Abstract: An aircraft rear structure comprising a substantially flat rear pressure bulkhead, with a first side and a second side, opposite to the first side. The aircraft rear structure also comprises a horizontal stabilizer and a vertical stabilizer which in turn comprises a first spar and a second spar. The first spar is attached to a first attachment zone of the second side of the rear pressure bulkhead via first attaching elements, and the second spar is attached to a second attachment zone of the second side of the rear pressure bulkhead via second attaching elements. The second attachment zone being different from the first attachment zone.

Abstract: An aircraft rear structure comprising a substantially flat rear pressure bulkhead, with a first side and a second side, opposite to the first side. The aircraft rear structure also comprises a horizontal stabilizer and a vertical stabilizer which in turn comprises a first spar and a second spar. The first spar is attached to a first attachment zone of the second side of the rear pressure bulkhead via first attaching elements, and the second spar is attached to a second attachment zone of the second side of the rear pressure bulkhead via second attaching elements. The second attachment zone being different from the first attachment zone.

Abstract: A propeller for an aircraft turbine engine comprising a plurality of vanes as well as a hub having a plurality of accommodating ports receiving the bases of said vanes, each vane base being rotatably mounted in its associated accommodating port. The propeller also has at least one vane retaining ring structure in the radial direction outwardly from the hub, being cladded around the latter.

Abstract: A pylon for attaching a turbine engine of an aircraft having a rigid structure including protruding fittings each having a first orifice and a plurality of ties to attach the pylon onto a wing of the aircraft, the plurality of ties comprising two side front ties to take the thrust forces, the two side front being secured to the first orifices of the protruding fittings to attach the rigid structure firmly to the wing. The plurality of ties further comprises a center front tie positioned between the two side front ties, the center front tie including a ball joint to take forces in a lateral direction of the rigid structure.

Abstract: An aircraft engine assembly including a turboshaft engine with a propeller and an attachment pylon intended to be laterally attached on a rear portion of the structure of the aircraft is disclosed. The pylon has an outer surface forming an aerodynamic profile incorporating a trailing edge which is arranged upstream of the propeller of the turboshaft engine. The pylon includes a mobile rear flap at least partially defining the trailing edge and a controller which steers the incidence of the flap according to a law depending on the incidence of the aircraft.

Abstract: A pylon for attaching a turbo-shaft aircraft engine designed to be laterally offset on a rear part of the aircraft structure, where the pylon possesses an aerodynamic profile which includes a leading edge, as well as a first hot air distribution channel passing along the leading edge in order to provide anti-icing, where this engine attachment pylon includes moreover a second hot air channel belonging to a system for supplying pressurized air to the aircraft. The second channel is housed inside the first channel.

Abstract: A securing mast for securing an engine to the wing of an aircraft, wherein the device includes two fasteners, a first end of each fastener being secured to the engine and the second end of each fastener being secured to the wing, wherein the fasteners include hinged junction means capable of modifying the geometry of the aforementioned fasteners in order to modify a distance between the engine and the wing.

Abstract: A propeller for an aircraft turbine engine comprising a plurality of vanes as well as a hub having a plurality of accommodating ports receiving the bases of said vanes, each vane base being rotatably mounted in its associated accommodating port. The propeller also has at least one vane retaining ring structure in the radial direction outwardly from the hub, being cladded around the latter.

Abstract: The invention relates to a pylon for attaching a turbine engine for an aircraft, having a rigid structure (10) and means for attaching the pylon on a wing of the aircraft, said means for attaching the pylon on the wing comprising two side front ties (11a, 11b) each designed so as to take the thrust forces and comprising a fitting (54) pierced with a first orifice (65) firmly attached to the rigid structure (10), as well as a yoke (66) firmly attached to the wing. According to the invention, a central front tie (15) positioned between the side ties comprises a ball joint (27), and is laid out between both side front ties so that the centre (72) of the ball joint is located, as seen along the transverse direction (Y), in each of the first two orifices (65) of the side front ties.

Abstract: A mount for an aircraft turbojet engine. The mount includes a central box formed by an assembly of two side panels joined via transverse ribs and two side boxes secured to a forward part of the box and arranged either side thereof, each side box including an aft closure frame. One of the ribs forming the box includes two side extensions made in a single piece with the rib and respectively projecting from the two side panels outwardly from the box, the two extensions being fixedly mounted on the frame of each of the two side boxes, respectively.

