situated beyond the second diametrical plane of the turbojet, orthogonal to the first diametrical plane, with respect to the third attachment.

Abstract: An aircraft engine assembly including an annular structure surrounding a central casing and mechanically connected to the central casing by the intermediary of a mounting mechanism. To each of the first and second engine mounts is associated a reinforcing structure forming a shear plane, fixedly connected: in an area of the annular structure at a first anchoring point; in an area of the fan casing at a second anchoring point; and in an area of a structural arm or of the intermediate casing at a third anchoring point. The structure extends along a radial imaginary plane passing through an anchoring point of the mount on the fan casing.

Abstract: An aircraft engine assembly with an annular load-transfer structure surrounding the central casing (16) and mechanically connected to a plurality of substantially planar reinforcing structures (64a-c) arranged externally with respect to the annular load-transfer structure, and biasing it at a plurality of load application points (68a, 68b, 68c). At least one connecting rod is associated with a load application point, with the connecting rod positioned tangentially with respect to the casing (16), and having an inner end (62a) connected to this casing, as well as an outer end (62a) connected to the annular load-transfer structure (60) so that the outer end of the connecting rod is in an imaginary plane (66a, 66b, 66c) in which the annular load-transfer structure is located and which extends through the load application point.

Abstract: This invention relates to an aft pylon fairing (30) for a suspension system of an aircraft engine, comprising two side panels (44) assembled to each other by inner cross stiffening ribs (46) spaced at intervals from each other along a longitudinal direction (X) of the fairing, and also comprising a heat protection deck (32) designed to delimit an engine core flow (36). According to the invention, it also comprises two longitudinal connecting walls (58) offsetting the deck (32) from the ribs (46), each of these two longitudinal walls (58) being provided with a first side end (62) fixed to one or the other of the two side ends (60, 60) of the deck (32), and a second side end (64) rigidly fixed to the ribs (46).

Abstract: An engine is mounted on a structure by an intermediate structure assembled by flanges, to the structure and to the engine, where a rigid structure connects the flanges. This arrangement enables design of the structure to be simplified while allowing a substantial overhang when it is sought to mount the engine by the plane of its center of gravity, while being obliged to move the mounting structure away from it. The intermediate structure is resistant to forces resulting from the overhang, and also allows assemblies that are favorable to a balanced transmission of forces to the structure and a satisfactory ability to filter vibrations.

Abstract: An engine is suspended from a main linear portion of a structure mounted on a fuselage or a wing surface of an aircraft. A connection includes flat symmetrical wings at an angle to one another, to support an attaching flange on which the engine is mounted, directly or through a mounting element. The flat shape of the wings makes them easy to manufacture, and enables them to resist the forces satisfactorily. The intermediate element resists overhang forces of the mounting satisfactorily. Flexible connections filter the engine's vibrations and prevent irregular forces being transmitted.

Abstract: A rear part of an aircraft including a support structure for supporting engines, extending through the fuselage, through a first opening and a second opening. A connection structure connects the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The connection structure also includes at least one effort recovery connecting rod, the first end of which is mounted on the support structure and the opposite end is mounted on the fuselage, at a distance from the first and second openings.

Abstract: An engine is suspended from a main linear portion of a structure mounted on a fuselage or a wing surface of an aircraft. A connection includes flat symmetrical wings at an angle to one another, to support an attaching flange on which the engine is mounted, directly or through a mounting element. The flat shape of the wings makes them easy to manufacture, and enables them to resist the forces satisfactorily. The intermediate element resists overhang forces of the mounting satisfactorily. Flexible connections filter the engine's vibrations and prevent irregular forces being transmitted.

Abstract: An engine is mounted on a structure by an intermediate structure assembled by flanges, to the structure and to the engine, where a rigid structure connects the flanges. This arrangement enables design of the structure to be simplified while allowing a substantial overhang when it is sought to mount the engine by the plane of its center of gravity, while being obliged to move the mounting structure away from it. The intermediate structure is resistant to forces resulting from the overhang, and also allows assemblies that are favorable to a balanced transmission of forces to the structure and a satisfactory ability to filter vibrations.

Abstract: An aircraft engine assembly including an annular load-transfer structure surrounding the central casing and being mechanically connected to a plurality of substantially planar structures arranged externally with respect to the plurality of substantially planar structures, and biasing it at a plurality of load application points. At least one connecting rod is associated with each of the load application points, the connecting rod being positioned tangentially with respect to the casing, and including an inner end connected to this casing, and an outer end connected to the structure so that it has extending through it an imaginary plane in which the annular structure is located and extends through the load application point.

Abstract: A rear part of an aircraft including a support structure for supporting engines, extending through the fuselage, through a first opening and a second opening. A connection structure connects the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The connection structure also includes at least one effort recovery connecting rod, the first end of which is mounted on the support structure and the opposite end is mounted on the fuselage, at a distance from the first and second openings.

Abstract: An aircraft engine assembly including an attachment mechanism of a turbojet onto a rigid structure of a mounting strut, including a first, second, and third forward engine attachment for taking up thrust loads brought onto the fan frame, and arranged such that the third attachment passes through a first diametrical plane of the turbojet, the first and second attachments being disposed on one side and another of the first plane. The first and second forward engine attachments are respectively brought to the fan frame at two points, situated beyond the second diametrical plane of the turbojet, orthogonal to the first diametrical plane, with respect to the third attachment.

Abstract: An aircraft engine assembly including an annular structure surrounding a central casing and mechanically connected to the central casing by the intermediary of a mounting mechanism. To each of the first and second engine mounts is associated a reinforcing structure forming a shear plane, fixedly connected: in an area of the annular structure at a first anchoring point; in an area of the fan casing at a second anchoring point; and in an area of a structural arm or of the intermediate casing at a third anchoring point. The structure extends along a radial imaginary plane passing through an anchoring point of the mount on the fan casing.

Abstract: This invention relates to an aft pylon fairing (30) for a suspension system of an aircraft engine, comprising two side panels (44) assembled to each other by inner cross stiffening ribs (46) spaced at intervals from each other along a longitudinal direction (X) of the fairing, and also comprising a heat protection deck (32) designed to delimit an engine core flow (36). According to the invention, it also comprises two longitudinal connecting walls (58) offsetting the deck (32) from the ribs (46), each of these two longitudinal walls (58) being provided with a first side end (62) fixed to one or the other of the two side ends (60, 60) of the deck (32), and a second side end (64) rigidly fixed to the ribs (46).