Abstract: An aircraft engine assembly including an engine and a mount device for the engine. The mount device can be positioned between a wing of the aircraft and the engine, and includes a rigid structure and a mechanism to mount the engine on the rigid structure, the mounting mechanism including a first attachment and a second attachment. The first attachment includes two side semi-attachments each fixed to a fan case of the engine, and the second attachment is fixed onto a forward part of a central case of the engine.

Abstract: An aircraft engine assembly including a turbojet engine, an engine mount, and a plurality of engine attachments. The engine attachments include first and second forward attachments fixed to a fan case and located symmetrically in relation to a plane defined by a longitudinal axis of the turbojet engine and a vertical direction thereof, both forward attachments configured to transfer loads exerted in a longitudinal direction of the turbojet engine and in the vertical direction thereof. Moreover, each of the two forward attachments includes a shear pin mounted on the case and going through two walls of a clevis fixed on the engine mount.

Abstract: The invention relates to an aircraft engine assembly, comprising a turboshaft engine with a propeller as well as an attachment pylon (14) intended to be laterally attached on a rear portion of the structure of the aircraft, the pylon having an outer surface (20) forming an aerodynamic profile incorporating a trailing edge (21), the latter being arranged upstream of the propeller of the turboshaft engine. According to the invention, the pylon comprises a mobile rear flap (24) at least partially defining the trailing edge (21), as well as a control means (34) of the flap designed to steer the incidence of the latter, according to a law depending on the incidence of the aircraft.

Abstract: A securing mast for securing an engine to the wing of an aircraft, wherein the device includes two fasteners, a first eng of each fastener being secured to the engine and the second end of each fastener being secured to the wing, wherein the fasteners include hinged junction means capable of modifying the geometry of the aforementioned fasteners in order to modify a distance between the engine and the wing.

Abstract: The invention relates to a turbojet suspension pylon for an aircraft, the pylon being provided with a rigid structure (10) comprising a longitudinal central box (22). According to the invention, the rigid structure also comprises two lateral boxes (24a, 24b) fixed to a forward part of said central box (22), the pylon also comprising a first (6a) and a second (6b) engine forward suspension designed to resist forces applied along the longitudinal direction (X) of the pylon, these first and second suspensions being arranged on the two lateral boxes respectively.

Abstract: The invention relates to a pylon (14) for attaching a turbo-shaft aircraft engine designed to be laterally offset on a rear part of the aircraft structure, where the pylon possesses an aerodynamic profile which includes a leading edge (16), as well as a first hot air distribution channel (30) passing along the leading edge in order to provide anti-icing, where this engine attachment pylon includes moreover a second hot air channel (36) belonging to a system for supplying pressurised air to the aircraft. According to the invention the second channel (36) is housed inside the first channel (30).

Abstract: A turbojet-mounting pylon for an aircraft. The pylon includes a rigid structure including a plurality of arcs arranged so as to jointly delimit a part of a fictitious approximately cylindrical surface with a circular section. The plurality of arcs also includes two lateral thrust resisting arcs located on each side of the central box, each of the two lateral arcs being fixed to each arc in the form of an annular portion, and on each side of the central box.

Abstract: An engine assembly for aircraft including a turboshaft engine, an attachment strut, and a plurality of engine mounts interposed between the attachment strut and the turboshaft engine. The plurality of engine mounts include two forward mounts arranged in a staggered manner in relation to each other in a vertical direction of the turboshaft engine, the first forward mount configured to assure uniquely taking up of stresses brought to bear along the transversal direction of the turboshaft engine, and the second forward mount configured to assure uniquely taking up of stresses brought to bear along the transversal and vertical directions.

Abstract: An engine assembly for aircraft including a turbojet, an attachment strut, and a plurality of engine mounts interposed between the attachment strut and the turbojet. Each of the engine mounts is attached to a fan casing of the turbojet.

Abstract: The invention relates to an aircraft engine assembly (1) including an engine (6) and an engine mounting device (4), the mounting device being designed to be inserted between a wing of the aircraft and the engine, and comprising a rigid structure (8) and means of mounting the engine onto the rigid structure, the mounting means comprising a forward fastener (10) and an aft fastener (12). According to the invention, the aft fastener comprises two aft half-fasteners (12a) that will each resist at least the forces applied along a longitudinal direction (X) of the engine, and the two aft half-fasteners are arranged so that a horizontal plane (P) passing through a longitudinal axis (5) of the engine passes through each of them.